REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
PART 8
ACCREDITATION
8-100
SCOPE
Part 8 provides rules for accreditation of Fabricators
vessels.
of RTP
8-200
GENERAL
(a) An accredited Fabricator is one wllo holds a valid
ASME RTP-I Certificate of Authorization.
(b) The responsibilities set forth herein relate only to
compliance with this Standard and are not to be construed as involving convactual or legal liabilities.
8-210
ASME RTP-1 Certificate of
Authorization Holders
The ASME RTP-1 Ctrtificate of Authorization holder
is the Fabricator of an RTP vessel who certifies thar tlte
vessel compIiw with all requirements of this Standard.
8-220
ASME RTP-1 Certificate of
Authorlza tlon Hofder's
Responsibillths
(4Use of the Cen$care and Symbol. When authorization is granted. each applicant agrees to the following:
(I] h e Cenificare and the S y h l art at all times
the property of ASME;
121 they shall be used according to the rules and
regulations of h i s Standard;
(3) they shall be promptly returned to ASME upon
demand or when the applicant discontinues the scope of
work covered by his Certificate.
Ib) Eramples of rhe ASME RIP-I Cem$cate Holder's Respomibiliries. Responsibilities include the following:
{fl obtaining an ASME RTP-I Certificate in accordance with para. 8 4 0 ;
(2) compIiaucc wilh this Standard:
(3) evaluation and approval of mteriat rnanufacturcrs and suppliers ofparts and s u b c o ~ c t c dservices
in accordance with Appendix Ma,
(4) establishing and maimaining a Quality Control
Program in accordance with Appendix M-6;
(51 filing of a Quality Contml Manud in accordance with p a . 8-220(g); and
(61 furrlishing the User or User's agcm with the
appropriate Fabricator's Data Repn:(s).
(c) ASME RTP-I CeniJScore of Aurhoriuttion. The
holder of a Certificate of Authorization shall not permit
any other party to use the Cenif~cateor RTP Symbol
issued to the holder.
(d) Conrpliance Wth 77th Sfandard. The ASME
RTP-I Certificate Holder shall fabricate vessels to be
marked RTP in corn~liliancewith this Standard.
(e) ~ubmnrracfini. It is the ASME RTP-1 Certificate Holder's responsibility to mure that the subcantracted acrivit ies comply with the appropriate
requirements of this Standard per para. 6-300. The
ASME RTP-I Ccnificace Holder sM1 retain overall Espnsibility, including certifying and marking vessels.
@ Responsibiiity for Qualip Assurance of Subcotjtmcted Acrivitic~~
The ASME RTP-1 Certificate Holder
shall be mponsibie for evaluation and approval of sup
pliers of subcontractad services. All subconuactad activities shall be surveyed and audited with at least the
m e scope and frequency as the ASME RTP-1 Certificate Holder. If the sukontractor is a holder of an
ASME RTP-1 Cenificare, no additional evaluation of
the subconmctor is required.
{g) Filing of Quality Control Manual. The ASME
RTP-I Certificate Holder shall fde and maintain a copy
of the ASME accepted Quality Control Manual with
ASME. If the M i c a t e Holder wishes to change the
program to a degree requiring changes to the manual,
the Certificate Holder shall submit the proposed changes
to ASME which shalI accept or reject them in writing.
ACCREDITATION FOR ASME
RTP-1 FABRICATORS
8-310
General
When requested by the applicant on forms designated by ASME, ASME will arrange for an evalua-
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
tion of the applicant's Quality Control Program and shop
q d c a t i o n s . Forms may be obtained by request to
Socie'y of
the Adtation
Depanment' Ibe
Mechanical Engineen,
Avenue. New York
NY 1001&5490.
8-320
(1) evaluation of the applicant's QualiCy Control
Manual and capability of implementation; d
(2) evaluation of the applicant's implementation of
the program described in his Quality Contro1 Manual.
@) The acceptance by ASME of a Quality Control
Program shall not be interpreted to mean endorsement
of technical capabfity to perform design work.
Evaluation of Shop Qualifications
The evaluation shall be in accordance with Pan 7.
8-400
ASME RTP-1 CERTIFICATE OF
AUTHORIZATION FOR VESSEL
FABRICATORS
8-410
General
A Fabricator shall obtain a valid Certificate of Authorization in accordance with para. 1-520, in order to
srnmp the vessel.
8-420
Application for Certificate of
Authorization
(al Each applicant shall identify the specific location(~)covered and state the scope and limits of any
activities for which authorization is granted. At its discretion. ASME may limit or extend the scope of an authorization.
@I The Certificate of Authorization shall include but
not be limited to the following scopes of work: shop
fabrication, shop and field fabrication, shop fabrication
and field modification or repair in accordice with Appendix M-9.All Cemficatt of Authorization hdders
shall be capable of both shop and field testing per para6-950.
Verification of Shop Quallflcatlon
An organization requesting accreditation shall have
i& &op[s) surveyed by an ASME appmved survey team
hr
ofpan 7
part 8 are
nut.
Issuance of ASME RTP-1 Certificate
Evaluation of the Quality Control
Program
(a) The evaluation consists of the following:
8-330
8-430
of Authorization
(a)The Certificate may IEgranted or withheld by
ASME at its discretion.
@) When satisfied ;hat the applicant has complied
with the requirements of this Standard. ASME shall issue an ASME RTP- 1 Ctnificate of Authorization. The
three-year certifica~tis issued to a Fabricator for a specific l d o n ( s ) as defined in the application and acq e d by ASME, and it shall describe the scope and
limits of work for which the applicant is accredited.
(c) If ASME RTP-1 authorization i s given and the
proper adminis~raiivefee is paid, the Cenificate of Authorization shall be forwarded to the applicant.
(d) Alter initial accreditation, ASME shall institute a
continuing audit program of the Certificate Holder's
Quality Control Program.
(e) Eadl Certificate shall be signed by duly authotixed ASME pesonnel.
If) Six months prior to the date of expiration of any
such Certificare, the applicant shall apply for a renewal
of authorbarion.
(g) Failure to apply for renewal of the Ceaificate in
time and with appropriate documentation may cause lass
of accreditation until such time as mccredilation procedures can be undertakenand all requirements for reaccreditation have been met.
0 ASME reserves the right to cancel or refuse to
renew accreditation.
8-450
Obtatnhg Stamps
AU stamps for applying the ASME RTP-I Symbol
shall be obtained from ASME. This Symbol i s shown
in Fig. 1-1.
8-460
Requirements Subject to Change
ASME may make requirements concerning the issuance and use of Certificates and Symbols as it deems
appropriate. Such requirements shall become binding on
thc Certificate Holder upon notification by ASME.
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
ASME RTP-1-1995 EDITION
MANDATORY APPENDIX M-l
MATERIAL SPECIFICATION FOR RTP LAMINATES
Article A of this Appendix is limited to fabication by
contact molding using the hand lay-up andlor sprayvp
methods. Anicle B of this Appendix describes thc hmination Analysis Method by which the modulus properties of filament wound laminates, including contact
molded layers, are obtained. Article C of this Appendix
descrik permissible rolerances for laminate thiclrnws
variation.
Appendix M-l is based on the requirement that each
Fabricator deveIop design basis data for the hand layup, spray -up, and filament wound laminates produced
by his shop. The design basis laminates become his shop
standards. Pmpenies of such laminates are used for design of equipment fabricated to this Standard by that
particular shop. The permitted laminates and qualification pmedures are described in Articles A and B. The
permissible tolerances for the thickness variation of uermined laminates are described in Article C.
MI-1 10
Resin and Reinforcement
Substitution
The Fabricator must use he same resins and reinforce men^ as identified by the Manufacturer's Specific
Product Identification (MSPI) as used in the design basis
laminates. with the exception of the surfacing veil (mat).
which may be changed as rrquimi for corrosion resistance.
M 1-200
MATERIALS
MI-210
Resin Matrix
The m i n shall be that polyester or vinyl ester specified by the User's Basic Requi~mcntsSpecification.
Only resins with an HDT of at least 180°F per ASTM
D 648 with a 264 psi loading and a % in. specimen, as
published by the resin manufacturer, shall be used.
When a maximum h e retardancy is specified by the
UBRS, the flame spread rating shall be determined by
the resin manufactu~raccording to ASTM E 84 using
dl mat laminates greater than 0.1 in. thick. verification
of the flame spread rating is not required as a
of
laminate qualification. Since flame spread can be determined only on flat laminate panels, verification is noi
raquired on fabricated equipment. Prior to use in laminate fabrications, the -in shall be inspected, tested,
and found acceptabIe by the inspections and tests specified in Appendix M-3.
(a)The cataly st/prornoter/acceleratorsystern shall bc
as recommended by the resin manufacturer and specified in the Fabricator's written pmcedures.
(b) The resin shall contain no pigment, dyes, colorants, or filler, except as follows.
( I ) A thixotropic agent which does not interfere
with visual inspection of laminate quality, or wirh the
required corrosion mistance of the laminate, may be
added for viscosity control.
NOTE: The addition of a thixanopic agent m y rrduee lhe mistance
of a lamimale to somc corrosive chemical environments. It i s tht rcspwmibility of the F a W r lo obtain ~ppmvdfrom h e elector of
the resin prior to using a rhixotropic agent in the inner surface (para.
M1A-22 I) or the inltrior layer (pa. M [A-222).
(2) Resin pastes used to fill crevices before overlay
shall not k subject to the limitations of para. MI210@).
(3) Pigments, dyes, or colorants may be added lo
the exterior surface when specified by the U8RS.
NOTE: The addhion o t pigmcnt. dyes. or colorants may inlcflem
with visual inspection of lmniuaw quaIity.
(4) Flame retardant synergists shall l
x used only
when required in the UBRS. If Eire retardant synergists
were usad to obtain the spacifkd ASTM E 84 flame
spread rating, the same type and amount must be used
in the laminate.
MOTE: The addition of fire rrtardglu qwFgisu m y interfere with
viswl inspocrion of laminatc quality.
(5) Common additives, as described in Appendix
M-3. Arricle G , may be added without requalifying the
standard laminate.
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
TABLE MIA-1
GRADE SYSTEM FOR HAND LAY-UP LAMINATES
USING MINIMUM PROPERTY VALUES
Grade
Numbers
Sremd Dlgit
Tensile Modulus,
Strength. psi
@
1
s
x lo3
I
XI@
2
10
11
12
x loo
1.1
xloa
x lo9
1.2
x 10'
x lo6
3
4
M1-220
FIrst DtgIt
Ultimate Tensif*
Fiber Reinforcement
Fiber reinforcements shall be in compliance with the
appendices listed below for each material rype:
(a)fihrgIass surfacing veil (mat), organic fiber surfacing veil (mat), carbon fiber surfacing veil [mar), and
fiberglass chopped strand mat - Appendix M-2, Anicle
A;
Ib) fiberglass spray-up roving and filament winding
mving - Appendix M-2, Article 8;
Ic) fibcrgtss woven mving fabric, fiberglass unidirectional fabric. and fiberglass nonwoven biaxial fabric
- Appendix M-2. Article C;
(4 fibeqhs milled fiber - Appendix M-2, Article
D.
ARTICLE A - REQUIREMENTS FOR
STANDARD CONTACT MOLDED
LAMINATES
1.3 x
lo6
chopped roving and woven mving construction as shown
in Table MIA-3.
0 Qass designates thc resin used and the level of
laminate flame retardancy obtained if required by the
UBRS. Class is written as the MSPI for the resin, followed in parentheses by the letters FS and the flame
sprcad. The flame spmd shall be determined according
to pam. MI-210.
(c) Grade shall designate the minimum mechanical
property levels of a laminate obtained at 73°F unless
orhenvise designated. Grade, spelled in capital letters,
shall be fotlowed by two Arabic numerals to designate
minimum levels of ultimate tensile strength and tensile
modulus, per Table h4 1A- 1. This shall be followed by
the minimum thickness, designated by Arabic numerals,
in decimal form to the nearest 0.01 in., or ALL.
NOTE: The Iwo Arabic grade numbers designate minimcchanical pmpcny levds f ultimrc tcmile streugh and tensik madulus from
Table MIA-I). Rtitr to p.
W I A-MO. Nominal mickntss s M bt
designated by an Arabif number in decimal form 10 rht n c a m 0.01
in.
M1A-1 00 LAMINATE DESCRIPTION
Laminate designation shall consist of the abbreviation
RTP. followed by the type, class, and grade as follows.
la) Type, in Roman numerals followed by the Manufactureis Specific Product Identification (MSPIJ for the
reinforcement, shdl designate the reinforcement structure comprised of specific plics ofglass fiber in specified
sequences. The MSPI forkach type of Rinforckent is
listed in the order each appeam, from the interior surface
10the exterior.
( I ) T y p I is a standard all-chopped srrand mat or
chopped roving construction as shown in Table M 1A-2.
Type 11 is a standard chopped strand mat or
M1 A-1 10 Examples of Laminate Classifications
(a) A laminate consisting of all mat construction
using MAT 80 reinforcement and RESISTALL 210
resin, without any required maximum flame spread rate
and having an ultimate tensile strength of 9000 psi and
a tensile mdulus of 1.30 x lo6 psi, is designated as:
-
RTP. TYPE 1 MSO. CUSS RESISTALL 210. GRADE 144 ALL
(b) A laminate consisting of alternating layers of mat.
MAT 80, and woven roving, R24. and RESISTALL 2 10
=sin, with a maximum required flame spread rating of
25 and having an ultimate tensile strength of 1 3 , m Psi
TABLE MIA-2
Thlokneas,
In.
INotsu~11,~211 1
2
3
4
5
6
7
V
M
M
M
M
M
V
V
M
M
M
M
M
M
M
M
M
M
M
M
V
V
M
M
M
M
M
W
M
M
M
M
V
V
M
M
M
M
M
M
M
M
V
V
M
M
M
M
M
M
M
M
M
M
M
M
STANDARD LAMINATE COMPOSlTtON TYPE I
Sequence of Plies
Draftlng
9
10
11
M
M
......
M
M
M
M
M
M
M
M
M
M
M
M
#
M
#
M
M
M
M
M
M
M
M
M
M
M
M
8
M
M
M
M
M
M
M
12
13
14
15
,,,
M
M
M
M
GENERAL NOTES:
(a} Thicknesses above 0.74 In. nomlnal can ba used by adding addltlonal piles of mat.
tb) Actual thleknes~snd elass content of each sequence of pliea shall ba established by each Fabrloator baaed on Hs design basls
laminate.
(el Cormslon barrier lplle8 1, 2, and 3) ahall gel and rrrtotherm kfwe structural plies are added,
(dl Stmctural lay-up may be Intempted at Ctewde long onough to exothwm In accordance with Fabrtcator's proaedure,
{el A welght equivalent layer or layers of chopped strand glasa or mat may be ueed In place of layars of 1.5 oz mat.
NOTES:
(11 Nominal thickness is calculated ss follows:
V 3 10 mil ilurfaee mat (veil) 0.010 In.lpty
M 0 1 H oxlsq ft mat 0.043 ln,lply
12) This information based on hlstorlclrl data and may not reflect all Laminates made todey, Laminates made today are often
thinner and have a hlghsr glass content than noted In the Table. The Tabk should b used for eetabliuhing mlnlmum g l e pIle8
~
per nomlnnl lamhate thickness. Ply thicknesses should be based on design basis larnlnetes.
-
-
10
17
18
Symbols
Z
V1
5
7
P
4
I
TABLE M1A-3
m
rn
m
STANDARD LAMINATE COMPOSITION fYPE I1
m
z
Nominal
Thickness,
Sequence of ma
In.
lNotas(1),12)1
1
a
3
4
1
6
7
8
9
lo
11
12
13
14
15
16
17
18
19
20
Draflng Symbols
V,ZM,3(AdR)M,3(1wR)#
V,2M,3(MR)M,3tMRI M,M
V,2#,3I MR)M,3{MR)M,IWRM
GENERAL NOTES:
(a) THcknesses above 0,76 In. nominal can be uaed following pattern established for 0.7B In, thlck laminate,
(bl Actual thlckness and glass content of each sequence of plies shall be estnMlshed by each Fabricator based on his design basis
laminate.
(e) Corrosion barrler (plles 1,2, and 3)shall gel and exotherm before structural plies ore added.
(ti} Structural lay-up may be interrupted long enough to ewolherm botwwn adjacent " M W p t h , If requlnd by fabricatlon procedure, location of exothrrm plies (plies 10 and 17) may be shifted within the lamlnale b d y . No plles may k
t omltted.
(0) A welght equivalent layer or layors of c h o p m strand glass or mat may be usad In place of layers of 1.5 oz mat,
NOTES:
(1) Nomlnel thlckness Is calculated as follows:
V = 10 mll o u r f m mat {vslll 0.02 0 In.lply
# = 1 'h ozlsq ft mat 0,043 tn.lply
R 3 24 ozlsq yd woven rovkng 0.033 in,lply
(2) This Information Is b s s d on hlatorlcal data end may not reflect all laminates made todey, Laminatoe meda today are often
thinner and have a higher glass content than noted In the Table. The Table should be used lor establishing mlnimum glass plies
per nominal laminate thickness. Ply thleknssse~~houldbe based on doslgn bosis laminates.
-
-
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
md a tensile modulus of 1.15
of 0.30 in.. is designated as:
X
lo6 psi at a thickness
RTP,TYPE U M80,R24. C U S S RESISFAUIIO (FS 25), GRADE
4.30
M i A-200 LAMINATE REQUIREMENTS
MIA-210 Lamlnate Construction
Laminate construction shall be in accordance with the
rabulated lay-up sequence for the specified type. These
lamhares shall be fabricaltd on a male mold.
(a)Type I laminate structure is detailed in Table
MIA-2.
(bl Type I1 laminate structure is detailed in Table
MIA-3.
MIA-220 Laminate Composit!on
bminates shall consist of a comsion resistant barrier
(comprised of an inner surface and interior layer) and a
stmctural layer.
MIA-221 Inner Surface - Corrosion Resistant
Barrier. The inner surface exposed to the contents shall
k a resin-rich layer in forced with a surfacing veil providing a thickness of 0.0 1 in. to 0.02 in., in accordance
with pan. M 1-220.
-
M I A-222 Interior Layer Corrosion Resistant
Barrier. The inncr surface layer, exposed to he contents, shall k followed with an interior layer. This layer
is composed of resin reinforced with noncontinuous
glass fiber strands (1 -0 in. to 2.0 in. long), applied in a
minimum of two plies totaling a minimum of 3 odsq ft.
These plies shall be layers of chopped strnnd mat and/
or chopped roving. Each ply of mat or pass of chopped
roving Wl be well rolled to thoroughly wet out *inforrement and remove entrapped air prior to the application of additional reinforcement. The combined
thickness of the inner surface and interior Iaytr shall not
be less than 0.10 in.
MIA-223 Structural Layer
(a) Application of Iht smctural Iayer shall not be
started until thc interior layer has been allowed to gel
and exorhem.
(bl The firstply of the structural layer of the laminate
shall be one or more plies of noncontinuous glass fibers
totaling Itis_ otlsq ft comprised of layen of chopped
strand mat andlor chopped roving.
(c) Continue lay-up in the sequence of plies stated for
the specified laminate type.
Id) All edges of reinforcemeni material shall be
lappd a minimum of I in. hpped edges of adjacent
Iayers shall be staggered.
Intemption of the fabrication prncess a allow for
an exotherm shall follow instructions noted on the appropriate table for the particularlaminate type. The final
ply of reinforcement before intemption for gel and exotherm shall be 1% d s q ft. The first ply of the ensuing
lamination MI also be 1't5 ozlsq ft. Both the final and
first plia shall be comprised of layers of chopped strand
mat and/or layers of chopped roving.
M l A-224 Outer Surface
{a) The outer surface of the finished laminate shall
be a separately applied paraliinated resin coat hat, when
cued, passes the acetone mt per ASTM C 582, para.
9.2.2. This outer surface coat shall either be applied over
the final mat ply of the suucmml layer or over an ad- ditional resin-rich layer when r e q u i d by (b) below.
(b) When rhe WBRS indicates the outer surface will
be subjected to spillage or a comsive environment, a
min-rich layer, in accordance with pan. M 1A-221,
shall be applied over the final mar ply of the structud
Iayer prior to the application of the paraffinatmi resin
coat in (a) above.
(c) The UBRS may include provisions 10 minimize
ulwaviolet degradation of the laminate. Methods include
use of ulrraviolet absorbers. screening agents, or resins
resistant to ulmviolet degradation, or incorpotation of
pigment of sufficient opacity in the pmffinated resin
coat. Since pigmentation makes laminate inspection difficult, the resin-rich layer shalI be applied only after the
laminate has been inspected by the Inspector.
(dl Where the Bnal lay-up is exposed to air, full surface cure shall be obtained by applying to the final layup a coat of parafinatad resin that, when cured, passes
the acetone test. Other techniques such as sprayed,
wrapped, or overlaid films are also acceptable methods
to attain surface cure, provided the surface resin under
the film passes the acetone rest.
M1A-300 REQUIREMENTS FOR PHYSICAL
AND MECHANICAL PROPERTIES
(a) The Fabricator shall prepare at least three design
basis laminates for a c h combination of resin (class) and
glass (type), identified by their respective MSPI (see
para. M 1A- 1001, to determine thickness and glass content. Straight line interpolation shall be used to determine values of thichesses and glass content not tested
dhetly . In addition, the Fabricator shall choose one d
the following two options to establish his design tensile
smngth and design tensile modulus.
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
TABLE MIA-4
Uominal
fhtckness,
In.
TYPe
All
0.22
0.28
0.37 and above
I
I1
II
II
Uldmate Tensile
Swength. psi
[Note (111
9.0
12.0
13.5
15.0
x
x
MINIMUM VALUES OF LAMINATES
Tensib Modulus, psi
lo3
lo3
x 103
x 10'
[Note (111
1.0
1.3
1.4
1.5
x
lo8
x lo6
x lo6
x 10'
Ultimate Flexural
Smngth, psl
[Note (211
16.0 x
nenural ~odulus,
lo9
19.0 x loa
20.0 x loa
22.0 x lo3
psi
[Note ta)l
0.7 x loa
0.8 x 10'
0.0 x lo6
1.0 x lo4
GENERAL NOTE:
The tabulated values remaln unchanged up to 180°F. Above that temperature, measured properlies may decrease.
NOTES
11) ASTM O 638 at 73OF.
(2) ASTM D 790 at 73OF.
( I ) The Fabricator shall specify the minimum values in Table M 1 A 4 and use the correspondinggrade as
found in Table MIA-I. This mcthd shdl not be used
where laminates are fabricated for use above 180°F.
(2) The Fabricator shall obtain the certified tensire
strength and tensile modulus of his design basis laminates in accordance with para. M 1A-400. Testing to establish the propertics of the design basis laminate may
be performed by thc Fabricator or by an independent test
laboraiory. Results shall be certified by the individual
who conducted or supervised the testing.
When the corrosion barrier is included in the design
as a contributor to the structural strength of the laminate, the design basis Iaminates shall include the inner
surface, interior layer. and structuml layer, but not the
outer surface. When the c o r d o n bamcr is excluded
from the design as a contributor to the structural strength
of the Iarninate per p m . 6-930(d)(31Id), the design bsis laminates shall include only the structural layer. Design basis laminates shall be at least 12 in. x 12 in. and
shall incIude the foIloa-ingfor each resin and glass combination:
(a)Type I - 0.18 in, nominal thickness
Ib) Type I - 0.48 in. nominal thickness
Ic) Type I - 0.74 in. nominal thickness
(d) T y p II - 0.22 in. nominal thickness
(e) Type Il - 0.49 in. nominal rhickness
If) Type I1 - 0.76 in. nominal thickness
Pmpenies of each type shall tK established on Rat laminates prepaid under shop conditions. For Type LI laminates the woven roving is laid-up in square array with
warp rovings parallel layer to layer, and test specimens
are cut parallel to the warp rovings.
Ibl Grade identiffration numbers will be assigned by
the Fabricator to the design basis laminates per para.
M1A- 100 based on mechanical propenies measured at
73°F. The assignment shall be based on the following
mles.
( I ] The Fabricator may select any laminate grade
listed in Table MIA-1 which is up to. bur not gmaer
than, the values established by hi design basis laminate
and not less than those values shown in Table MI A 4 .
(2) For lamhare sequences without certified properties, the identification number assigned shall not be
greater than the lesser cenified property of the thicker
and thinner sequences between which ir falls. For design purposes, pmpenies at 73°F are acceptable up to
180°F.Where laminates are fabricated for use at design
temperatures above 180°F, cei-iification of tensile
smgth and tensile modulus per para. M 1A-(a)
shall
be supplied at or above the specifred temperature.
(c) Thc thickness and glass content of a production
laminate shdl be established by the designer b a e d on
the data obtained from the Fabricator's design basis
laminates. Six thickness and glass content per unit area
readings shall be taken on each design basis laminate.
They shalt be taken at 1 in. to 2 in. from each comer,
except for two readings taken from the middle of the
laminate. The highest thickness and glass content per
unit area reading taken (of the six) must be no more than
1 15 % of rhe lowest reading taken. The six readings shall
be averaged to give the design basis laminate thicknas
and glass content for each Iarninate tested. The average
thickness value shall be from 85% to 115% of the nominal thickness listed in Tables MIA-2and MIA-3.
NOlE
_,a
Glass content pcr unit arm m a w wight per unit area and is
pcmnt rduc.
(d) The laminate compositions and minimum propenies for Type I production laminates are given in Tables MIA-2 and MIA-4.
(el The laminate compositions and minimum prop-
REINFORCED THERMOSET PLASTIC
COAROSlON RESISTANT EQUIPMENT
erties for Type Il pmduction laminates are given in Tables MIA-3 and M l A 4 .
NOTE: The h m h t t p r a m found in TabIt MIA-4 nrr ronscrvative and hisrorically pmvcn. Thty itprescar compilation of data on
t k mmt availabk laminating matcrialr.
Part 6 of this Standard, para. 6-930,requires tests to
be conducted on a sample of laminate ~emovedfrom
each vessel, to verify hat mechanical properties of tht
as-constructed laminate meet or exceed those properties
as used in the design.
Based on the relative dificulty of suictly controlling
the laminating process during the manufacture of a cornplcx vessel as c o m to~the sample preparation pmctss, the test laminate may have higher strength
pmperties than the production laminate, Fabrica~orsare
urged to establish conservative or historically proven
mechanical property values for design purposes.
Should the mechanical propenies of an as-constructed
laminate fail to meet orexceed those used in the design,
the equipment must then bc dedared by the Jnspec~orto
be nor in compliance wilh this Standard.
M IA-400 TEST METHODS
(a) Tensile srength and tensile modulus of elasticity
shall be determined by ASTM D 638. Specimens shall
be in accordance with Type III, Fig. 1 of ASTM D 638
except that actual laminate thickness shaI1 be used.
(b) Glass contcnt, weight perrent. shall be determined in accordance with ASTM D 2584.
(c) When required, the residual undistuhed glass fiber plies from ASTM D 2584 shall be sepmtcd carefully and counted andlor weighed to confirm standard
lay-up sequence.
(d) Thickness shdl be measured with a ball foot rnicmmeter or caliper. When the configuration of the part
will nor allow the use of these instruments. a digital
magnetic intensity instrument (ASTMD 4 166) or an ultrasonic &ickness gauge found to l
x accurare when
measuring vessel cutouts shall be usad.
(e) When required, thermal conductivity shall be
measured in accordance with ASTM C 177.
fl When required, thermal expansion shdl be measared in accordance with ASTM D 6%.
-
ASME RTP- 1 1995 EDITION
ARTICLE B - REQUIREMENTS FOR
LAMINATES DEVELOPED USlNG THE
LAMINATION ANALYSIS MET HOD
M l B-100 LAMINATE DESCRIPTION
(a) Fabricators shall describe their laminates according ro type, class, and grade. All Article B laminates are
designated Type X to diffemntirlte them from the stm-
dard laminates dcscribd in Article A.
(bl Type followed by Roman nurneral X is in turn
followed by the identification of the reinforcements in
the sequence they appear in the laminate, from the inrenor surface to the exterior.
Reinforcements shall be identified consistently by the
Fabricator in both the Laminate Description and the
Manufacturer's Specific P d u c t Identification (MSPIIThe accompanying MSPI shall identify each reinforcement making up the laminate sequence. For continuous
fiber reinforcements, the thickness of each reinforcement layer and the angle from the principal loading axis
(which in the case of a cylinder is the cylinder axis) shall
be Sited. Repeating constructions shall be identified in
brackets followed by a subscript indicating the number
of repeating constructions.
kc) Class designates the resin used and the level of
laminate flame d a n c y required. Class is written as
the MSPI for the resin. followed in parentheses by the
letrem FS and the maximum allowable flame spread. The
flame spread shall be determined according to para. M1210.
(dl Grade shall designate the tensile modulus, hoop
and axial, in psi. as determined by the taminat ion Analysis Method (Appendix M-5).
M1B-200 LAMINATE REQUIREMENTS
M I 8-210 Laminate Construction
Laminate construction shall be the same as described
in para. M1B-l00(a).
M1B-220 Laminate Composition
Laminatesshall consist of a corrosion resistant barrier
(comprised of an inner surface and interior layer) and a
structural layer.
M1A-500 RECORDS
M I 6-221 Inner Surface - Corrosion Resistant
Barrier. See para. M 1A-22 1 .
The resulrs of all required tests shall be corded and
shdl be available for review by the Inspector-
M l B-222 Interior Layer
Barrier. See para. MIA-222.
- Corrosion Resistant
.
ASME RTP-1-1995 EDITION
M1B-223 Structural Layer
(a) The structural Iaycr is k r i b e d in p.
M 13100.
(b) Application of the stmctural layer shall not be
started until the interior layer has been allowed to gel
and exarherm.
Ic) The first layer of the structural portion of the laminate shall be one or more plies of chopped srrand mat
totaling 1 'h ozlsq ft or equivalent chopped roving saturated with resin. Thii layer shall be well rolled to thoroughly wet out reinforcement and remove entra~wdair
and shall not be allowed to gel prior to stan df'subsequent layers.
Id) The balance of the suuctural layer shall then be
applied in stricr duplication of the laminate described in
para. MlB-100.
M IB-224Outer Surface. See para. MI A-224.
M l B-300 REQUiFIEMENTS FOR PHYSICAL
AND MECHANICAL PROPERTIES
and specific
gravity are m c a s u ~ don a fully cured '/e in. thick neat
=in casting. Tensile modulus properties at or above the
design temperature shall be used. Specific p i t y values at 75'F may be used for all design temperarures.
(bl Standardized tensile modulus and specificgravi~y
for E glass shall be used for the Lamination Analysis
Method (Appendix hi-5).
(c) Laminate propenits are calcuIated using the
Lamination AnaIysis Method contained in Appendix
(a)
The =sin
matrix tensile modulus
M-5.
REINFORCED THERMOSET Pusnc
CORROSlOM FIESISTANT EQUIPMENT
forcement per pan. MlB-100. The objgetive is to
uniquely define each laminate. Also, for each laminare,
m o d ~ s u l t of
s m i n g done in paras. MlB400(a) and
@) a d make them available for review by h e Inspector.
ARTICLE C - PERMISSIBLE TOLERANCES
FOR LAMINATE THICKNESS VARIATION
MIOIOO
lNTRODUCTION
There are two types of laminate thickness tests. The
first, average spot thickness, is used to measure a small
area or a small component [st& Part 6, para. 6920(f)Q)J.The second, average thickness of a major
part, is used to measure a large area. such as a shell or
head, where several average- spot thicknesses can be
taken [see para. 6-920(f)(2)].
M I C-110 Tolerance for Average Spot
Thickness
The thinnest value (of six) must be equal to or grearer
than 90%of the &sign thickness of the laminate. The
thickest value (of six) rnm be no more than 12042 of
the thinnest value. The average of six thickness valucs
must be no less than 95% nor more than 125% of the
design thicknes of the laminate. See para. MlC-130 for
exceptions.
MI C-120 Tolerance for Average Thickness of a
Major Part
MIB-400 TEST METHODS
(a) Glass content, weight percent, shall be determined in accordance with ASTM D 2584.
IbJ Matrix tensile modulus shaIl be determined in accordance with ASTM D 638.
(c) Matrix spscific gravity shall bc determined in accordance with ASTM D 792.
(d) Thickness of individual plies shall k determined
with a microscope or other insrrument having an accuracy of 0.001 in.
M1E500 RECORDS
For each laminate in pam. MlB-223,record wind angles, numbcr of wind cycles. and supplemental =in-
The arerage 111ichrrsof a ~~tajor
pnri is the average
of four average spot thickness values. The average
thickness of a major part shall be not less than 95% nor
more than 120%ofthe design thickness of the laminate.
Sce para. M I C- 130 for exceptions.
Fabricato~may add additional material to achieve the
minimum thickness spceified. All such additions sllall
be in accordance with the repeating sequence of strucrural layers as described in para. MIA-100 or para.
M IB-100. The repeating construction of reinforced
laminate mny result in an over-thickness, which i s permissibIc. Refer to para. MI3-100(b) for ~quirements
and proeedu~s.
1
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMEMT
MANDATORY APPENDIX M-2
RElNFORCEMENT MATERIALS RECEMNG PROCEDURES
M2-100
INTRODUCTION
All inspections and tests specified in Appendix M-2
are to k performed by Fabricuor personnel or an independent testing laboratory.
ARTICLE A - FIBERGLASS SURFACING
VElL IMAT), ORGANIC FIBER SURFACING
VElL IMAT), CARBON FIBER VElL IMAT),
AND FIBERGLASS CHOPPED STRAND
MAT
(bl
M2A-100 INTRODUCTION
This Articlc specifim the minimum inspections and
tests that shall be pcriormed on the rolb of fiberglass
surfacing veil. organic fiber surfacing veil. and fiberglass chopped strand mat that shall be used to fabricate
equipment to this Standard.
M2A-200 ACCEPTANCE INSPECTlON
(a)
(a)
(a) Acceptance inspection shall include inspection of
all rolls for proper packaging and identification, and
contamination. This acceprance inspection is to te conducted on the unopened roll. Acceptance requirements
and limits are as defined in pan. M2A4 10. Acceptance
inspection shall include inspection of selected rolls lor
measurement of unit weight per ANSIlASQC 21-4 criteria. Inspection for manufacturing imperfections shall
be conducred during use of mlled goods. Acceptance
requirements and limits are as defined in paras. M2A420 and M2A430.
(bl The form shown in Table M2A- 1 of his Anicle,
or a similar form that contains the pm~~isions
to record
the results of thesc rrquirsd i n s ~ t i o n sand certifiestions, if applicable, shall be used by the Fabricator and
shall l
x retained in the inspection records. A separate
form shall be used for each mat manufacturer, mat nomenclature, mat treatment, and mat unit weight.
(c) In lieu of performing the above manufacturing inspections, measurements, and documentation. the Fab-
ricaror shall provide the User or User's agent with a
Ceniticate of ~ o r n ~ l i a n cfmm
e the material manufacturer, This Certificate shall assuE that materials were
manufactured, inspected, and tested per the mattrid
supplier's specifications.
M2A-300 EQUIPMENT AND MEASURING
TOOLS REQUIRED
M2A-310 Inspection Table and Ughts
An inspection table and adequate overhead lighting
that are suitable for the inspection and testing of the mat
a= required. The equipment used must not intduce
conramination to the mat during inspection and testing.
M2A-320 Linear Measuring Tools
A standard Iinear measuring tool (longer than the
width of the rolls) that measures the mll widths with
minimum accuracy of f '/p in. is mquired. A 12 in. f %?
in. x 12 in. f '/32 in. template i s required.
M2A-330 Laboratory Balance
A Iaboratory balance that measures to 0.1 g is required.
M2A-400 PROCEDURES AND ACCEPTANCE
LIMITS
M2A-410 Roll Identification and Package
Inspection
(a) The mat shall b packaged as shipped from the
mat manufacturer's factory. If repackaging is required.
h e Fabricator shall assure that a material Certificate of
Complimce uaccable to the original mattrial is pmvided. The original labels can k modified in regards to
number and width of rolls only. All orher docurnenlation shall remain unchanged. Verify and enter on the
La)
REINFORCED THERMOSET PLASTlC
CORROSION RESISTANT EQUIPMENT
TABLE M2A-1
VEIL AND MAT REINFORCEMENT LOG SHEET
Fabricator's name
Mar manufacturer
Address
Mat mmenclature
Mat treatment lif given) [Note (1 11
QC tile no.:
-
Met weight [Note 1211
1
2
3
4
5
6
Roll
Reinforcement
Production
Lot No.
Pmekaging
Width
Weight
[Mote (1 11
Inspection
No.
Date
(if given)
BY
Date
of sq ft
Sample
7
Pro~ertv
Inripean
(cob. 5 and 6)
By
Date
8
Visual
Inspection
BY
Comments an visual and packaging inspection {indicate which roll):
GENERAL NOTE:
This form may be reproduced and used without written permisston from ASME if used for purposes other than repubtication.
NOTES
4 f 1 Lot. batch. product code. or other label identification.
12) Manufacturer'slabel weight.
Date
REINFORCW THERMOSET PLASTIC
CORROSfOPI RESISTANT EQUIPMENT
MANDATORY APPENDIX M-2
REINFORCEMENT MATERIALS RECEIVING PROCEDURES
M2-100
INTRODUCTION
i n s ~ t i o nand
s rens 'pecified in
M-2
dependent testing khrarary.
ARTICLE A - FIBERGLASS SURFACING
VEIL (MAT), ORGANIC FIBER SURFACING
VElL (MAT). CARBON FIBER VElL [MAT],
AND FIBERGLASS CHOPPED STRAND
MAT
M2A-100 INTRODUCTION
This Anicle specifies the minimum inspections and
tests that are to be performed on the rolls of fiberglass
slrrfacing veil, organic fiber surfacing veil, and fikrglass chopped strand mat thar are ro be used to fabricate
equipment to this Standard.
MZA-200 ACCEPTANCE INSPECTION
(a) Acceptance inspection shall include inspection of
alI rolIs for proper packaging and identification. and
contamination. This accepmce inspection is to be conducted an the unopcned 1-011. Acceptance requi~ments
and limits are as &fined in para. M2A410. Acceptance
inspection shall include inspection of select4 d l s for
measurement af unit weight per ANSUASQC 21.4 critcria. Inspection for manufacturing imperfections shall
be conducted during use of rolled goods. Acctpmce
requirements and limits are as defined in paras. M2A420 and M2A-430.
@) The form shown in Table M2A-1 of rhi Article,
or a similar form that contains thc provisions to record
the resulrs of these required inspections, shall h used
by the Fabricator and shall be remined in the inspection
records. A separate form shall be used for each mat
manufacturer, mat nomendamre, mat treatment, and
mat unit weight.
(c) In Iieu of performing the above inspections, measurrments, and documentation, the Fabricator shall pro-
vide the User or User's agent with a Cenificate of
Compliance from tlte material manufacturer. This Ccrcificaeshall a s w ~
ha materials w e e -ufactu&,
hcations.
M2A-300 EQUIPMENT AND MEASURING
TOOLS REQUIRED
M2A-310 Inspection Table and Lights
An inspection table and adequate overhead lighting
that are suitable for the inspection and testing of the mat
are required. The equipment used must not introduce
contamination to the ma1 during inspection and testing.
M2A-320 Linear Measuring Tools
A standard linear measuring tool (longer than the
width of the rolls) that measures the roll widths with
miaimurn accumcy of 4% in. is required. A 12 in. f 'hz
in- x 12 in. f 'I32 in. template is required.
M2A-330 Laboratory Balance
A lahrataq balance that measures to 0.1 g is required.
MZA-400 PROCEDURES AND ACCEPTANCE
LIMITS
M2A-410 Roll ldentificatlon and Package
Inspection
(a] The mat shall be packaged as shipped from the
mat manufacturef s factory. If repackaging is r e q u i d ,
the Fabricator shall assure that a marerial Cenificate of
Compliance m d i e to the original material is provided. The origid IabeIs can be modified in regards to
number and width of rolls only. A11 other documentation shall remain unchanged. Verify and enter on fie
REINFORCE0 THERMOSET PUSTtC
CORROSION RESISTANT EQUIPMENT
ASME RTP-1-1995 EDITION
TABLE M2A-1
VEIL AND MAT REiNFORCEMENT LOG SHEET
Fabricafor's name
Mat manufacturer
Address
Mat nomenclature
Mat treatment (if given) [Mote (111
QC file n
Roll
No.
Reinforcement
Production
Date
(if given)
Lot No.
[Note Ill1
o
.
Pecksging
Inspection
By
Date
:
Wdth
Mat weight [Note 1211
Weight
of sq ft
Sample
Visual
Inspection
(cobs. 5 and 6)
By
Date
Inspection
BY
Comments on visual and packaging inspection (indicate which roll):
GENERAL NOTE:
This form may be reproduced and usad without written permission from ASME i f used for purposes other than republication.
NOTES:
(1 I Lot, batch, product code, or other labet identification.
(2) Mandacturer'~label weight.
Dare
RElNFORCED WERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
.inspection record that the mat rolls as identifid by the
mat manufacmnr have rhe same nomtaclature as h e
mat specifiedto produce the laminate by Appendix M- I ,
Articles A and B, and examine &e packaging of the mat
for damage that renders the mat unusable. Indicate acceptable rolls by recording the date and name of the person performing the examination on Table M2A-1,
column 4.
&) For paelaged mats that are found ra be acceptable
for further insption and tests, enter the reinfo~ement
production date and lot number on Table M2A-1, columns 2 and 3,
M2A-420 Visual Inspection of Mat
la) As the mat i s used during fabrication, it shall be
visually inspecled for impcrfcctions and contamination.
Date and name of person performing visual inspecrion
sMI be recorded on Tablc M2A- 1, column 8.
Ib) The mat shall be uniform in color, texture, and
appearance. lmperiecrions andlor conraminants shall be
removed so as not to damage the mat or by making two
parallel cuts across the width of the mat and discarding
the rectangular section of the mat containing the defects.
Contaminants do not include white or light gray binder
spots.
NOTE Exampks of imperfections are froits.cuts. thin spots. or dclaminations. i-e.. scparaling into h ~ e r sduring unrolling. ExampIcs
of conurninants arc din. oil. g-.
and ioreign objccts.
(el Rolls having any of the following defects shall
not be ustd in laminates made to this Standard:
11) wet spots
(2) water contamination
131 bar marks
(4) lenglhwise wrinkles exceeding 5 ft in length
M2A-430 Weight per Square Foot of Mat
From the leading edge of each roll of mat that will be
tesred as p r para. M2A-200.cut a 1 sq ft ( I 0 sq fi for
surfacing veil) sample using the template sperified in
para. M2A-320. If the roll is less than I2 in. wide, use
the full width of the roll. but adjust the length of the
sample (use the linear measuring tool specified in para.
M2A-320). Any property measurement shall be conducted by unrolling only the quantiry of material required to conduct the test. Using the laboratory balance
required by pan- M2A-330. weigh the sample of mat
to the nearest 0.1 g. Convert the grams to ounces. if
needed, by rnuhipl~inggmms by 0r0352. If the sample
fmm a roll falls outside the mat manufiicturer's specified
weight range, the mI1 of mat shall be rejected. Enter the
of weighed samples for acceptable and unacceptable rolls on the inspeetion form under column 6.
Note the rejected mlb wirh the word "rejected" next to
the recorded weight in column 6values
ARTICLE B - FIBERGLASS SPRAY-UP
ROVING AND FILAMENT WINDING
ROVING
M2B-100 INTRODUCTION
This Article specifics the minimum inspections and
rests that a= to k performed on fiberglass spray-up roving and filament winding roving chat are to be used to
fabricare equipment to this Standard.
MZB-200 ACCEPTANCE INSPECTIONS
(a) Acceptance inspections shall include inspection
of the roving balls for proper packaging, identifica~ion.
and contamination. This acceptance inspection is to be
conducted on the unopened roll. Acceptance q u i r t ments and limits are as defined in para. M2B410. Acceptance inspection shall include inspection of selected
rolls for measurement of roving yield per ANWASQC
Z 1.4 criteria. I m r i o n for manufachlring imperfections shall k conducted during use of roving balls. Acceptance quirements and h i t s are as defined in paras.
MZB420 and M2B430.
(b) Tht form shown in Table M2B-1 of this Article,
or a similar form that contains the provisions to record
the results of inspections, shall be used by the Fabricator and shall be retained in h e inspection records. A
separate form shall be used for each mving manufacrurer, mving nomcnclarure, and roving yield.
Ic) In lieu of performing the above inspections, measurements, and dccumentation. the Fabricator shall provide the User or User's agent with a Certificate of
Compliance from the material manufacturer. This Certificate shdl assure that materials were manufachired.
inspected, and tested per the material supplier's specifications.
M2B-300 EQUIPMENT AND MEASURING
TOOLS
M2B-310 Wrap Reel
A device may be used which provides a minimum of
a 6 yard sample measumd and cut under sufficient tension to keep h e strand taut. Equipment such ns standard
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
ASME RTP-1-1995 EDITION
TABLE M2B-1 ROVING REINFORCEMENT LOG SHEET
--
Fabricator's name
Raving manufacturer
Address
M n g nomenclature
Roving yield
OC file m-:
1
2
3
4
5
Ball
Reinforcement
Production
Lot No.
[Note (1 11
Packaging
Yield
No.
Inspection
Date
(if given)
By
Date
6
7
mr*I
Inspaction
Ieolumn 5)
By
Date
Visual
Inspection
By
Comments on visual and packaging inspection (indicate which roll):
GENERAL NOTE:
This form may be reproduced and used without wrltten permission from ASME if used for purposes other than republication.
NOTE:
(1) Lot, bat&, product code, w othar label Identification.
Date
REINFORCED THERMOSET PLASriC
CORROSION RfSlSfANT EQUIPMENT
36 in. or 54 in. (1 ymd or 1.5 yard) yam reeI with adjustable uansvefse, four skein capacity is suggested.
M2B-320 Laboratory Balance
A labratory balance that measums to 0.1 g is required.
M2B-400 PROCEDURES AND ACCEPTANCE
LIMlTS
M28-410 Roving Identification and Package
Inspection
(a) The roving shall be packaged as shipped fmrn the
manufacturer's factory. The roving shall not be repackaged in the distribution of thc materid afrer the manufacntrer has shipped the roving. Verify that the roving
balls as identified by the manufacturer have the same
nomenclature as the mving required by Appendix M-1
and examine the packaging of the roving for damage
that renders the mving unusable. Indicate acceptable
roving by recording on Table M2B-1. column 4, the date
and name of the person performing the examinarion.
@) For packaged rovings that are found to be acceptable for further inspection and tests, enter the reinforcement production date and lot number for each ball
on Table M2B-I. columns 2 and 3.
M2B-420 Visual Inspection of Roving
(a) The mving ball shall be visually inspected forirnperfections and contamination prior to use by the Fabricator. Record the date and the inspactor's name on
Table M2B-1,column 7. If any roving ball is rtjec~ed,
record the reason under the comments section in Table
M2B- 1.
0 Roving balls having any of the following defects
shaH not be used for laminates made to this Standard:
(1) any package rhat exhibits foreign manes such
as din, oil. grease, wasie glass fiber, or beads of glass
such thar it would detract from the performance or appearance of the finished product;
0) balls that have been contaminated by water.
M20-430 Measurement of Roving Yield
From one roving ball per shipment, obtain a rninimum of a 6 yard sample (length A) of roving as required
by para. M2B-3 10. Roving sball be pulled fmm the same
side ofh e package as used in the Fabricator's process.
If the roving is pulled from the o u ~ i d eof the package,
suficient material shall be removed and discarded so
ASME RTP-1-1995 EDITION
that the sample will
k lalrcn from undisnubed material.
Remove the sample from the wrap reel. Double the Sample several times and tie with a single knot. Using the
balance requid by para. M2B-320,weigh the sample
to the nearest 0-1 g. Convert grams to ounces by multiplying grams by 0.0352. Two specimens from each
package shall be measured and the average computed.
Record as Weight A.
Calculate the yield, yardsob, using the following formula:
yield, yardsfib =
I6 oznb x leogtb A =
96
weight A (0x1
wei* A (02)
Enter h e yield of acceptable and unacceptable MIS
of roving on Table M2B-1, column 5. lf the yield of the
ball of roving is outside the manufacturer's specification, thc remaining balls in the shipment are to be inspeckd per ANSYASQC 21-4 criteria, following the
p d u m specified in para. M2B430.Balls whose yield
is outside the rnanufacrunzr's s-cation
shall not be
used for laminates made lo this Standard. Note the rejected roving balls with the word "rejected" next to the
yield in column 5. Atso, record the da~cand name of
the person performing the yield measumnent in column
6.
ARTICLE C - FIBERGLASS WOVEN
ROVING FABRIC, FIBERGLASS
UNIDIRECTiORIAL FABRIC, AND
FIBERGLASS NONWOVEN BlAXlAL
FABRIC
This Article specifies the minimum inspections and
are to be performed on the mlls of fiberglass
woven roving fabric, fiberglass u n i d i i i o d fabric, and
fikrgIass nonwoven biaxial fabric that are to k used to
fabricate equipment to this Standard.
tests that
M2C-200 ACCEPTANCE INSPECTIONS
(a) Acceptance inspections shall include inspection
of all fabric rolls for proper packaging and identification. and contamination. T h i s acceptance inspecuon is
to be conducted on the unopened roll. Acceptance requiremears and limits are as defined in para. M2C-410.
Acceptance inspection shall include inspection of selected rolls for measurement of unit weight and verification of construction of fabric per ANSIIASQC Z 1.4
REINFORCED THERMOSET PLASTIC
CORROSION RESISTAM EQUIPMENT
criteria. Inspection for manufacturing imperfecEions
shall be conducted during use of rolled goods. Acceptance requirements and Iimics are as defined in p a .
M2C420 through M2C450.
(b) The form shown in Tabk M2C-1 of this Article,
or a similar form that contains the provisions to record
the mults of these mquired inspections, shall be used
by the Fabricator and shatl be retain4 in the inspection
mods. A separate form shall be used for each fabric
manuiactumr, fabric nomenclature, fabric unit weight
(ozlsq yard), and fabric construction.
(c) In lieu of pforming the a b v e inspections, mas u m n t s , and documentation, the Fabricator shall provide the User or User's agent with n Certificate of
Compliance from the material manufacturer. This Certificate shall assure that materials were manufactu~d,
inspected, and tested per the material supplier's specifications.
M2C-300 EQUIPMENT AND MEASURING
TOOLS REQUIRED
M2C-310 lnspection Table and tights
An inspection table and adequate overhead lighting
that are suitable for the inspection and testing of the fabric are required. The equipment usad shall not introduce
contamination to the fabric during inspction and testing.
M2C-320 Linear Measuring, Marking, and
Cutting Tools
(a) A standard linear measuring toot (longer than
width of mll) dat measures the roll widths with minimum accuracy of &'/s in. i s requid.
(b) A 3 in. f %: in. square template is required.
Ic) A fine point felt tip pen md scissors are required.
aged in the distribution of the material after the manufacturer has shipped the fabric. Verify hat the fabric
rolls as identified by the manufacturer have the same
nomenclature as the fabric required by Appendix M-I
and examine the packaging of the fabric for damage that
renders the fabric unusable. Indicate acccptabIc rolls by
recording the date and name of the peaon performing
the examination on Table M2C-1, column 4.
@) Forpackaged rolls that are found to be acceptable
for fuEtber iaspection and tests, enter the fabric production date and lot number on Table M2C- I , columns 2
and 3.
M2C420 Visual Inspection of Fabric
la) As fabric is used, it shall be visually inspected
for imperfections and contaminations by the Fabricator.
Record date and name of inspector on Table WC-1.
column 9. If a roll is rejected, record the reason under
the comments section in Table M2C-1.
Fabric shall be uniform in color. texture, and appcarance. The foilowing imperfections and/or contaminations shall be removed fmm fiberglass woven mving
and fiberglass nonwoven biaxial fabric by making two
parallel cuts across the width of the fabric and d i a r d ing the rectangular sections of fabric containing the following defects:
(1) dirt spots (%s in. to in. in diameter) in txccss
of one per 10 lineal feet (dirt spots are defined as a11
foreign matter, din, grease spots, etc.);
121 missing ends for more than 2 consecutive feet
in length;
(31 firs clumps or loops greaterthan 1 in. in height
frnrn the surface.
(cl FibergIass woven and fiberglass nonwoven biaxial fabric having any of the following defects shall not
be used for laminates made to this Standard:
(1) dirt spots in exof % in. in diameter (din
spots are defined as all fo~ignmatter, din. grease spots,
etc.);
M2C-330 Laboratory Balance
A labormory balance that measures to 0.1 g is required.
G'l more than 11 missing ends. either individual
picks or any combination of individual and multiple (2.
3, 4, or 5 ) ends in any consecutive 100 lineal feer;
(3) fuzz clumps or Imps that prevent the proper
lay-dawn of the fabric and which C a M O t be easily removed;
M2C.400 PROCEDURES AND ACCEPTANCE
LIMITS
M2C-410 Roll Identification and Package
Inspection
la) The fabric shdl be packaged as shipped from h e
manufactutrr's factory. The fabric shall not be repack-
(41 rolls that have been contaminated by water.
(dl Fiberglass unidi~ctionalfabric shdI be uniform
in color, texrure, and appearance. The following i m p fections andlor contaminations shall k removed fmm
the fabric by making two parallel curs across rhe width
of the fabric and discarding the mctangdar sections of
fabric containing the following defects:
REINFORCED THERMOSET PLASTIC
CORROSION RESLSTANT EOUIPMENT
-
ASME RTP- 1 1995 EDITION
TABLE MPC-I
FABRIC REINFORCEMENT LOG SHEET
-.
Fabricator's name
Fabric mamtfacturer
Address
Fabric nomenclature
Fabric weight
QC file no.: -
1
2
3
Roll
Reinforcement
No.
Production
Lot No.
INote(1)I
4
Packaging
Inspection
5
Width
6
Weight
7
8
Conmction
Property
9
Visual
Inspaction
Inspection
[cols. 5.6. and 7 )
Date
(if given)
Fabric c o n d o n
BY
Date
By
Date
By
Comments on visual and packaging inspection (indicate which roll):
GENERAL MOTE:
TM9 form may be reproduced and used without written permission from ASME if used for purposes other than republicatian.
NOTE
(11 Lot, batch, product code. or other label identifieation.
Date
REINFORCED THERMOSET PLASUC
-
ASME RTP- 1 1B9S EDITION
( I ) dirt spots
in. to % in. in diameter) in excess
of one per 10 l i d feet (dirt spots are defined as all
foreign matter, dirt, grease spots. etc.);
(2) missing ends in any dimtian Iess than one per
l i d foot:
(3) a m s of the fabric less than 6 in. X 6 in. where
wings are disoriented w loo* Icss thmtn 1 in. in height
fmm tbe surface, The number of these area shall not
exceed two per 5 Iineal yards of fabric. If so, the roll
shaII not be used for laminates made to this Standard;
(4) weft mils exceeding 1 in. or Iess rhm Va in. in
length;
(5) bias exceeding f 10 deg. from 0 deg.1 180 deg.
in a warp [machine d i t i m ) product or from 90 deg.1
270 deg. in a weft (All dimrion) praduct.
{e) Fiberglass unidirectional fabric mlls having any
of the foIIowing defects shall not be used for Iaminates
made to this Standard:
( I ) dirt spots in excess of % in. in diameter (dirt
spots are defined as all foreign matter, dirt. grease spots.
etc.);
121 missing ends in any direction more than one
per lineal foot of fabric;
(3) areas of the fabric greater than 6 in. x 6 in.
where rovings are disoriented or Iooped less than I in.
in height from the surface;
(4) areas of the fabric where mvings are disoriented or looped greater than 1 in. in height from the
surface;
(51 rolls that have k e n contnminated by water or
CORROSION RESISTANT EQUIPMENT
Due w the mclhads of ~ k t w S n fabrics,
g
there are diffmnt ways of docribirrg widths of fabrics.
NO=
M2C-440 Weight per Square Yard of Fabric
Unroll the fabric on the inspection table and lay flat.
Pull one fill pick from tbe sample or mark a lime across
the width of the fabric. Measure fmrn the pulled pick or
line using a 36 in. rule meering the accuracy requiements of para. M2C-320-Pull another fill pick or mark
offthe 36 in. sample for cuniag. Cut thc 36 in. long
sample across the width of the fabric using scissors.
Measure the, width of the fabric according to para. M2C430. Weigh the sample to the nearest 0.1 g. Convert
griuns to ounces by multiplying grams by 0.0352. Calculate h e weight per square yard in ounces per square
yard using the following formula:
weight. oz
%yare yard
=r
36 in.
quare yard
sample weight. or
sample width, in.
Rolls whose weight per square yard are outside the
manufacturer's spcicication shall nor be used for laminates ma& to this Smdard. Enter the weight per square
yard of acceptable and unacceptable mlls on the inspection report shown in Table M2C-1. Note the rejected
rolls with the word "rejected" next to the weight in
column 6.
other substances.
M2C-450 Construction
M2C-430 Width Measure of Fabric
With the linear measuring tool given in para. k12C320, measure the width of the fabric at least 1 yard from
the beginning (leading) edge of the roll and at ~ w o
additional positions at least 6 in. apart. Follow the manufacrurer's definilion for the width of the particular
fabric (see note below). Measure to the nearest VB in.
Average the three measurements and enter the measured
width of acceptable and unacceptable rolls on the inspection form shown in Table M2C-1. Note the rejected
rolls wirh the word "rcjccted" next to the width in column 5. Rolls with variations greater than f 5 in. for
1-011 widths of 12% in. or less and f'k in. for roll widths
greater than 12% in. shall not be used in laminates made
to his Standard.
Record the date and name of thc person performing
the width, weight. and construction measurement in column 8.
Unroll the fabric on the inspection rablz and lay fiat.
Perform the verification of mnstrllction han area at least
1 yard from the beginning of the mll and one-tenth of
the width from the edge of the fabric. For example, on
60 in. material start at least 6 in. from one edge and 1
yard from the beginning of the fabric. Using the template required by para. M2C-320,measure a 3 in. square
and count the number of warp strands (if applicable) to
the nearest half strand in the secrion. Repeat this three
times diagons1fy across the fabric. Add the total warp
saands counted in the three 3 in. squares and divide by
nine. This will give picks pet inch in the warp o f the
fabric- Repeat for the fill (weft) strands if applicable.
Rolls whose picks per inch in either warp or fill are outside the manufacturer's specification shall not be used
for laminates made to this Standard. Enter the picks per
inch in the warp and fill of acceptable and unacceptable
rolls to the neamt 0.1 picks on Table M2C-1, column
7.
RUNFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
ARTICLE D - FIBERGLASS MILLED
FIBERS
M2D-400 PROCEDURES AND ACCEPTANCE
LIMITS
M2D-100 INTRODUCTION
M2D-410 Package Identification and Inspection
This Article specifies the minimum inspections and
tests that am to ix perfomred on the package of fiberglass milled fiber that are to bt used to fabricate equipment to this Standard.
(a) The milled fiber shall be packaged as shipped
fmm the manufacturer's factory.The milled 6 h r shall
not be repackaged in the disttibution of the material after
the manufactu~rhas shipped the milled fiber. Verify
that the milled fiber as identified by he manufacturer
has the =me nomendatu~as the milled fiber r e q u i d
by Appendix M-1 and examine each package of rniIled
fiber for damage that renders it unusable. Indicate acceptable milled fibers by recording date and namc of the
person performing the examination on Table M2D-1.
column 4.
(bl For packaged milled fiber that is found to be acceptable for further inspection, enter the reinforcemenr
production date and lot number for each package of
milled fiben used on Table M2D-I, columns 2 and 3.
M2D-200 ACCEPTANCE INSPECTIONS
{a) Acceptance inspections shall include inspection
of the milled fiber for proper packaging and identification, and visual inspection for contaminarion. Acceptancc requirements and limits are defined in paras. M2D-
410 through M2D420(a).
a) The form shown in Table M2D-1 of this Article.
or a similar form that contains the pmvisions lo record
the results of these required inspections, shall be used
by the Fabricator and shall be retained in the inspeaion
records. A separate form shall be used for each milled
fiber manufacturer, milled fiber nomenclature, and
milled fiber length.
M2D-300 EQUIPMENT REQUIRED
M2D420 Visual Inspection of Milled Fiber
{a) As milled fiber is used, it shall be visually inspected for contamination by the Fabricator. Record the
date and the inspector's name on Table M2D-1. column
5.
An inspection table and adequate overhead lighting
Packages having contapination of the milled fiber evident in the form of water, oil, g m e , ox clump-
that are suitable for the inspection of the milIed fiber we
required. The equipment used must not inrroduce contamination to the milled fiber during inspection.
ing together shall be rejected.
(c) Record the results of tht visual inspection of each
package of milled fiber on rhe inspection report.
REINFORCED THERMOSET PeASTlC
CORROSION RESISTANT EQUIPMENT
TABLE M2D-1
MILLED FIBER REINFORCEMENT LOG SHEET
Fabricator's name
Fiber manufacturer
Address
Fiber nomenclature
Fiber length
QC file no.:
1
2
3
4
5
Package
Reinforcement
Packaging
Visual
No.
Production
Date
(if given)
Lot No.
INote (111
lnspecdon
Inspection
By
Date
By
Comments on visual and packaging inspection (indicate which package):
GENERAL NOTE:
This form may be reprduced and used without written permission fmm ASMf if used for purposes other than republication.
NOTE:
(1) LOT, batch, ~ r o d u ccode,
t
or other label identifieation.
Date
REINFORCED THERMOSET PLASf lC
CORROSION RESISTANT E[1UIPMENT
MANDATORY APPENDIX M-3
MATRIX MATERIALS RECEIVfNG PROCEDURES
M3-100
INTRODUCTION
Appendix M-3 with Articles A (Visual Inspection Requirements). B (Specific Graviry),C (Viscosity, Gardner-Holdt Methd), D (Viscosity, BmMieId Method),
and E (Room Temperature Gel Time) specifies the minimum requiremenls for the inspecrions and rests that are
to be performed by rbe Fabricator personnel or an independent resting laboratory on resins and curing agents
(curing agents include accelerators, promoters, and peroxides as required for specific rains systems). These
inspections are to be performed on one mndorn sample
from each lot or batch of material received fmm a supplier. If any containers or packages are damaged. then
the contents of each damaged container shall be inspected. The requirements of this Appendix are to be
accomplished prior to acceptance of resins and curing
agents for fabrication of equipment to this Standard.
These requirements shall help assure rhat the resins and
curing agents arc c o m t l y identified; meet the manufacturer's specification;and are suitable for proper fabicaiion. curing practice, and design requirements of
equipment fabricated to this Standard.
M3-200
SAFETY
See Mated Safety Data Sheets for materials to k
used.
- VISUAL INSPECTION
REQUIREMENTS
ARTICLE A
M3A-100 INTRODUCTION
This Anicle specifies the steps that shall be followed
when inspecting resins and curing agents that are to be
used to fabricate vessels to this Standard.
{ I ) They shall be checked ta assurr they are the
products ordered.
121 They shall haw proper labeling for the specified product, including the manufacturer's pradua name
and identifying number.
(3) A sample shall be of normal color and clarity
for the specific resin, free from solid or gelled panicles
and dirt as dttcrrnined by visual examination.
(4) They shall be within the manufacnrrer's specification Iimits for specific gravity, viscosity, and m m
temperature gel rime as determined by the test melhods
of Articles B through E.
(5) Results of visual examinations and specific tests
shall be recorded on the Resin Log Sheet, Table M3F-1.
(b) Curing agents, before use, shall comply with the
following.
( I ) They shall be checked to assure they are the
products o r d e ~ d .
(2) They shall have proper hbel for the specified
product, including rhe manufacturer's product name and
identifying number.
(3) They shall have no layering or separation into
two or more phases.
CAUTION: byering or separarion presents porcnrial b t d : conwct
qphur immedia~elyat cmergtnq telrphorpe numbea shown on the
Curing Agea b g Shcct for instnrFlions if layering is obsenred.
(4) I n the case of liquids, they shall be free of sediment or suspended solids.
(5) They shall have proper curing activity as defined by the Fabricator's process andlor manufacrurer's
spacification. as determined by the mrn tempamre gel
time test (stc Article El.
161 Results of visual examination and gel time resting shall I
x recorded on the Curing Agents Log S h e .
Table M3F-2.
M3A-300 ACCEPTANCE CRITERIA
M3A-200 REQUIREMENTS
la) Resins, before use. shall comply
- - with the follow-
ing.
Materials failing visual inspection criteria or failing
manufactureis specificaiions in any pmscribed test s M not be used unless:
to meet the
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
ASME ATPI -1 995 EDITION
(a} in codtation with the manufacturer's QC contact (shown on log sheet), comctive sampling procedures are undemken which result in the material passing
visual examination; and
fi) test result differences are shown. by retest, to be
caused by p r d u d differences in tesring mther than
by differences in quality of materials.
ARTfCLE
B
-
SPECIFIC GRAVITY
M3B- 100 1NTRODUCTlON
This Article specifiesthe procedure that shall be used
to determine the spific gravity. This is accompIished
by weighing a standard volume of liquid at a specific
temperature and converting this weight to specific ,wvity
.
The following apparatus i s required:
(a) laboratory balance (0,l g sensitivity);
@I weight per gallon cup (water capacity 83.3 ml)
wirh lid (Gardner catalog No. CG 9652 or equivalent);
{c) thermometer IASTM No. 17C).
M3B-600 REPORT
Record specific graviry on the Resin Log Sheet, TabIe
M3F-1.
ARTICLE C
- VISCOSITY, GARDNERHOLDT METHOD
This Article specifies the p~ferredprocedure for determining the viscosity of nonthixompic resins. The
Gardner-Holdt methd is based on the rate a "bubble "
rises throughout the liquid resin under controlled condirions. The method determines viscosity in bubble seconds. Above 2.65 bubble seconds, the readings are
appmximately equal ro stokes. This method is not suirable for thixotmpic resins; the Brookfield rnerhod defined in Article D shall be used for thixotropic resins.
Two variations of the method are the Comparison
Method and rhe Timing Method.
(a) The Comparison Method is required for kintmatic viscosities below 6 stokes. The rare of bubble rise
is compared with rate of rise in Gardner-Holdt nurnerical standard tubes.
Ib) The Timing Method is suitable for kinematic viscosities of 6 stokes and above and interchangeable with
the Comparison Method in this viscosity m g e .
MJC-200 APPARATUS
M3B-300 PROCEDURE
la) Precondition the resin sample and weight per gallon cup for 20 min ai 25°C f0.1"C. Insen thc cup and
the =sin sample s e p t e I y in a large beaker. P k in a
25'C w a r bath.
(b) T m weigh the empty cup and lid to f 0.1 g.
{c) Fill the cup to the brim with bubble-free resin.
[dl Place the cover on the cup and farce it down to
sear fully.
(el 'Nipthe cup clean on the outside.
tfl Weigh the fiI1ed cup to f 0.1 g.
(a) Constant temperature bath, 25°C f0.1"C, with
water as the bath medium. The bath shall be equipped
with ASTM No. 23C thermometer for monitoring bath
temperature.
(b) Viscosity tubes, having clear glass and flat boitoms. 10.65 m m +0.025 mrn inside diameter, and 114
mrn f 1 mrn outside length. Plainly legible lines are to
bc located as follows:
(1) 27 m m f 0.5 mm from the ourside bortom of
the tube;
(2) 100 mm f0.5 m m f o m the outside bottom of
the tube;
(3) 108 m m f0.5 m m from the outside bottom of
the tube.
The distance between lines (I) and (2) above shall be
M3B-400 CALCULATIONS
weight. Iblgal =
73 mm f0.5 rnrn.
weight of full cup, g
specific gravity =
- tare weight. g
10
weight, Iblgal
8.33
(c) Gsrdner-Holdt references standards, consisting of
a series of standard viscosity rubes filled with transparent liquids having predetermined kinematic viscosities
in ranges of 0.10 stokes to 1000 stokes and bubble seconds as shown in Table M3C-1.
+
REINFORCED THERMOSn PLASTIC
CORROSION RESISTANT EQUTPMEMT
TABLE M3C-1
RECOMMENDED NUMERICAL STANDARDS FOR COMPARATOR VISCOSITY
TUBES
Bubbir
Secclndr
[Note (111
0.75
Tube Number
--
0.81 --
-
0.22 0.34
--
1-00
0.50 -0-6s -
1.15--
0.92
1.30--
1.15-
0.90
--
f -55--
1.85,2.20-
-
-
215 2-65
0.13
-
- A3
0.20 - A2
0.25 0.32-L
0.40
A1
-
-- A
0.50
0.63'0.80
-
8.30- 8.00-5.00-
--
40-
B
-
--80 --
50
03
--
1.26--
E
125 --
-F
1.60-G
2-00
H
2.50
-- J
-K
-200 -180
-I
-
4.00
- -- MN
-- P
50
-
--
loo --
5.00--
6.00
-
--
A30
8.00
10.0
--u
160-
-
-V
320
--
320
-
400--
400-
500 --
500
1WO--
26
2w-
250-
---
25
125
-
830
800
24
80
-0
-0
-R
-S
-T
- z2
=--
250
-L
4.00
10.0
40-
loo
3.20
Letter
32
D
--
Stokes
-13 -16 -20 -25 -32 --
1.m--
3.20
6.308.00--
Gardner-Holdt
Tube Numb~r
10
0.16
[Note {2))
3.201-
10.0
1.45-
-
0.10'
1.80
2.65[Note (211
4.00-
-
-
Gardner-Holdt
Letter
Stokes
- 27
-a
830 800
loo*--
--
29
210
GENERAL NOTE:
Table is arranged to show relationship between stokes, bubble seconds. and Gardner-Holdt letten. Stokes are shown in logarithmic progression.
NOTES:
( 1I The bubbIe time, in sewnds, of the numerical tubes under 4 see we8 determined by a technique employing a movie camera.
(21 Above 2.65 see. the bubble seconds as meawred by the kinematic method are approximately equivalent for most products.
Below 2.65 sec, this relationship does not hold.
RBNMRCEO THERMOSET PLASTIC
CORROSION RESISTAMT EQUIPMWJT
NOTE:The serits of skdards is s p e d in Iogarithmicdly even incRmenrr of h u t 26%. log 1.260 - 0.1000.The -merits are
marktd numeridly as shown ia Tabk MX-1.Since above 2.65 he
valrw are qpmximaIcly aqual to sldru. results will be r e p m i in
stok for mosr mins.
(dl Timing device in the form of a timing clock calibrated in units of 0-1 sec.
(el Inverting rack, capable of inverting three or more
viscosity tubes 180 deg. to within 1 deg. of venical position while rack and tubes are imm& in the constant
temperature bath.
0 Viscosity tube corks, No. 2 short.
@red for the bubble to risc in seconds. The t&
must
bt in the exact vedcal position. S m the timing device
when the tup of the bubble becomes tangtat lo tht 27
mm line mi the tube. Stop the timing &vice when IIR
top of the bubble kames tangent with the 1MI mm line.
This gives a 73 mm timed bubble tmvd.
to kinematic \PisId) Bubble s e ~ ~ ~ t d equivalem
s
mity in stoktg.
M3C-000 CALCULATIONS
Convut bematic viscosity in stokes to viscosity in
M3C-300 PREPARATION OF SAMPLES
All samples aFe transferred ro a viscosity rube to approximately !eve1 with the top of the 108 mm Iine. Immediately transfer the tube to the 25'C water bath wirh
cork Ioosely inserted and hoId at this temperature for 10
rnin.
M3C-400 PROCEDURE BY THE
COMPARISON METHOD
(a) Immediately following the 10 min hold time, level
off the material so that the bottom of the meniscus is
level with the 100 mrn line. Insert the cork so that the
cendpoise as follows:
noka =
poise
spccifw gravity
cemipoisc = stokes x specific p i t y x 100
M3C-700 REPORT
Record viscosity in antiwise on the Resin Lag Sheet,
Table M3F- 1.
bonom of h e cork is level with the 108 mm line. This
will assure a bubble of suitable and uniform size.
Ibl Insen the rube in the rack with the proper standard rubes and immerse with the cork down in the 25°C
constant temperature bath. Allow the rube to stand in
the barh a minimum of 20 rnin before reading the viscosity (see (c) below].
{c) T o mad the viscosity. invert the rack and compare
the rate of bubble rise of the sample bubble to those of
the standards. The tubes must remain in the exact verticaI position.
(dl The tube number is equivalent to the kinematic
viscosity in stokes.
The Brookfield method determines the viscosity nnd
thixotmpic index of a resin using a Brookfield viscometer. It is applicable for both thixotropic md nonthixotropic resins. However, because cIose control of resin
temperature and careful maintenance of the Brookfield
viscometer are required lo obrain accurate viscosity values, h e Gardrier-Holdt method defined in Article C is
preferred for nonthixompic resins.
M3C-600 PROCEDURE BY THE TIME
M3D-200 APPARATUS
METHOD (Greater Than 6 Stokes)
(a) Adjust the size of the bubble as in para. M3C400(a).
0 Insert the t u b in the nck with rhe cork down and
immerse in the 25'C constant temperature barh. Allow
the tube to stand in the bath a minimum of 20 min before
reading the viscosity.
(c) lnven the tube quickly nnd determine the time re-
ARTICLE D - VISCOSITY, BROOKFIELD
METHOD
M3D-100 INTRODUCTION
The following apparatus is required:
(a) Brooldield viscomewr model LVF (calibmted via
manufacrurrr's directions)
(b] 250 mI poiypropylem beakers
(c) constant temperature water bath at 25°C 20.1 ' C
Id} thermometer (ASTM No. I7C)
le) stainless steel spatula
@ timer. reading in 0.1 min
REINFORCED THERMOSFf PLASTlC
CORROSION RESISTANT EQUIPMENT
M3D-300 PROCEDURE FOR TEMPERATURE
ADJUSTMENT
(a) Fill M e r with material to k tested.
(b) Immcrse covered beaker in agitated 25°C water
bath and allow to come ro temperature, 2S°C f0.1 "C.
The temperature adjustment may be hastened by spatuIa
agitation of thc sample (avoid air entrapment).
Ic) Check temperature using Saybolt thermometer.
M3D-400 PROCEDURE FOR THIXOTROPIC
RESINS
(a) Agitate the resin with a spatula for 1 rnin at a a t e
of 120 rpm withour entrapment of air, replace cover on
beaker, allow to stand ior 5 rnin +0.1 min.
Ib) LRvel Bmkiield viscometer. attach spindIe and
guard as designated by resin manufacwrer.
1c) Remove beaker from bath, place open beaker in
position under Brookfield vixom&er, center and immerse spindIe to middle of the notch{d} Set s p d to 6 rpm, aart Bmkfield viscomeier
and timer. After 1 min, increw s ~ to 60
d rPm. At 2
min on timer, stop viscorneier and read. Reduce speed
to 6 rpm and take final readins 1 min after restafling.
Record the 60 rpm and 6 rpm values.
(e) Repeat steps (a) through (d) a h v e for second
reading at each spindle speed.
ASME RTP-I -1995 EDITION
BmokfieId ronstant for the particular spindle number and
rpm used to obtain the d u e .
@) Jfthe two m l t s for a pmicular spindle and speed
do not agree wiihin f 50 centipoise, ~epeatthe test.
(c) Determine thixouopic index as viscosity at 6 rpm
divided by viwarily at
rpm.
M3D-700 REPORT
Report the fo1lowing on the Resin Log Sheet, Table
M3F-1.
(a) Brookfield viscometer spindle and speed;
(b) viscosity in centipoise a[ 2S°C average d two
trials at both Vrnand 60 Vrn-
ARTICLE E
-
ROOM TEMPERATURE GEL
TIME
M3E-100 INTRODUCTION
This Anicle specifies h e pmedure that shall be used
to determine the mom temperature (25'C) gel time of
resins that have been property mixed with correctly proportioned amounts of accelerator, promoter. and peroxide curing agents.
M3E-200 APPARATUS
M3D-500 PROCEDURE FOR
NONTHIXQTROPlC RESINS
(a) Level Brookfield viscometer, attach spindle and
guard as designat4 by resin manufacturer.
(6) Remove beaker from bnth, place open bealccr in
position under Brookfield viscometer, center and immerse spindle to middle of the notch.
kc) Run viscosity at 642 rpm for 1 min with a spindle
chosen so that the Bmokfield pointer falls approximately
in h e mid-nnge of the recording dial. Alternatively,
run at rpm and spindle recommended by resin rnanufactuer. Rceord the value.
{dl Repeat steps (a) and (b) above for second result.
M3D-600 CALCULATIONS
(a) Determine viscosiry by multiplying the values
obtained in paras. M3D-400 and M3D-500 with the
The following appamus is required:
(a) constant temperature water bath at 25°C *O. 1"C
(5) popoIypropylene graduated beaker. 250 ml
(c) stainless sieel spatulas
Id) Wratory timer. calibmed in units of 0.1 rnin
Ie) laboratory balance (0.I g sensitivity)
@ graduated syringes, delivery 0.1 d to 3.0 ml
f0.01 rnl
(g) rhemwmeter (ASTM No. 17C)
M3E-300 PROCEDURE
(a) Place I00 g of resin to be tested into a clean 250
rnl polypropylene beaker. Place charged kaker in the
constant temperatuE bath previously set at 25°C
HI. 1 "C for a minimum of 20 min until the resin in the
beaker is stabilized throughout at 25 "C f0.5 "C.
(b) Add controlled promoters and/or accelcratos individually, stirring with the metal spatula between each
addition until they are thoroughly dispersed (1 rnin for
REINFORCED THERMOSET
msnc
CORROSION RESISTANT E W IPM€MT
each addition). The quantities and p ~ c i s i o nofamounts
m to be as specified by the resin supplier.
ance and use of any of the common additives in the
=in.
NOTE IIis rerommmdtd that w d t n tongue
m bt Ilsed.
s h c e Ihe). will a b r b curing mmpmnts and may also b h u&s i d l e con-mts
into the rcsin solution.
M3G-200 DEFlNlTlON AND LIMITS
(c) After addition of the promoters and accelerators.
dtow the resin to rest in
control temperature bath,
When enough of the entrapped air h r n stirring has left
the sample LO allow visual e x h a t i o n , check ~e sample fbr good dispersion, particularly of cobalt additives.
Any signs of striations or strings of the cobalt wit1 re-
the
cataIyst and mix vigorously with a clean m e t i spatula
for 1 min. Start the timer simultaneously with the stan
of mixing.
WARNING: Pemxides will matt violently if placed in dim1 conract
with metallic promoters w q a n i c accclem;ors E x ~ m
cam must
h d e n to avoid his. Refer c a ~ h l l yto peroxide manufacturer's innntcriom and Appcndix NX1-3 ror safe h i d i n g of these merials.
(4 Return the polypropylene beaker with the remaining resin to the constant temperature bath. Periodically
probe the re& solution with the spatula until such time
that the resin rums veiy thick and will "map" or break
evenly when the probe is lifted from the resin. When
h e snap occurs, stop the timer and record the time lapse
as "gel time."
M3E-400 REPORT
Record the room tempemre (25'C) gel time on the
Resin Log Sheet, Table M3F- 1.
M3G-210 Thixotmpic Agents
Thixotropic agents are flame-processed silicon diox-
ides which are used to adjust the resin flow characteristics. The laminating min shall conrain not more than
1.5 p m per I00 pam resin by weight.
Flame retardant synergists are antimony oxides which
are added to halogenated resins 10 enhance their measured flame retardant characteristics when measured per
ASTM E 84. The lamhating resin shaH not contain more
than 5 parts antimony oxide per 100 parts w i n by
weight. When pre-dispsed concentmtes are used, the
aclaminating resin shall contain not more &an 5
tive antimony oxide by weight. No more than I0 parts
of rht pre-dispersed concentrate per 100 parts resin by
weight is permissible.
M3G-230 Ultraviolet Light Absorbers
Ultravioler light absorbers a~ organic compounds
which by converting photochemical encrgy to thermal
energy effectively srabilire resin binders against the deteriorating effects of ultraviolet Ught. Only the outer surface resin-rich layer may contain the ultraviolet light
absorber.
M3G-240 Pigments
ARTICLE F - RESIN AND CURING
AGENTS LOG SHEETS
Pigments are compounds which provide coloration
andlor opacity. Only the outer surface resin-rich layer
may contain pigment.
See Tables M3F1 and M3F-2for the Resin and Curing Agents Log Sheets.
ARTICLE G - COMMON ADDITIVES
M3G-100 INTRODUCTION
This Article specifies the minimum inspections by the
Fabricator that must be p e r f o d prior to !he accept-
M3G-300 ACCEPTANCE INSPECTION
(a) The package for each of the common additives
shall be inspected at the time of delivery. Accepmce
requirements are defined in para. M3G-400.
Ib) The form shown in Table M3G-I. or a similar
form that contains the provisions to record the results of
these ~ q u i r e dinspections, shall be used by the Fabricator and shall be retained in the inspection records,
RElNFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
ASME RTP-I -1995 EDITION
TABLE M3F-I.
RESIN LOG SHEET
Manufacturer
QC contact
Spindk no.
Address
Telephone no.
Emergancy telephone no.
Date
Lat No.
Get Time
@ 2S°C
(Minutes,
VlscosIty Q 25-C
Icp)
@ 60 rpm
@ 6 rpm
Specific
Gravity
@ 25OC
Visual
Examination
-
Manufacturer's Specification:
GENERAL NOTE:
This form may be reproduced and used without written permission from ASME if wed for purposes other than republication.
TABLE M3F-2
CURING AGENTS LOG SHEW
Manufacturer
QC contact
Curing agent
Address
Standard resin
Telephone no.
Emergency telephone no.
Oate
Lot NO.
Gel Time @ 25*C (Minutes)
Visual Examination
GENERAL NOTE:
This form may be reproduced and used without written permission from ASME ifused for purposes other than republication.
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMEW
ASME RTP-1- 1995 EDITION
M3G-400 ACCEPTANCE CRlTERlA
M3G-500 INSPECTION IN USE
la) The primary package shall be clearly labetad by
the additive manufacturer to identify the contained product by manufacturer, name, and lot number.
The primary container shall be fw from damage
(a) At the time of use, additives shall be visually inspected for contamination. Solid contaminants may be
removed and discarded. Any ponion of a product which
has been agglomerated by exposure to a liquid contaminant must be mmoved and discarded before the remainder can k added to a resin.
IbJ When contamination is found. the Fabricatormust
enter the date. describe the condition. and initial the entry on the original Common Additives Log Sheet {see
Table M3G- 1 ) .
(breakage, tear, or puncture). Them shall be no visible
sign that any part of the primary container wall has at
any time been saturated with a liquid such as water.
(bl For additives found to be acceptable, the Fabricator must list the manufacturer's name, product name,
product lot number. and purpose of additive on the inspection form. In the space next to "As Received." the
inspector will sign his nnme and record the date.
REINFORCED THERMOSET PLASTtC
ASME RTP-1-1995 EDITION
CORROSION RESISTAMT EQUIPMENT
TABLE M3G-1
COMMON ADDlTlVES LOG SHEET
Raw Materials Inspeedoon
Manufacturer
Insrntot
Date
As Received
in Use Quality Probtams
Product Name
Lot Number
Additive Purpose
Manufacrurer
As Received
1
In U s e Oirality RobIems
Product Name
Lor Number
Additive Purpose
Manufacturer
As Received
In U s e Quality Problems
I
Product Name
Lot Number
Additive Purpose
Manufscturer
As Received
In Use Quality Problems
1
Product Name
tot Number
Additive Purpose
GENERAL NOTE:
This form may be reproduced and used without written permission from ASME if used for purposes orher than repubIica~ion.
RUNFORCED MERMOSm PLASnC
CORROSION RESISTANT EQUIPMENT
APPENDIX M 4
rnESIGNATED
AS APPENDIX W - 1 3
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
MANDATORY APPENDlX M-4
STRESS ANALYSIS METHODS
ARTICLE A - ANALYSIS OF
CYLINDRICAL SHELLS
Fl,(fi) = (cosh f i sin Bx
- sinh @xcos Bx)12
M4A-100 SIGN CONVENT1ON AND
NOMENCLATURE
F12(B.r)= sinh P.r sin f i
The symbols and sign convenlion adopted in this Article for the anaIysis of cylindrical shells are defined as
follows:
(21)
D = ~ t ~ 1 (1
1 2- IF'). lb-in.
E = modulus of elasticity, psi
L = ten& of cylinder, in.: subscript to
denote evaluation of a quantity at
end of cylinder removed from reference md
FIJ(B.r)=
( C O S ~fix
sin fi
+ sinh /Icos
T
13412
(22)
(23)
M = bngitudinal bending moment per
unit length of circumference, in. Iblin.
(24)
f i ( f i ) = e-a
(COS
f i -- sin Bx)
o = subscript to denote evaluation of a
quantity at reference cnd of cylinder, r = 0
p = internal pressure. psi
Q = radial shearing forces per unit
length of circumference, Iblin.
R = inside radius, in.
S = stress intensity. psi
r = thickness of cylinder, in.
M? = radial displacement of cylinder
(25)
f3I&x) = e-& (cos
(26)
h(&)= C-&
(27)
+ sin PII]
sin Bx
31, = BlllflL)
= (sinh 2j3L - sin 2flL)
/2(sinh2 BL - sid DL)
wall, in.
x = axial distance measured from the
rrferencc end of cylinder. in.
B = rotation of cylinder wall, rad
rp = Poisson's ratio
langential (circumferential) stress
component, psi
q = longirudinal (meridional) stress
component. psi
ur = radial stress component, psi
cf =
(29)
BE
=
B={BL)
= (sinh 28L
+ sin 20L)
/{sinh2 OL - sin2 BL)
ASME RTP-1- 1995 EDmON
130)
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
--:
I
GI, = GI~(BL)
=
- (cosh flL sin @L
- sinh flL cos BL)
/(sinh2 BL - sin2 BL)
GI, = Gl,(@L)
=
- 2 sinh BL sin BL
t(sinh2jYL - sin'BL)
=
- 2 (cosh BL sin BL
+ sinh BL cw BL)
The sign convention arbiuarily chosen for the analysis of cylindrical shells in this Anicle is as indicated in
FIE.M4A-1. Positive directions assumed for pertinent
qwntilies are indicated.
M4A-200 PRINCIPAL STRESSES AND
STRESS INTENSITIES DUE T0
INTERNAL PRESSURE
The formulas for principal stresses and stress intensities presented in this paragraph include the loading effects of internal pmssure only and exclude the effectsof
a11 structural discontinuities.
M4A-210 Principal Stresses
The principal strcsses developed at any p i n t in the
waIl of a cylindrical shell due to internal pressm are
given by the formulas:
x=x
X * X
x=L
FIG. M4A-1
M4A-220 Stress Intensities
-,.
fa) The general primary membrane stress intensity
developed acmss the thickness of a cylindrical shell due
to internal pressure is given by the formula:
M4A-300 BENDING ANALYSIS FOR
UNl FORMLY DISTRIBUTED EDGE
LOADS
The formulas in this paragraph describe the behavior
of a cylindrical shell when subjected to the action of
bending moments M, in.-lblin. of circumference. and
radial shearing foxes Q, Iblin. of circumference. uniformly distributed at the edges and acting at the mean
radius of the shell. The khavior of the shell due to all
other loadings must be evaluated independently and
combined by superposition.
M4A-310 Displacements, Bending Moments.
and Shearing Forces in f erms of
Condhlons at Reference Edge, x = 0
la) The radial displacement w(x), the angular displacement or rotation B(.r). the bending moments Aft-r),
and the radial shearing forces Q(x)at any axid location
A
-,- .I
RHNFORCED THERMOSET PLASTIC
CORROSION REaSTANT EQUIPMENT
ASME RTP-1-1995 EDITION
of the cylinder are given by the following equations in
terms of rv,, B,, Mopand Q,:
Q ( x ~ 2 f l '=
~ 1QJ2/3'~)ft(&)
-;z(M~zB~W~B~)
M4A-320 Edge Displacementsand Rotations In
Terms of Edge Loads
{a) The radial displacements w, and VI , and rotations
8, and -8, developed at the edges of a cylindrical shell
sustaining the action of edge loads Q,, M,,QL,
and ML
arc given by the following formulas:
Ibl In the case of cylinders of sufficient length, the
equations in (a) above reduce to those given belowThese equations may be used for cylinders characterized
by lengths not less than 318. The combined effects of
Ioadings at the two edges may be evaluated by applying
the equations to the loadings at each edge. separately,
and superposing h e results.
@J The influence functions, B's and G's, appearing
in the formu1as, (a) above, rapidly approach limiting
values as rhe length L of the cylinder increases. The
limiting vaiues are:
(1) Thus for cylindrical shells of sufficient length.
the loading conditions prescribed ar one edge do not in-
(3)
fluence the displaccrnents at the aher edge.
@) In the case of cylindrical sheIIs characterized
by Iengths not less than 3/19, the influence functions, B's
dG's. a E sufficiently close to the limiting valuts that
the Smiting valuts may lx used in the formulas, (a)
above, without significant e m .
ASME RTP-I -1 995 EDITION
(c) In the case of sufiiently short cylinders, the influence functions, B's and G's, appearing in the formulas, la) b v e , are, to a first approximation, given by
the followiug expressions:
ARTICLE B - ANALYSIS OF SPHERICAL
SHELLS
M48-100 SCOPE
(4In this Article, fomnlas are given for stresses md
deformations in spherical shells subjected to i n r d or
e x m l pressure.
0 Formulas are also given for bending malysis of
pmial spherical shells under the action of uniformly distributed edge forces and rnommts.
M48-200 NOMENCLATURE AND SIGN
CONVENTION
Introducing these expressions for the influence functions, B's and G's, into the formulas, (a) above, yields
exp~ssionsidentical: to those obtaincd by thc application of ring theory. Accordingly, the resultant exprtssions are subject to all of the lintitations inherent in the
ring theory, including the limitations due to the assumption that the entire cross-sectional area of the ring, t x
L, rotates about its centroid without distortion. Nevcrtheless, in the analysis of very short cylindrical shells
chancterized by lengths nor greater than 0.543, the
expressions may be used without intmducing significant
error.
The symbols and sign anvention adapted in tbis Article a ~ defined
e
a s follows:
p = uniform pressure. internal or ex(1)
ternal, psi
A3 = rneridional bending moment per
(2)
unit Iength of circumference, in.Iblin.
H = force per unit length of circumference, perpendicular to centerline
of sphere, Ib/in.
N = membrane force, lb/in.
Q = radial shearing force per unit of
circumference, I b/in.
S = stress intensity. psi
R = inside radius. in.
r = thickness of spherical shell, in.
E = modulus of elasticity, psi
= Poisson's mtio
D = flexural rigidity, in--lb
M4A-330 Principal Stresses Due to Bending
= ~1~/12( 1 r2)
Tk principal stresses developed at the sudaces of a
cylindrical shell at any axial location .r due to unifomly
distributed edge loads (see Fig. M4A-1) are given by
the formulas:
(I2)
(13)
114)
0 = [3(1 - v ' ) / ~ ~*]'",
r
llin.
# = meridional angle measured from
centedine of sphere, rad
= meridional angle of refcrencc edge
where loading is applied, rad
bL = meridional angL of second edge.
rad
cr = meridionat angle measured from
the refemnce edge, rad
x = length of arc for angle a, measured from reference edge of htmisphere
= Ra,in.
In these formulas where terms are preceded by a double
sign f ,the upper sign refers to the inside surface of the
cylinder and the lower sign refers to the outside surface.
(''I
X = BR
< 19)
w = radial displacement of midsurface,
in.
REINFORCED THERMOSET PLASTK
CORROSION RESISTANT EQUIPMEMT
ASME RTP-1-1995 EDITION
Spherical segment. for values of do:
F(at a) = &in
(32)
+6
-
(3)
Hemisphere for o, = ri2. tad
(b)
------e
I
0,
11
09
CI
-A
1 r, tad, and
X
-
at = tangential (cirrum ferential) stress
component, psi
(36)
at = longitudinal (rneridional) stress
component. psi
The sign convention i s listedbelow and shown in Fig.
M4B- 1 by the positive directions of the pertinent quantities.
( p ) pressure, positive radially outward
(61 lateral displacement, perpendicular
to % of sphere, positive outward
(8) mation, posi~ve when accompanied by an increase in the radius
or curvature, as caused by a positive moment
M ) , ( M moment, positive when causing
tension on the inside surface
(35)
+-------------
+@
q:
- OL1 3
=/A. rad
FIG. M4B-1
H
lateral displacement of rnidsurface, perpendicularto centerline of
spherical shell, in.
0 = rotation of midsurface, rad
o = subscript to denote a quantity at
~eferenceedge of sphere
C = subscript to denote meridional direction
t = as a subscript. used to denote circumferential direction
H ) force perpendicular to
,positive
outward
N
8
- a)
yo = tan-' (- k,), rad
or = radial stress component. psi
(33)
+@t/
Frustum. for values of 4
(+A sin
N
membrane force, positive when
causing tension
=
M4B-300 PRIMClPAL STRESSES AND
STRESS INTENSITIES RESULTING
FROM INTERNAL OR EXTERNAL
PRESSURE
I n this pmgraph formulas are given for principal
stresses and stress intensities resulting from uniformly
distributed internal or cxtemd pmsure in complete or
partial sphtrirical shells. The effects of discontinuities in
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
ASME RTP-1-1995 EDITION
aeomtrv and loading are not included and should be
&IIJ&& independen&. The smsses resulting
all
effects must be combined by superpsition.
NOTE: 'fbt fwmulas in paras. WE-339 and h14B-340 may bt wed
ifthe applisd e*kl p m e is less lhan ~ hc
tritid p w r e
wbiFh would EBUX iwabiliv of &t spherical h
1
1
.Tht value of &e
c r i r i d -re
must k e\;rlua~edin accordance with rbt ~ t -~ v e n
M4B-310 Principal Stresses R~sultIngFrom
Internal Pressure
The principal stresses at any point in the
of a
spherical shell are given by the following formulas:
(1)
(2)
a,
= or = 0
(3)
M4B-320 Stress Intensities Resulting From
Internal Pressure
The average primary srressintensiry in a sphericd she11 resulting from i n m d pressure is given by the
M4B-400 BENDING ANALYSIS FOR
UNtFORMLY DISTRIBUTED EDGE
LOADS
(a)The fonnulas in this paragraph describe the behavior of @a1 spherical shells of Ihc types shown in
Fig. M4B- 1, when subjected to the action of meridional
bending moment Mo (in.-lblin. of circumference) and
fmes H, (in.-lbh. of circumference), uniformly diitributed at the reference edge and acting at h e mean
radius of the shell. The effects of all other loading must
bt evaluated independently and combined by superpo-
sition.
The fomulas listed in lhipamgraph become less
accumtc and should be used w i h caution when Rlt is
less rhan 10 andlor the opening angle limitations shown
in Fig. M4B- I are exceeded.
formula:
M4B-410 Displacement, Rotation, Moment,
and Membrane F o ~ in
e Terms of
Loading Condltlons at Reference
Edge
M4B-330 Principal Stresses Resulting from
External Pressure
Thc principal stresses at any point in the ibral! of a
spherical shell resulting from external pressure are given
by [he following formulas:
The displacement 6. the rotation 0 , the bending moments M1, dbf,,. and the membrane forces N,. 4 at any
location of sphere are given in terms of the edge loads
Meand H, by the follo\r.ing fomulas:
1
- KZ sin (ha)]
F(ar a ) e T h [cos (ha)
M4B-340 Stress Intensities Resulting From
External Pressure
The avenge primary stress intensity in a spherical
shell resulting from external pressure is given by the
formula:
+ Ho[$
sin
diL.
x [ e ~ (ha
a
+
T,,)
- fi sin Or. + y,,)lj
4~~
#=M,Imb C<ar a)e-'" ms ( Ad
[it
+ H, -A, sin +o CCai a )e-"
1
x cos (Xu + 7J
I
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
C(at U ) ~ - ~ [ cos
K , (14
ASME RTP-1-1995 EDITION
1
+ sin (htu)]
@I h the case where the sheH under consideration is
a full hemisphere, the formulas given in (1) and (2)
above reduce to those given below:
+ K[&
A. sin +o qat ale+
R
A, sin & C(ar a)c
x [B[cr)cos (k+ rd
sin ( ~ r +
* y
2h
N,= - M
- H.
+ 2r'
-"
1
1
~ l
(41
~ cta~
[ m ~~ e sin
- ~( h l rm (h- P )
I:,
I;
-A,
+ H, - A,
M4B-430 Principal Stresses In Spherical Shells
Resulting From Edge Loads
The principal stresses at the inside and outside surfaces of a spherical shell at any location, resulting from
edge loads Meand H,, a= given by the following formulas:
cot (9,- u) sin @*C(at ~ ) e - ~
sin 6,,
C(at ale-"
In these formulas where term are preceded by a dmble sign f & upper sign rtfers to the inside surface
of the shell and the lower sign refers to the outside sur-
.
face.
M4B-500 ALTERNATE BENDING ANALYSIS
M4B-420 Displacement and Rotation of
Reference Edge in Terms of Loading
Conditions at Reference Edge
(a) At
the reference edge u = 0, and 9 = Q,. The
fornutas for the displacement and rotation (para. M4B410) simplify to those given below:
2 h' sin 9,
60 = M.
Erk,
OF A HEMISPHERICAL SHELL
SUBJECTED T O UNIFORMLY
DISTRIBUTED EDGE LOADS
If a less exacting but more expedient analysis of
hemispherical shells is required, formulas derived for
cylindrical shtlIs may be used in a modified form. The
formulas listed in this paragraph describe the behavior
of a hemispherical shell as approximated by a cylindrical shell of the same radius and thickness when subjected to the action of uniformly distributed edge loads
REINFORCED THERMOSET PLAsnc
CORROStON RESISTANT EQUIPMENT
M, and H, at (Y
= 0, x
= 0, and 4, = 90 deg. = d 2
ARTlCLE C - ANALYSIS OF FLAT
CIRCULAR HEADS
lad.
M4C-100 SCOPE
M4B-510 Displacement Rotation, Moment, and
Shear Forces In Terms of Loading
Conditions at Edge
6(x) =
H, sin' Q
M,sin 4
zgl,,
I;(&) + 1
B'Dfirar>
H, sin 4
W)=-
2820
h(8.r)+
zfi(&)
(a) In this Article, formulas are given for stresses and
displacements in flat circular plates used as heads for
pressure vessels.
@) Formulas a E also given for stresses and displactments in these heads due to forces and edge moments
uniformly distributed along the outer edge and uniformly distributed over a circle on one face. The radius
of this circle is intended to match the mean mdius of an
adjoining element such as a cylinder. cone, or spherical
segment.
(3)
(4)
M4C-200 NOMENCLATURE AND SIGN
CONVENTION
(5j
The symbols and sign conventions adopted in this Ar~icleam defined as follows:
(1) p = pressure, psi
(2) M = radial bending moment. in.-lblin. of circumference
(3)
~herefi.j5~fr.
adh are defined in Article A, Analysis
of Cylindrical Shells, and
x = aR = ( r l 2
- b)R
M4B-520 Principal Stresses in a Hemispherical
Shell Due to Edge Loads
The principal stresses in a hemispheical shell. due to
edge loads M, and H, at the inside and outside surfaces
of a hemispherical shell a any meridional llocation, are
given by the formulas:
(I)
(2,
Q
-
radialforce,Ib/in.ofcircumfe~nce
(4) ur = radial stress, psi
( 5 ) a, = longitudinal stress. psi
(6) a, = tangential (circumferential) stress, psi
(7) ~c = radial displacement. in.
(8) B = rotation.rad
(9) R = outside radius of plate, in.
(10) r = radial distance from center of plate, in.
(1 1) x = longitudinal distance from midplane of
plate, in.
r = thickness of plate
(12)
(13) t, = thickness of connecting shell at the head
junction. in.
(1 4) E = elastic modulus, psi
(15) l7= Poisson's ratio
(16) F = geometry constant, given in Table M4C-I
Tensile stresses are positive. The positive directions
of the coordinates, radial forces, momenE, and displacements are shown in Fig. M4C-1. The pressure is
assumed to act on the surface where x = -t12.
(31
In these formulas where terms are preceded by a doublc sign f. the upper sign refers to the inside surface
of the hemisphere and the lowcr sign refers to the outside surface.
M4C-300 PRESSURE AND EDGE LOADS
CIRCULAR FLAT PLATES
ON
In the following paragraphs formulas am given for the
principal stresses and deformations of flat plates under
uisymmetric loading conditions.
REINFORCED THERMOSET PLASTIC
CQRROSlON RESISTAKT WUlPMENf
ASME RTP-1- 1995 EDITION
M4C-3 10 Pressure Loads on Simply Supported
Flat Plates
The principal stresses and deformations for a flat
plate, simply supported at in periphery and loaded in
the mafiner shown in Fig. M4C-2, are given for a radial
location r at any point x in the CCDSS section by the following formulas.
Radial bending stress
Tangential bending stress
Simple
Longitudinal stress
Rotation of the midplane
X
r
4
Rotation of he midplane at the ouferedge
FIG. M4C-2
R a d i i displacement
u*=
M4C-320 Edge Loads on Flat Plates
The principal stresses and deformations of a Ilat plate
subjected m uniformly distributed edge loads, as shown
in Fig. M4C-3, are given for radial Iocation r at any
point x in the cross section by the following formulas.
Radial and tangential smsxs
Rotation of the midplme
FIG. M4C-3
REINFORCED W E R M m PtASnC
CORROSION RESISTANT MUIIPMM
ASME RTP-1-1995 EDtTION
Radial displacement
W
=
TABLE M4C-1
(1
- v)(rl
+
ulfl
Et
M4C-400 FLAT PLATE PRESSURE VESSEL
HEADS
Flu plam used as p-re
-1
h
d are anached
to a vessel shell in the manner shown by the typid ex-
amples in Fig. M K - 4 ,
Since the supcodirions ar the edge of b e plate
depend upon Iha flexibility of the adjoining shell, the
s m s distribution in the plate is influend by time shell
thickness and geomcq. The structure fomaed by the
head and the shell may b analyzed according to rhe
principles of discontinuity analysis descn'bed in Article
D.In the following paragraph formulasare given for the
quantities nccessargt to pwbm a discontinuity andpis.
M4C-410 Displacements and Principal Stresses
in a Flat Head
The head i s assumed to be separated from the adjoining shell element and under the action of the pressure
load. Figure M4C-5 illustrates this condition. The effects of the adjacent shell are ~prtsentedby thc pmssure reaction force. the discontinuity force Q,and the
discon~iwitymoment M. These act at the assumedjunction point (a). The pressure acts on the left-hand face
over a circular area defined by the inside radius of the
adjacent shell. The support point Iics on this same face
at the midradius of the adjacent shell. The formulas in
this paragraph are given in terms of rhe head dimensions
R and r and multiplying factors F, to F,. These factors
reflect the extent of h e pressure area and the location of
the junction p i n t . The numerical values for F, to F4am
given in Table M4C-1. These are functions of thc ratio
of the shcll thickness t, to the head mdius R.
FIG. M4C-4
Reaction force
4
M4C-43 1 Displacements of a Flat Head
la) For a plate simply supporred at n point (a), the
mta~ionaldisplacement 8, and the radial displacement
nb of point (a) due to pressure p acting over the area
defined by the mdius ( R - t,) are given by the following
- 4
FIG. M4C-6
formulas:
Ibl The rotarional displacements 8 and the radial displacement r of point (a) doe m a onifonnly distributed
102
REINFORCED THERMOSET PLASTiC
CORROSION RESISTANT EQUIPMENT
ASME RTP-1-1995 EDITION
d i a l force Q and moment M acring at point (a) are
given by the following formulas:
M4C-412 Principal Stresses in a Flat Head.
When the values of the discontimiry force Q and the
moment M have been determined by a discontinuity
analysis, the principal stresses in a Rat plate can be calculated as folIows:
(a} For n plate simply supported at point (a), the radid stress a, for a radial location r less than ( R - t,) at
any point .r due to pressurep acting over t h e m defined
by the radius (R - t,) is given by the following formula:
I n these expressions
Table M E - 1 lists these functions for various values
of rJR. These tabular values have been computed using
0.3 for Poisson's ratio.
M4G-600 STRESS INTENSITIES IN A FLAT
PLATE
(b) For these same conditions. the tangential stress or
and the axial stress u, are given by the following for-
mulas:
The p ~ c i p astresses
l
due to pressure p. discontinuiry
force Q, discontinuity mown1 M,and other coincident
loadings should be combinad alg&mically and the stms
differenms detennhed according to the procedures of
Subpart 38. The calculated stress intensity values should
not exceed the allowable values giiren in Subpan 38.
ARTICLE
D - DISCONTINUITY
STRESSES
M4D-100 GENERAL
(cJ The radial stress or and the tangentid stress 0, for
any radial location at any point x in the m s section,
due to uniformly distributed radial forcc Q and a unif o d y disrributed moment M acting at point (a), me
given by the formula:
M4C-500 GEOMETRY CONSTANTS
The geometry constants Ft through F, are functions
of Poisson's ratio and r,lR. Thtse are:
(a) Pressure vessels usually contain regions where
abrupt changes in geometry, material, or loading occur.
These regions at known as disconrinuiy areas and the
strcsses associated w i h~e m are known as disconrinuify
srresses. The discontinuity stresses are required to sarisfy the compatibility of deformarions of these regions.
(b) This Article describes a g e n e d procedure for
analyzing the discontinuity stresses. A numerical example is included to illusmtc the procedure.
(c) To determine the principal stresses at a discontinuity, it is necessary to evaluate the stresses caused by:
( I ) pressure;
(2) mechanical loads;
(3) thcrmal loads;
(4) discontinuity loads.
The stress intensities are then obtained by superposition
of the stresses according to the rules given in para. 3B400.
REINFORCED THERMOSET PlASTlC
CORROSION RESISTANT EQUIPMENT
ASME RTP-1- 1995 EDITION
M4D-200 INFORMATION REQUIRED
In order to pdorm a discontinuity analysis. the following information must be bown:
(a) the dimensions of the vessel:
(b] the materid properties (E, y) of the component
parts of h e vesseI (symhls as in para. M4B-200);
kc) mechanical loads, such as pressure. dead weight.
bolt loads, and pipe loads;
(dl temperature disriibution in the component parts.
The deformations due m local flexibidities may be
considered in the calculation of these influence coefi-
ciems.
kc) Calculate the edge deformations of each element
caused by loads other than d u d a n t loads.
Id) Cdcuhe the edge deformations of each element
caused by the temperature distributions.
(e) Al a c h juncture of two dements, equate the told
radial displacemeors and the total rotations of a h element.
Cfl Solve he final: system of simultaneous equations
for the redundant shears aud moments.
M4D-300 METHOD OF ANALYSIS
-
(a) The analysis of a pressure vessel containing discontinuity m a s can be performed in a stnndnrd mnnner
similar to the analysis of any statidly indeterminate
structure. The analysis is initiated by separating the yessel inro shell elcrnents of simple geometry (such as rings,
cylinders, ere.) of which the structud behavior is
known. The pressure, mechanical. and thermal loads
acting on the structure me applied to the shell elements
with a system of forces required to maintain h e static
equilibrium of each elcrnent. These loads and forces
M4D-320 Stresses
When iht values of the redundant shear forces and
moments have been determined. rhc stresses resulting
from the redundant loadings may be computed by conventional rncIhods- The final stresses for mch element
;tre determined by combining lhese stresses with the
stresses which would exist in the individual shell elements of Step 1-
cause individual element deformations, which in gen-
erai are not equal at the adjoining edges. The deformations at an eiernenr. edge are defined as:
(0 radial displacement:
42) rotation of meridian tangentA redundant moment and shear force must generally exist on the edges of the elements in order to have compatibility of deformations and restore con~inuityin the
StntClUre.
0 At each juncture discontinuity, two equations can
k wtiren which express the equality of the combined
deformations due to all thc applied loads and rhe redundant forces and moments. One equation will express the
equality of rotation; the other equation, the equality of
dispIaccment of the adjacent elements. The resulting
system of simultaneous equations can be solved to obtain the redundant moment and shear force at each juncture.
M4D-310 Procedure for Discontinuity Analysis
The following are the basic steps to follow for determining the redundant shear and moment that may exist
at a pressure vessd discontinuity.
(a) Separate the vessel into individual shell elements
at locations of discontinuity.
Calculare h e edge deformations of each elemcnt
caused by a unit shear force and a unit moment at each
edge. These values are known as influence coefficients.
M4D-400 EXAMPLE ILLUSTRATING THE
APPLICATiON OF PARAGRAPH
M4D-310
Given
A pressure vessel as shown in Figs. M4D-1 and
MJD-2.It is constmctcd ~f all-mat RTP subjected lo an
internal pressure of 15 psig. The vessel consists of:
(a) a hemispherical head
inside radius R = 30 in.
thickness r = 0.5 in.
(b) a cylindrical shell
inside radius R = 30 in.
thickness r = 0.5 in.
length L = 10 in.
(c) a flat head
outside radius R = 30.5 in.
thickness r = 6 in.
Maliterid propnies assumed:
E = lo6 psi
r7 = 0.3
Required
TO
calculate the discontinuity stresses at the location5
of s t ~ c r u n discontinuity.
l
'<
RHMFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
ASME RTP- 1-1 995 EDfTlON
of a hemispherid s M l . the hrcral force H mi
NOTE: For dis
rhe radial force Q are eqwJ.m y . thc 1aru;ll displacunent 6 aad
& radial dispIacemcnt n-arc equal.
Substituting the given dimensions and material prop
erties gives:
-10-MKI
Elernen1 B, Cylindrical Shell:
From paras. M4A-320(a) and Ib), the radiaI displacements and rotations at the edges O and L due ro edge
loadings
M,, QL,and MLare given as:
a,
in. = L-
'
FIG. M4D-1
JunctureO.--loin.0.5 in.
Mg M ~ %
Elamenr A .
Juncture L
ML%
ML
QL
Element 8 5
:,\,
#
d
-9Odg.
O;
t. -.
0.5 in.
Element C
k
'
--
6 in.
I
.i
:
0
.
;
1'
L"
(3
Substituting given dimensions and material properties
gives:
t
I
_I
FIG. M4D-2
Solution
Step 1. Separate the vessel at locations of discontinuity into individual elements.
Step 2. Calculate the influence cactficicnts,
Element A, HetrzisphericnI Head:
From para. M4&420(b), the lated displacement and
mtation at junction 0 due to edge loads Q, and M, are
given as:
'Note that 31B = 9-076 in.. whiih i s less h n tht kn@ L * 10 in.
Then by para. M4A-3W). B,, = 5,: = 1.8, = 2. and G,,= Gnr
=&Po.
REINFORCED THERMOSET PLASTIC
CORROSiON RESISTANT EQUIPMENT
ASME RTP-1-1985 EDITION
- Point O
Ehnertr C, Flat Head:
From pam. M4C-411(b), the radial displacement and
mation at j u n c t u ~L due to edge loadings QLand ML
are given as:
Substituting given dimensions and material properties
gives:
FIG. M40-3
Point L
Step 3. Calculate the edge deformations due to Ihe
internal pressure.
Element A, Hernispliericul Shell (See Fig. h14D-3):
The lateral displacement of point 0 at the midsurface
of a hemispherical shel! subjected to internal p r e s s u ~
is
givcn by the expression:
--t
--,---.
Substituting the dimensions, pressure. and material
properties gives:
II:,,
t-r
FIG. M4P-4
= 0.009767625 in.
There is no miation resultins from the internal p ~ s sure and membrane forces as shown.
There i s no rotation resulting from internal p r e s s u ~
and the membrane- forces shown.
Element B. CyIindn*calShell (See Fig. M4D-4):
The radial displacement of the midsurface of a closed
end cylindrical she11 subjected to internal pressure is
given by the expression:
-
Ekmsnt C. Flat Head (See Fig- M4D-5):
In Article C. the rotatian of a Aat head at point L due
to internal pressun? is given by para. M.CC-4 1 I (a):
Substituting the dimensions. pressure. and material
properties gives:
properties gives:
n'mprrraurrl
- I I - ~ - ~ , = 0.02314125 in-
Substituting the dimensions, pressure, md material
-
RElNFORCED THERMOSFT PLASTIC
CQRROSIOM RESISTANT EOUIFMEN'T
FIG. M 4 D - 5
Combining like terms and multiplying through by 104
results in the following system of simultaneous quations which expms compatibility at the junctum:
The didisplacement at juncture L is given by para.
M4C-411(a):
- - - Om
w m w ~ f
= -69190082
in.
x
Step 4. Calculate the fiee deformations of the edges
of each dement caused by temperature distributions.
In this example all pans of the vessel are at the mt
temperatu~~
and ~IE of the same mattrid; therefore.
temperature deformations need not. be considerd.
Step 5. Equate the to& lateral displacements and
rotations of adjacent elements at each juncture.
Juncmr~0
Step 6. Solve the above equations for Q,, Mo.QL.
and ML.
The results are:
Q, = -5.52733 lblin.
NOTE: A n c p t i v ~
sign irPdicjteP that h e 4direction o f the loadiagisoppOaitcwthatrhoKninS!cp1.
(-3.9984962Qg
= (-3.9984962
+ 2.6431369MJ
Qo
X
10"'
- 2.643 1369Ma) x 1o4
(2)
Step 7. Compute the discontinuity stresses at each
juncture due to the redundants Q,. M,, QL,and ML.
REIPlFORCED THERMOSET PLASTIC
CORROSION RESISTANT EWIMENT
ASME RTP-1-1985 EDITION
To illusrrate the procedure, these stresses Will be
computed in the cyWricaI shell (eiement B) ar both
iuncrures 0 and L.
(b) J~lncrureL. At juncture L. M(x1 = ML and ~vfx)
=w ~ .
From para. M4A-330:
(a) Junctzire 0. At juncture 0,M(x) = M, and ~vcx)
= w*.
surface
NOTE: When aompuling a,k) only h e didispksFmtent due 10the
dundsnt shear fwcc~and moments should bt d.Tht Fm duplanmnfi fi.wn Steps 3 and 4 auld not bt included.
w,
0,
6
6(83.669i86)/(0.5)'
= 2008.1 psi
= (12.09772SQ, -F 3.99849621V0}x lo-*
= -330.W psi
= -0.006686812 in.
= -6686.81 Iblin.
hf" = 0
Outside surface
uf = -6(83.6692)/[0.5)'
Inside surface
ut =
= -2008.1 psi
-28277-I
- 6(0.31'(d3:"~)@~3)'
30.25
= -2941 -02 psi
= -221.1 psi
or = 0
Outside surface
0,
NOTE: E
-
=0
10b psi.
M The discontinuity stresses in the hemispherical
shell may be computed by using the expressions given
in paras. M4H10 and M48-430.
(d) The discontinuity stresses in the flat head m y be
computed using the e x p ~ i o n given
s
in p m . M4C412.
-221.1 psi
a, = 0
Step 8. Compute the totd stresses.
The total stresses may be compaed in any element at
any juncture by combining the stresses due to the redundant shear forces a d moments, as complued in Step
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
ASME RTP-1-1995 EDITION
7, with the stresses resulting from ali other loadings. In
this case the stresses in the cylindrical shell, hemispherical shell, and fiat head due to internal pressuE may be
computed by the expressions given in paras. M4A-2 10,
M4B-3 10, and M4C412, respectively. To illustrate the
procedu~,h e total stresses in the cylindrical shell at
junctures O and L will be computed.
The stresses in the cylindrical shell due to inlernal
pressure may be compured from the expressions given
in para. M4A-210.
u, = 937.5
- 22 1.1
= 686.4 psi
Outside surface
From pressure:
01= 453.8
u, =
psi
907.5 psi
The stresses due to the redundant shear forces and
moments were computed as:
(a) Jtirtcrure 0
Inside surface
u, = -221.1 psi
R = 30.25 in.
or = 0
p = 15 psig
of
= 453.8 psi
0,
= 907.5 psi
0, =
The total stresses are:
o, = 453.8 psi
or = 907.5 - 221.1 = 686.4 psi
0
0,
The stresses due to the redundant shear forces and
moments were computed in Step 7 as:
U(
=0
(b) Jrr~lcrureL
Inside surface
The stresses due to the internal pressure are the same
as at juncture 0.
=0
0,
= 453.8 psi
or = -221.1 psi
q = 907.5 psi
u, = 0
The total stresses are:
ol
= 453.8
+ 0 = 453.8
psi
The slresses due to the redundant shear forces and
moments are:
RHNFORCED THERMOSET Pusnc
CORROSION RESISTANT EQUlPMEPlT
-
ASME RTP- 1 I995 EDITION
= 6(83.669)1(0.5)' = 2M)8 psi
The stresses due to redundant shear forces and moments m:
0,
= -2008 psi
= -6(83.669)/(0.5)'
= 1476 psi
= -3342.6 psi
Tbt total stresses are:
ul = 453.8
+ 2M)S = 2462 psi
u, = 907.5
+ 1476 = 2383 psi
The total stresses am:
C~ =
Outside surface
The stresses due to the internal pressure are the same
as at junc~ure0.
U,
453.8
- M08
=
-1554psi
= 907.5 - 3342.6 = -2435.1 psi
0,
=0
a,. = 453.8 psi
4 = 907.5
0,
=0
psi
Step 9. When evaluating the stresses in accordance
with para. W-500, the strength &ios at each location
should be computed from the total principl stresses determined in Step 8.
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
MANDATORY APPENDIX M-5
CALCULATION OF PHYSICAL AND MECHANICAL PROPERTIES USING LAMINATION
ANALYSIS METHOD
M5-100
SCOPE
This Appendix sets fonh the Lamination Analysis
Method to be used to calculate the laminate properties
needed for design.
The Lamination Analysis Merhod consists of determining the physical and mechanical properties of each
layer of a laminate and using weighted averaging techniques to determine the physical and mechanical properties of the total laminate.
Direct calculation of laminatc properties according to
para. M5-400 is required for S u b w 3B design. However, the extensive calculations required for Subpart 3B
are not necessary for Subpan 3A and they would limit
ia usefulness. Paragraphs M5-200and M5-300present
a shorter method which may be used with Subpan 3A
design d e s instead of the equations in p a . M5-400.
The equations defining the theory of f a i l u ~for use
with Subpan 3B design a r given
~
in para. M5-500,They
give rtlles for calculating the strength ratio R at a pint.
from the stiffness coefficienrs and m l t a n r forces and
moments at. the point.
The elastic properties of oriented and random glass
fikr reinforced layers have been calculated from the
theory of composite micromechanics and are pmxntsd
htte in a graphical form for convenience.
Elastic interactions between extension and shear have
been included in the gmphical data; however, other
elastic interactions between layers cannot be taken into
account with this simplified appmach. I n practice, this
meam the graphical data is accurate for laminates containimg both +$ md -8 layers, but the dab is not aecurate for a single oriented layer unless the orientation
angle is tither 0 deg. or 90 deg. Also, the graphical data
dots not account for elastic inieraction between bending
and extension or bending and shear. If the laminate does
not comply with these limitations, this simplified design
method shall not be used.
M5-200
LAMINATION ANALYSIS METHOD
The following formulas shall be used to calculare the
physical and mechanical properties of laminates.
.Y
Apparent &e
modulus = C Egk / r
h-1
,v
Apgmnt shear moduIus =
I
C GhrL t
k- 1
where
D = density, lblcu in.
V = fiber volume fraction, decimal fom
r = total laminate thickness, in.
g = thickness of layer k, in.
K = fiber weight per unit arm, lblsq A
RHNFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
E, = tensilt modulus of layer k, psi
G, = in-plane shear mdulus of layer k, psi
Zk = a m moment of inertia, in?, about the neutral
axis pf a unit width of layer k
i = d i c e from reference plane to the neutral axis
of the laminate (see Fig. M5-161,in.
4 = distance from mference plane to the centmid of
layer k (see fig. M5-16), in.
v, = P o h n ' s ratio of layer k
f = subscript denoting fiber
tent per square foot K is calculated as follows for each
layer of the laminate.
r = subscript denoting resin
k = subscript denoting layer number
The volumc fraction of glass fiber or the thickness for
tach layer of the laminate is calculated using Eq, (1). If
the laminate exists, the layer thicknesses are measured
microscopically From the edge of a sample. I f the laminate does nor physically exist, then either the glass content or thickness is assumed and the correspondingvalue
calculated. All Iaminates designed on the basis of rhis
initial assumption must be checked after fabrication to
confirm the assumed value.
The glass fiber volume fraction, orientation. and the
resin modulus at the optrating temperature are then used
to determine the mechanical pmpnies of rhe layer from
the appmpriate graphs (see Figs. M5- 1 through M5- 13).
The physical and mechanical pro@= of the layers
are tabulated, and the apprent properties of the lamtnate are calculated using the weighted averaging m&ods indicated by Eqs. (5) through (8). These methods
are illustra~edin para. M5-300,
M5-300 ANALYSIS EXAMPLE
To illustrate the Lamination Analysis Method. assume a laminate construction of VMM 1+1-54], AdRd.I.
The layer of surfacing veil V is 0.1 1 odsq ft glass fiber
veil, and the mat layers M arc 1.5 ozlsq ft chopped
strand mat. The filament wound layer [+I-541, consists
of three wind pattern closures with a wind angle of 54
deg. relative to the mandrel axis, using 225 yardflb mving and with a roving spacing of 8 strands per inch of
band width. The woven roving layer R consists of 24
ozlsq yard fabric with a 5 X 4 weave style. The glass
6 k r used i s E glass with a density Dl of 0.0943 Ib/cu
in., and the resin densiry D, is 0.0468 lblcn in. Thc
tensile modulus of the matrix at the operating tempera-
ture is 400.000 psi.
la) Layer Physical Properties. The glass fiber con-
Using Eqs. (1) and (2), calculate the glass volume
fmction and density of each layer. Results are given id
Table M5-1.
(bj Laminate Physicai Proprrties
(1) total rkickness = 0.35 1 in.
12) total glass content = IMI9 lWsq ft
13) laminate density = 0.0212 / 0.351 = 0.0604 IW
cu in.
(4) laminate weight = 0.0212 x 144 = 3-053 1W
sq ft
(5) glass content by weighr = (1,4019 1 3.05) x
100% = 46%
(c) Layer MecI~anicalProperties. Using the matrix
modulus, the glass volume penrent, and the orientation
of the gIass fiber for each layer, the corrcspodig tensile modulus. in-plane shear madulus, and Poisson's mtios aie obtained from the apprbpn'ate graphs (Figs.
M5-1 through M5-13).For layers with oriented glass
fiber, the ~ w omodulus values and Poisson's ratio are
obtained for each of the nvo principl directions of the
layer (8 for the axial direction and 90 - 6 far the hoop
dimion).
The distance r b e e n the reference plane and the
centroid of each Iayer is calculated from the layer thicknesses (refer io Fig. M5- 16).
The woven roving layer is maleled as two layers oriented at 0 deg, and 90 deg. The thickness of these two
layers is proportioned with m ~ ctot rhe weave style t51cl
for axial and W for hoop). However, the distance z between the reference plane and the centroid of this layer
is taken to the centroid of the total layer to prevent an
unbalanced calculation of the flexural properties.
The layer properties are listed in Table M5-2 and the
pmducts of these values, as required in Eqs. (5) through
(8). are l i d in Table M5-3.Using Eqs. (3) through
(8), the laminate properties are calculated; they are listed
in Table M5-4.
'3 closures; 2 hycdclo~ua;8 x 12 d
3 ltnb of roving yield.
f
I of band width: 225
X
REINFORCED THERMOSET PLASTIC
CORROSlON RESISTANT EQUIPMENT
M5-400
STIFFNESS COEFFICIENTS FOR
DESIGN BY SUBPART 3B RULES
This paragraph gives the equations required for calculating the stiffness coeficienis needed to design cylindrical vessel parts constructed of Type X Iaminates,
according to Subpart 3 8 design mles. Type X laminates
arc defined in Appendix M-I, Arride B.
Oher valid statements of lamination analysis may be
used in place of fhe equations herein, but it is the responsibility of the registered engineer to show that they
can be mathematically derived from the equations
herein.
ASME RTP-I - 1995 EDITION
ei = normal strain of a layer in the i direction (i =
1. 2, 61
E! = midplane normal srrain in direction i of the
laminate
Ki = midplane curvature along thc srructurd axis
0 x 7 OF,
normal Iayer smsses in the material coordinate
axis
oi = normal stress in the i direction t i = 1 , 2, 5 )
u6 = shear stress in the i-j coordinate system
8 = angle between the .r coordinate axis and the I
coordinate axis pig. M5-17)
us =
Lamina Reduced Stiffness
The symbols used in paragnph M5400 are defined
below.
Aij = extensional siiffness coefficients defined by Eq.
(26);i, j = 1. 2, 6
B,, = coupling stiffness coefficients defined by Eq.
(27); i , j = 1. 2, 6
Di,= bending stiffness coeficicnts defined by Eq.
(28): i , j = l , 2 , 6
EI = Young's modulus of an onhotropic lamina in
the principal direction of the gmaier modulus
E, = Young's modulus of an onhorropic Iamina in
rhe principai d i ~ c t i ~ofnthe lesser modulus
E, = shear modulus of an ortholropic lamina in the
principal coordinates
M , = moment resultant about I axis (Fig. M5-15)
1
%
= mornenl resultant about 2 axis (Fig. MS-14)
M, = twisting resultant (Fig. M5- 14)
N, = force resultant in I direction (Fig. M5-15)
N2 = force resultanr in 2 direction (Fig. M5-IS)
N6 = in-plane shear force resultant (Fig. h.15-15)
en,
a,,,
Q??.
Q,,= reduced stiffness in
h e principal material direction, defined by Eqs. (4) through (7) (onaxis directions)
Q,, = reduced stiffness transformed to the vessel
(1-2) axes (off-axis directions); i , j = 1, 2 , 6
r, = thickness of the
layer (Ag. M5-16)
zk = distance from the reference surface to the center of h e Phlayer (Fig. M5-16)
EI. E , ,
E, =
z~ =
normal layer strains in the material coordinate
axis
principal Poisson's ratio of a lamina (the negative of strain in the y direction from stress in
the x direction)
The stress-strain relations in rhe principal material directions of an orthotropic lamina are as follows.
The reduced stiffnesses of a lamina are calculated
from [he elastic properties, E,, E,., ,;I and Es. These
may be measured values or calculaied by the sernigraphicd procedure belo~v.The required input information
far each layer is the fiber weight per unit area, the tensile modulus of the resin matrix, the type of reinforcement, and the fiber density.
A step-by-step procedure for lamina with unidirectional roving is as follou,~.
( I ) Calculate the volume fraction of fiber Vffrom Eq.
(1) in para. M5-200.
(2) Using the value of V, from step (11, obtain rhe
value of Er from Fig. M5-3,M5-5,M5-7,or M5-9,
depending on the value of VI. E, is I h e value of the modulus at an orientation angle of 0 deg. Obtain E,. frorn the
same graph as the value of the modulus at an drienration
angle of 90 deg.
(3) Using h e value of Vf from step (I), obtain the
value of E, frorn Fig. M54, M5-6,M5-8,or M5-10,
depending on the value of Vp EE,is the in-plane shear
modulus at an orientation angle of 0 deg.
(4) The major Poisson's ratio v, is obtained from Fig.
M5-13 for an orientation angle of 0 deg.
The reduced stiffnesses of each lamina are then given
as follows.
REINFORCED THERMOSFT PLASTIC
CORROSION RESISTANT EQUIPMENT
ASME RTP-1-1995 EDITION
a-= ~>-W(l-
GV&
wbere v,. = Y, E, / Ex. Lrnina with randamly oriented
fibers are isotropic in the plane of the laminate, and art
characterized by a single tensile modulus E and Poisson's ratio v. To obtain E and v :
111 Calculate V, from Eq. (1) in para. M5-200.
(2) The tensile modulus is obtained using the value
of V,, from step (1 ) and Fig. kl5-I.
(3) Poisson's ratio is given by Y = 0.33.
In an isotropic lamina, Ex = E,. = E and P, = Y,. =
r. Then rhe reduced stifmesses in-anisotropic layer are
computed from:
The stress-strain relations for the lamina in the 1-2
coordinates ME:
In an isotropic laminate, the reduced stiffnesses have
the same value for any value of 8, so that the stresssmin retation for the 1-2 system has the same form as
Eqs. (11, (21, and (3)-
MS-430
Stiffness CoeWcients for the
Laminate
-
The stiffness coeficients A,+ B p and Dq are used to
relare the resultant forces and moments (Figs. M5-14
and M5- 15) to the middle surface strains and curvatures.
The transformed reduced stiffnesses are the reduced
stiffnesses expressed in the 1-2 system. The relationship
between the .r-y and 1-2 axis systems is shown in Fig,
M5-17. The 1-2 systcm is in the plane of the laminate
and is chosen for convenience. A typicat choice would
be to align 1 with the circumferential vessel direction
and 2 with the axid direction. The transformed reduced
stihesses Qy are caiculated from the ~ d u c e d
sriflitesses
and the angle 8. Let m = cos 8 and 11 = sin 8. Then the
equations for the transformed reduced stiffncsses are:
=
CQ,
+ Q, - 4Q,~?n'+ a & m 4 + n')
(la)
REINFORCED THERMOSET PtASnC
CORROSION RESISTANT EQUIPMENT
(e) Calmlare the coupling gtiffntss&dents
Bu for
the Iaminate from the (&)kt tk, t ,and &. (27).
(f)CalcnIatt rht bending stiffness coefficients Dufor
the laminate from the [Q& tk, a,and Eq. (28).
The &tensional stifie-ss coeficients are calculated
from the transformed reduced stihesses for each layer
(Qu)k, the thicknesses t,, and the distance a.The 10cation of the reference plane in the z direction does not
affect the validity of the equations in this paragmph.
However, it must coincide with the plane to which the
s f n s resultants and moments are referred for design by
Subpan 3B, or it mwt coincide with the neutral axis as
specified in para. M5-200 for design by Subpart 3A.
whe~
i = l,2,6
j = l,2,6
N
=
number of layers
The stiffness coefficients are what are required for
suess analysis.
M5-440
Procedure for Calculating the
Stiffness Coefncients
This section contains a step-by-step algorithm for calculating the laminate sriflncss coefficients.
la) Fmrn the known layer thicknesses and laminating
sequence, calculate t, and zk for each layer.
@I For each layer, obtain values for (Ex),, (EJk,
(v,),,
and (E,),, and compute the reduced stiffntsses
isowpic plies, use Eqs. (8) through (10).
(QA,
(Q)tl
a d (QyylL fmEqs (4) through (7) For
Ic) T d o r m the reduced stiffness (Qli)t for each
layer from the principal material directions to the vessel
directions, using Eqs. (1 11 through (16), to obtain the
transformed d u d stiffness for each layer (Q&. In
the case of isotropic layers, the transformation is not
required, because Qs. @), (9), and (10) are valid for
all angles B.
Id) Calculate the extensional stiffness coefficients AU
for the entire laminate from the CQir)k,tk,and Eq. (26).
M5-500
THE QUADRATIC lNTERACTION
CRlTERION
In general, a lamina bas five independent uniaxial ultimate strengths: tensile and compressive strengths in
the principal direction of g m e r strength, tensile and
compressive strengths in the direction of lesserstrength,
and shear smngth with respect to a pure shear stress in
the principal directions. Type I and Il laminates are
treated as isotropic herein, sa any direction can be cons i d e d as a principal direction. In Typc X laminates,
rhe principal direction of greater strength is aligned w i h
the continuous roving and the principal direction of
lesser strength is perpendicular to the roving. Further,
the five smngth values may be unequal.
The quadratic interaction criterion defines the interactions between the five strengths in cases when more
than one component of stress is applied to the lamina.
and it defines aliowablt stress states in terms of the
strengths.
The criterion is applied to each lamina separately, and
if one or more lamina fail the criterion, tbe corresponding load on the vessel is not allowed, The criterion is
applied separately to each combination of smsses or
stress and moment resultants calcuIated by the rules of
p m . 33-400. In the following seaions it is assumed
that the laminate stiffnesscoefficients aad sbxs and moment multants haye shady been calculated for all sections md load combinations under c o n s i d d o n .
The rest of para. M5-500gives the definitions and
equations needed to make the wlcul;ttioas reqby
paras. 3B-400 and 3B-500,
M5-510
Nomenclature
In addition to the n o m e n d m defined in para. M5410. the following symbols are used.
F,, F,,
F,,,Fx,
F, = saeagtb paramerers defined in terms of the five
strengths
X = ultimate tensile suength of a Iamina in the x
(strong) direction
X, = ultimate compressive strength of a lamina in the
x direction
Y = ultimate tensile suength of a lamina in the weak
direction
Pwnc
REINFORCED THERMOSET
CORROSION RESISTANT EQUIPMENT
Y, = ultimate wmprtssivc strength ofa lamina in h e
weak direction
S = ultimate shear strength with respect to shar
stin the x-y axes
Sii = i-j component of the compliance matrix [the
compliance matrix is the inverse of the stiffness
matrix defined by Eqs. (20) through (2511
lv = pameter that equals 1 for the upper surface of
a laminate and -1 for the Iower
(b) M5-520
Calculation of Layer Strains and
Stresses
The strains at the reference surface are calculatd
using the force and moment resultants and the inverted
stiffness matrix of the laminate. The invert.4 stiffness
matrix is defincd as follows.
The strains in each Iayer are then obtained from Eqs.
0)m u &
19);
(tlk = f + Q + n~fl)K,
If Ihe rhickness of any layer is less than one-fifth of
the total lamiaate thickness, then the strains at the midplane of the layer are sufficientIy accurate and w = 0.
Otherwise, the surface strains must bt calculated by xtting w = 1 for the uppr surface or w = 1 for the
lower surface.
The layer strains art then transformed to the axis of
each layer by Eqs. (10) thmugh (12).
-
where i = 1 to 6 and j = 1 to 6 . inclusive.
The strains and curvatures at the reference surface are
then calculated by Eqs. (1) through (6):
The corresponding st~essesin each layer a then -1culated by Eqs. (13) through (15).
M5-530
Calculation of Strength Ratios
The strength ratio is the ratio of thc stress capacity of
a single layer relative to the stress generated by an applied loading condition, and is cdculated by using the
suesses from Eqs. (13) through (15) and the fallowing
quadratic interaction equation [Eq. I 16)1.
The smngth ratio R is then given by
(b)
Id1
(el
REINFORCED THERMOSET Pumc
CORROSION RESISTANT EQUIPMENT
Random
Oriented
FSkr
Fik
O . m
0.0120
0.0015
0.ODSO
0.0268
Tht strength coefficients are calculared using the layer
strengths as follows.
I
F,. = w,
The layer smngh may be derermined from approp d e testing of individual layers or they m y be calmlatad using strain limits as follows.
The strain limits may be determined from appropriate
tesring of individual layers w the following smin limits
may be used.
M5-540
Procadure for Calculating the
Strength Ratio
The following computation must be performed for
each sel of superimposed resultants required by para. 3B400.
(a) Compute the reference surface strains, cumawes,
and twist using Eqs. (I) through (6). These are in rhe yessel coordinates.
Ibl For h e upper and lower surfaces of each lamina.
calcuIate the swains in vessel coordinates using Eqs. (7)
m u g h (9).
[cl Calculate the stresses in vessel coordinates at the
upger and lower surface of each lamina from the results
of (b) using Eqs. (1 0) through (12).
(d} Transform the stresscs computed in (c) to on-axis
coordinates using Eqs. (13) through (15). Each lamina
may have a different K.
(el Calculate the strength ratio at h e top and bouom
surfaces for each lamina using Eqs. (16) and (17).
REINFORCEDTHERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
-ER-
0
100,000~
- ER - 2100,000psi
0 -ER-300.000pi
-ER-400.OM)pi
x -ER-500,OOOpsi
0-ER-MX1.000psi
V - ER 7700.000 psi
+
-
X I
I
f
I
I
I
I
t
t
I
I
I
I
f
I
I
I
1
I
0
5
10
15
20
25
30
35
Vo!. Percent Glass Fiber
FIG. M5-1
RANDOM GLASS FIBER
118
I
1
I
40
REINFORCED THERMOSEF
msnc
CORROSION RESISTANT EQUIPMENT
- ER - 100,000 psi
- ER - 200.000 psl
- ER - 300,000 psi
+ -ER-m,OM3pai
x - ER - 6 0 0 . 0 0 0 ~
0 - ER - 600.000 psi
V
ER - 700,000 psi
0
A
-
r
I
15
20
26
V d , Petcern Glass Fiber
FIG. ME-1
RANDOM GLASS FIBER
118
REINFORCED THERMOSET PLASTIC
CORFlOSlOM RESISTANT EQUIPMENT
(2s)
The extensional stiffness coefficients are calculated
from the transformed reduced sriffnessa for each layer
(Q& the thicknesses t ~md
, the distance zk. The location of the reference plane in the t direction does not
affect the validity of the equations in thii paragraph.
However. it musr coincide with the plane to which the
stress resultants and moments are referred for design by
Subpan 3B, or ir must coincide with the neutral axis as
specified in para. M5-200b r design by Subpart 3A.
(28)
where
i = 1.2. 6
j = 1,2,6
N = number of layers
The stiffness coefficients are what -are required for
stass analysis.
M5-440
Procedure for Calculating the
Stiffness Coefficients
This section contains a step-by-step algorithm for calculating the laminate sriffness coefficients.
(a) From the known layer thicknesses and laminaring
sequence, calcuIate t, and ra for each layer.
(b) For each layer, obrain values for
(E,.),,
( v , ) ~ . and (EJk, and compute the reduced stiffnesses
(Q,>,. (&)k, and EQv,-)a f~ Eqs. (4) through (7)- For
isotropic plies, use
(8) through (10).
(c) Transform the reduced stiffness (Q& for each
layer from the principal material directions to the vessel
directions. using Eqs. (11) through <]ti), to obtain the
transformed reduced stiffness for each layer (Qij!k. In
he case of isotropic layers, the transformation is not
required, because Eqs. (8). 191, and (10) are valid for
all angles 8.
{dl Calculate the extensional stiffness cocficients Aij
for the entire laminate from the (Qii),, it. and Eq. (26).
Gs.
re) Cakulate the coupling stiffnesscoefficients Bij for
the laminate fmm the (Qv)t, rk, zk. and Eq. (27).
(1)Catculate rhe bending stiffnm coeficicnts Dii for
the laminate from h e (Q&, tt. 4,and Eq. (28).
M5-500
THE QUADRATIC IN1ERACTION
CRITERION
Tn general. a lamina has five independent uniaxial ultimate strengths: tensile and compressive strengths in
the principal direction of grearer strength, tensile and
compressive strengths in the direction of lesser smngth*
and shear stren@h \r.ith respect to a pure shear s m in
the principal directions. Type I and Il laminates are
mated as isotropic herein, so any direction can be c m sidered as a principal direction. In Type X laminates,
the principal direction of greater strength is aligned with
the continuous roving and the principal direction of
lesser strength is perpendicular to the roving. Further.
rhe five stmgth values may be unequal.
The quadratic intemction criterion defines the interactions belween the five strengths in casts when more
than one component of stress is applied to the lamina,
and it defines allowable stress states in terms of thc
strengths.
The criterion is applied ro each lamina separately, and
if w e or more Iamina fail the criterion, the corresponding bad on the t7essel is not allowed. The criterion is
applied separately to each combination of stresses or
stmss and moment resultants calculated by the rules of
pam. 3B400. In the following sections it is assumed
thar the laminare stiffnesscaefficientsand s i n s and moment resultants have already been cdclated for all sections and load combinations under consideration.
The rest of para. M5-500gives the definitions and
equations needed to make the calculations required by
paras. 3B400 and 3B-500.
M5-510
Nomenclature
In addition to the nomenclature &fined in pam.
4 10. the following ssymbols are used.
MI
F, F,,,
Fssm Fxv
F,
= strength m e t e r s defined in terms of the five
strengths
ultimate tensile strength of a lamina in the x
(strong) direction
X, = ultimate compressive strength of a lamina in the
x dimtion
Y = ultimate tensile strength of a lamina in the weak
direction
X
=
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
Y, = ultimate camp-ive streng1:hof a lamina in the
weak direction
S = ultimate shear strength with respecr
to shear
s t ~ s sin the x-j* axes
Sv = i-j component of the compliance matrix [the
compliance matrix is the inverse ofthe stiffness
matrix defined by Eqs. (20) through (25) J
w = parmeter that equals 1 for the upper surface of
a laminate d -1 for the lower
M5-620
Equations (71,(81, and (9) give strains at the upper surface of the lamina when w = 1 and the bwer surface
when w = -1. The corresponding stresses are then cdculatad from the swabs and the reduced niffnesses in
the vessel coodinares as follows.
Lamina Stresses and Strains
The first step in using the quadratic interaction criterion is u, compute the upper and tower surface strains
in each lamina. The suains are computed from the reference surface strains and curvatures. which am obtained from rhe forre and moment resulm~sby Eqs. ( I )
through (6).
The final step in cdculating the stresses is to express
h e vessel coordinate lamina stress componems in terns
of the principal material coordinates, in each of the hmha. The socalicd on-axis components of stress are given
by the usual transformation equations as follows.
M5-630
(4)
The quadratic interaction criterion required by this
Standnrd is as follows.
where
Thc upper and lower surface strains in each layer (A)
are then obtained from Eqs. (7) through (9).
Calculation of Strength Ratio
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
-
ASME RTP- 1 1995 EDITION
Then the solution for R is the positive of the two values
given by
For Type I1 (or other oriented fiber layer):
For each mess state under considemion, R must be
equal to or greater than the value required by para. 3B500.
M5-540
Procedure for Calculating the
Strength Ratio
The following computation must be performed for
each set of superposed stress resultants required by para.
For Type I (or other random fiber layer):
Measured values of X. X,, Y, Y., and 5 may be used
instead. The tern in the parentheses in Eq. (16) conrain
the five strength properties and thc on-axis stress components of a lamina. which are known. and Eq. (16) can
be soIved for R. Let
3B-400.
( I ] Compuw the reference surface strains. cumtures, and rwist using Eqs. ( I ) through (6). Thtse are in
the vessel coordhws.
121 For rhe upper and lower surface of each lamina,
calculate h e strains in vessel coordinates using Eqs. (7)
through (9).
(3) Calculate the stresses in vessel coordinates at the
upper and lower surface of each lamina from the results
of step (2) using Eqs. ( 10) through (1 2).
(4) Tmnsform the stresses computed in step (3) to
on-axis coordinates using Ep.(13) through (15). Each
iamina may have a different K.
(5) Calculate the strength mtio at the top and bottom
surFact for each lamina using Eqs. (16) and (1 7).
REINFORCED THERMOSET PLASTIC
CORROSION RESISTANT EQUIPMENT
ASME RTP-1-1995 EDITION
Vol. Percent Glass Fiber
FIG. M5-1
RANDOM GLASS FIBER
118
REINFORCED 1)IERMOSET PLASTIC
CORROSION RESISTAMT EQUIPMENT
ASME RTP- 1 - 1 905 EDITION
Vol. Percent Glass Fiber
FIG. M5-2 RANDOM GLASS FIBER
I19