ENGINEERING DELIVERABLE
Document No.
Rev. : 1
MECHANICAL CALCULATION OF
FAME ANALYSIS TANK
CAL-230-020-004
Page No.
1 of 55
DISCIPLINE
: MECHANICAL
CLIENT
: PT. JHONLIN AGRO RAYA
PROJECT NAME
: PEMBANGUNAN PABRIK BIODIESEL
PLANT KAPASITAS 1500 TPD
TERMASUK PRETREATMENT,
BATULICIN, KALIMANTAN SELATAN
1
31-Aug-20
Issued For Approval
JN
RDT
AR
0
21-Jan-20
Issued For Approval
JN
IS
AR
PREP'D
Rev
Date
Description
CHK'D
APP'D
PT. WIKA Rekayasa Konstruksi
APP'D
APP'D
PT. Damanito
PT. Jhonlin Agro
Teknologi
Raya
Rekatama
ENGINEERING DELIVERABLE
Document No.
CAL-230-020-004
MECHANICAL CALCULATION OF
FAME ANALYSIS TANK
Rev. : 1
Page No.
1 of 55
REVISION SHEET
Rev. No.
Date
Description
1
5-Aug-20
Perubahan internal design pressure dari sebelumnya atmospheric menjadi 7.5 kPa
1
5-Aug-20
perubahan design top member, dari sebelumnya detail B dengan size angle bar
L100x100x8mm menjadi detail B dengan sixe L200x200x15mm
AMETANK REPORT
Page: 1/53
TABLE OF CONTENTS
SUMMARY OF DESIGN DATA AND REMARKS
ROOF DESIGN
ROOF SUMMARY OF RESULTS
SHELL COURSE DESIGN
SHELL SUMMARY OF RESULTS
BOTTOM DESIGN
BOTTOM SUMMARY OF RESULTS
WIND MOMENT
SEISMIC SITE GROUND MOTION
SEISMIC CALCULATIONS
ANCHOR BOLT DESIGN
ANCHOR BOLT SUMMARY OF RESULTS
CAPACITIES AND WEIGHTS
MAWP & MAWV SUMMARY
Page: 2/53
No Warnings!!
SUMMARY OF DESIGN DATA AND REMARKS Back
Job : Fame Analysis Tank 500 MT
Date of Calcs. : 27-Aug-2020
Mfg. or Insp. Date :
Designer : WRK
Project : Proyek Pembangunan Pabrik Biodiesel Plant Kapasitas 1500TPD termasuk Pre-treatment
Tag Number : 220-TK-115
Plant Location : Kalimantan Selatan
Site : Batulicin
Design Basis : API-650 12th Edition, March 2013
1
Design Internal Pressure = 7.5 KPa or 764.8575 mmh2o
Design External Pressure = -0 KPa or -0 mmh2o
MAWP = 8.1534 KPa or 831.4938 mmh2o
MAWV = -1.015 KPa or -103.5101 mmh2o
D of Tank = 7.7 m
OD of Tank = 7.716 m
ID of Tank = 7.7 m
CL of Tank = 7.708 m
Shell Height = 14.7 m
S.G of Contents = 1
Max Liq. Level = 13.9 m
Min Liq. Level = 0.6 m
Design Temperature = 90 ºC
Tank Joint Efficiency = 0.85
Ground Snow Load = 0 KPa
Roof Live Load = 1 KPa
Additional Roof Dead Load = 0 KPa
Basic Wind Velocity = 120 kph
Wind Importance Factor = 1
Using Seismic Method: API-650 - ASCE7 Mapped(Ss & S1)
Seismic Use Group = II
Site Class = E
T_L (sec) = 4
Ss (g) = 0.12
S1 (g) = 0.05
Av (g) = 0.1
Q = 0.67
Importance Factor = 1
DESIGNER REMARKS
Remarks or Comments
Page: 3/53
SUMMARY OF SHELL RESULTS
Shell Width
CA
Material
# (mm)
(mm)
JE
Min
t-min
Tensile
t-min
t-min
Yield
Sd
St Weight Weight
t-Des t-Test
ExtStrength
Erection
Seismic
Strength
(MPa) (MPa)
(N) CA (N)
(mm) (mm)
Pe
(MPa)
(mm)
(mm)
(MPa)
(mm)
1
1800
A283MC
1.7 0.85
205
380
137
154 26,759 21,078
6 5.6562 3.3322
4.384
2
1800
A283MC
1.7 0.85
205
380
137
154 26,759 21,078
5 5.1605 2.8912
3
1800
A283MC
1.7 0.85
205
380
137
154 20,075 14,390
4
1800
A283MC
1.7 0.85
205
380
137
5
1500
A283MC
1.7 0.85
205
380
6
1500
A283MC
1.7 0.85
205
7
1500
A283MC
1.7 0.85
8
1500
A283MC
9
1500
A283MC
6
8
OK
4.0317
NA 5.1605
8
OK
5 4.6648 2.4502
3.5017
NA
5
6
OK
154 20,075 14,390
5 4.1691 2.0092
3.1821
NA
5
6
OK
137
154 16,729 11,991
5 3.6733 1.5682
2.8632
NA
5
6
OK
380
137
154 16,729 11,991
5 3.2602 1.2007
2.5977
NA
5
6
OK
205
380
137
154 16,729 11,991
5 2.8471 0.8332
2.3284
NA
5
6
OK
1.7 0.85
205
380
137
154 16,729 11,991
5 2.434 0.4657
2.0551
NA
5
6
OK
1.7 0.85
205
380
137
154 16,729 11,991
5 2.0209 0.0982
1.7851
NA
5
6
OK
Total Weight of Shell = 177,316.3901 N
CONE ROOF
Plates Material = A283M-C
Structural Material = A36M
t.required = 6 mm
t.actual = 6 mm
Roof corrosion allowance = 1 mm
Roof Joint Efficiency = 0.85
Plates Overlap Weight = 443.4819 N
Plates Weight = 22,201.2901 N
RAFTERS:
Qty At Radius (m)
Size Length (m) W (N/m) Ind. Weight (N) Total Weight (N)
12
3.85 IPE120
3.5243 101.9891
359.4483
4,313.3802
Rafters Total Weight = 4,313.3802 N
Bottom Type : Cone-Up Bottom Floor
Bottom Material = A283M-C
t.required = 7.7 mm
t.actual = 8 mm
Bottom corrosion allowance = 1.7 mm
Bottom Joint Efficiency = 0.85
Total Weight of Bottom = 29,517.6312 N
ANCHOR BOLT : (10) M33 mm UNC Bolts, A36M
Page: 4/53
NA
tt-min
Actual Status
(mm)
(mm)
TOP END STIFFENER : Detail B
Size = l200x200x15
1 Material = A36M
Weight = 11,102.9272 N
INTERMEDIATE STIFFENERS QTY (: 2)
Stiffener
Size Elevation (m) Z-Req'd (cm3) Z-Actual (cm3) Weight (N)
1 l76x76x12.7
8
6.3673
48.5332 3,349.1878
2 l76x76x12.7
11
4.6605
48.5332 3,349.1878
TANK NAMEPLATE INFORMATION
Pressure Combination Factor
0.4
Design Standard API-650 12th Edition, March 2013
Appendices Used
E, F
Roof
A283M-C : 6 mm
Shell (1)
A283M-C : 8 mm
Shell (2)
A283M-C : 8 mm
Shell (3)
A283M-C : 6 mm
Shell (4)
A283M-C : 6 mm
Shell (5)
A283M-C : 6 mm
Shell (6)
A283M-C : 6 mm
Shell (7)
A283M-C : 6 mm
Shell (8)
A283M-C : 6 mm
Shell (9)
A283M-C : 6 mm
Bottom
A283M-C : 8 mm
Page: 5/53
STRUCTURALLY SUPPORTED CONICAL ROOF Back
A = Actual Part. Area of Roof-to-shell Juncture per API-650 (cm^2)
A-min = Minimum participating area (cm^2) per API-650 5.10.5.2
a-min-A = Minimum participating area due to full design pressure per API-650 F.5.1 (cm^2)
a-min-Roof = Minimum participating area per API-650 App. F.5.2 (cm^2)
Add-DL = Added Dead load (kPa)
Alpha = 1/2 the included apex angle of cone (degrees)
Aroof = Contributing Area due to roof plates (cm^2)
Ashell = Contributing Area due to shell plates (cm^2)
CA = Roof corrosion allowance (mm)
D = Tank Nominal Diameter per API-650 5.6.1.1 Note 1 (m)
density = Density of roof (kg/mm3)
DL = Dead load (kPa)
e.1b = Gravity Roof Load (1) - Balanced (kPa)
e.1u = Gravity Roof Load (1) - Unbalanced (kPa)
e.2b = Gravity Roof Load (2) - Balanced (kPa)
e.2u = Gravity Roof Load (2) - Unbalanced (kPa)
Fp = Pressure Combination Factor
Fy = smallest of the yield strength (MPa)
Fy-roof = Minimum yield strength for shell material (Table 5-2a) (MPa)
Fy-shell = Minimum yield strength for shell material (Table 5-2a) (MPa)
Fy-stiff = Minimum yield strength for stiffener material (Table 5-2a) (MPa)
hr = Roof height (m)
ID = Tank Inner Diameter (m)
Insulation = Roof Insulation (m)
JEr = Roof joint efficiency
Lr = Entered Roof Live Load (kPa)
Lr-1 = Computed Roof Live Load, including External Pressure
Max-p = Max Roof Load due to participating Area (kPa)
Net-Uplift = Uplift due to internal pressure minus nominal weight of shell, roof and attached framing
(N), per API-650 F.1.2
P = Minimum participating area (kPa)
P-ext-2 = Max external pressure due to roof shell joint area (kPa)
P-F41 = Max design pressure limited by the roof-to-shell joint (kPa)
P-F42 = Max design pressure due to Uplift per API-650 F.4.2 (kPa)
P-F51 = Max design pressure reversing a-min-A calculation (kPa)
P-max-ext-T = Total max external pressure due to roof actual thickness and roof participating area
(kPa)
P-max-internal = Maximum design pressure and test procedure per API-650 F.4, F.5. (kPa)
P-Std = Max pressure pressure allowed per API-650 App. F.1 & F.7 (kPa)
P-Uplift = Uplift case per API-650 1.1.1 (N)
P-weight = Dead load of roof plate (kPa)
Pe = External Pressure (kPa)
pt = Roof cone pitch (mm) rise per 12 (mm)
Pv = Internal Pressure (kPa)
R = Roof horizontal radius (m)
Ra = Roof surface area (cm^2)
Roof-wc = Weight corroded of roof plates (N)
S = Ground Snow Load per ASCE 7-05 Fig 7-1 (kPa)
Sb = Balanced Design Snow Load per API-650 Section 5.2.1.h.1 (kPa)
Shell-wc = Weight corroded of shell (N)
Su = Unbalanced Design Snow Load per API-650 Section 5.2.1.h.2 (kPa)
T = Balanced Roof Design Load per API-650 Appendix R (kPa)
t-calc = Minimum nominal roof plates thickness per API-650 Section 5.10.5.1 (mm)
t-Ins = thickness of Roof Insulation (m)
Theta = Angle of cone to the horizontal (degrees)
U = Unbalanced Roof Design Load per API-650 Appendix R (kPa)
Wc = Maximum width of participating shell per API-650 Fig. F-2 (mm)
Wh = Maximum width of participating roof per API-650 Fig. F-2 (mm)
Page: 6/53
Roof Design Per API-650
Note: Tank Pressure Combination Factor Fp = 0.4
D = 7.7 m
ID = 7.7 m
CA = 1 mm
R = 3.9098 m
Fp = 0.4
JEr = 0.85
JEs = 0.85
JEst = 0.85
Insulation = 0 m
Add-DL = 0 kPa
Lr = 1 kPa
S = 0 kPa
Sb = 0 kPa
Su = 0 kPa
density = 0.000007841 kg/mm3
P-weight = 0.4768 KPa
Pe = 0 kPa
pt = 0.75 mm rise per 12 mm
t-actual = 6 mm
Fy-roof = 205 MPa
Fy-shell = 205 MPa
Fy-stiff = 250 MPa
Shell-wc = 130,896.6472 N
Roof-wc = 18,501.0751 N
P-Std = 18 kPa, Per API-650 F.1.3
t-1 = 6 mm
CA-1 = 1.7 mm
Sd = 137 MPa
Theta = TAN^-1 (pt/12)
Theta = TAN^-1 (0.75/12)
Theta = 3.5763 degrees
Alpha = 90 - Theta
Alpha = 90 - 3.5763
Alpha = 86.4237 degrees
Ap-Vert = D^2 * TAN(Theta)/4
Ap-Vert = 7.7^2 * TAN(3.5763)/4
Ap-Vert = 0.9264 m^2
Horizontal Projected Area of Roof per API-650 5.2.1.f
Xw = D * 0.5
Xw = 7.7 * 0.5
Xw = 3.85 m
Ap = PI * (D/2)^2
Ap = PI * (7.7/2)^2
Ap = 46.5662 m^2
DL = Insulation + P-weight + Add-DL
DL = 0 + 0.4768 + 0
Page: 7/53
DL = 0.4768 kPa
Roof Loads per API-650 5.2.2
e.1b = DL + MAX(Sb , Lr) + (0.4 * Pe)
e.1b = 0.4768 + MAX(0 , 1) + (0.4 * 0)
e.1b = 1.4768 kPa
e.2b = DL + Pe + (0.4 * MAX(Sb , Lr))
e.2b = 0.4768 + 0 + (0.4 * MAX(0 , 1))
e.2b = 0.8768 kPa
T = MAX(e.1b , e.2b)
T = MAX(1.4768 , 0.8768)
T = 1.4768 kPa
e.1u = DL + MAX(Su , Lr) + (0.4 * Pe)
e.1u = 0.4768 + MAX(0 , 1) + (0.4 * 0)
e.1u = 1.4768 kPa
e.2u = DL + Pe + (0.4 * MAX(Su , Lr))
e.2u = 0.4768 + 0 + (0.4 * MAX(0 , 1))
e.2u = 0.8768 kPa
U = MAX(e.1u , e.2u)
U = MAX(1.4768 , 0.8768)
U = 1.4768 kPa
Lr-1 = MAX(T , U)
Lr-1 = MAX(1.4768 , 1.4768)
Lr-1 = 1.4768 kPa
Ra = PI * R * SQRT(R^2 + hr^2)
Ra = PI * 3.9098 * SQRT(3.9098^2 + 0.2444^2)
Ra = 481,165.4422 cm^2 or 48.1165 m^2
Roof Plates Weight = density * Ra * t-actual
Roof Plates Weight = 0.000007841 * 481,165.4422 * 6
Roof plates Weight = 22,201.2901 N
STRUCTURE CALCULATIONS
Area = Area per rafter = (m^2)
CRR = Center Ring Outside Radius = (mm)
D = Tank Nominal Size = (m)
G = Total Rafter Weight = (N)
h = rise = (m)
ID = Inside Diameter = (m)
l = Horizontal Rafter Length = (m)
l1 = Actual Rafter Length = (m)
n = Number of Rafters
OD = Outside Diameter = (m)
Pt = Pitch of Roof
q = Roof Design Load = (kPa)
QQ = Total Load per Rafter = (N)
R = Inside Radius = (m)
rft-S = Rafter Section Modulus = (cm^3)
Page: 8/53
rft-r = Rafter Radius of Gyration = (mm)
rft-wgt = Rafter Weight = (kg/m)
rft-A = Rafter Area = (mm^2)
RL = Roof Load = (kPa)
Sd = Allowable Stress = (pa)
T = Balanced Roof Load = (kPa)
Theta = Angle of Cone to the Horizontal = (degrees)
t-1 = Top Shell Thickness = (mm)
U = Unbalanced Roof Load = (kPa)
D = 7.7 m
OD = 7.716 m
ID = 7.7 m
IR = 3.85 m
t-1 = 6 mm
T = 1.4767 kPa
U = 1.4767 kPa
Pt = 0.75
n = 12
Rafter Type = IPE120
rft-S = 52.96 cm^3
rft-r = 14.5 mm
rft-wgt = 10.4 kg/m
rft-A = 1,320 mm^2
Sd = 160 MPa
CRR = 664.9707 mm
Compression Ring Material = A36
Compression-Ring-Sd = 160 MPa
Area-Crown = Area Crown Ring = m^2
Z-Crown = Section Modulus Crown Ring = m^3
phi = 1/2 of angle between rafters = (degrees)
S-actual-between-rafters = Total Compressive Stress = Pa
Calculated Variables
Fa = Sd = 160,000,000 Pa
Fbx = Sd = 160,000,000 Pa
Theta = ATAN (PI / 12) = 3.5763 (degrees)
RL = MAX(U , T)
RL = MAX(1.4767 , 1.4767)
RL = 1.4767 kPa
Area = PI * OD^2 / 4 / n
Area = PI * 7.716^2 / 4 / 12
Area = 3.8966 m^2
l = IR - CRR / 2 / 1000
l = 3.85 - 664.9707 / 2 / 1000
l = 3.5175 m
l1 = l / COS(Theta)
l1 = 3.5175 / COS(3.5763)
l1 = 3.5243 m
h = l * TAN(Theta)
h = 3.5175 * TAN(3.5763)
Page: 9/53
h = 0.2198 m
Rafter Weight Load (Uniform Load)
G = rft-wgt * l1
G = 10.4 * 3.5243
G = 36.6535 kg or 359.4483 N
H-GB = G / 2 *( l / h)
H-GB = 359.4483 / 2 *( 3.5175 / 0.2198)
H-GB = 2,875.5868 N
M-G-Max = G * l / 8
M-G-Max = 359.4483 * 3.5175 / 8
M-G-Max = 158.0456 N-m
N-G-Max = G * SIN(Theta) + H-GB * COS(Theta)
N-G-Max = 359.4483 * SIN(3.5763) + 2,875.5868 * COS(3.5763)
N-G-Max = 2,892.4086 N
Design Load (Dead Load + Live Load + Snow Load + Roof Plates)
q = RL = 1.4767 kPa or 1,476.7677 Pa
QQ = Area * q
QQ = 3.8966 * 1,476.7677
QQ = 5,730.6289 N
H-QB = (QQ / 3) * (l / h)
H-QB = (5,730.6289 / 3) * (3.5175 / 0.2198)
H-QB = 30,563.3543 N
M-Q-Max = 0.128 * QQ * l
M-Q-Max = 0.128 * 5,730.6289 * 3.5175
M-Q-Max = 2,580.169 N-m
N-Q-Max = QQ * SIN(Theta) + H-QB * COS(Theta)
N-Q-Max = 5,730.6289 * SIN(3.5763) + 30,563.3543 * COS(3.5763)
N-Q-Max = 30,861.3014 N
Hmax = H-GB + H-QB
Hmax = 2,875.5868 + 30,563.3543
Hmax = 33,438.9411 N
Mmax = M-G-Max + M-Q-Max
Mmax = 158.0456 + 2,580.169
Mmax = 2,738.2146 N-m
Section Modulus Reqd = Mmax * 1000 / Fbx
Section Modulus Reqd = 2,738.2146 * 1000 / 160
Section Modulus Reqd = 17,113.8418 mm^3 or 17.1138 cm^3
Nmax = N-G-Max + N-Q-Max
Nmax = 2,892.4086 + 30,861.3014
Nmax = 33,753.71 N
Area-Reqd = Nmax / Fa
Page: 10/53
Area-Reqd = 33,753.71 / 160
Area-Reqd = 210.9606 mm^2
fa = Nmax / rft-A
fa = 33,753.71 / 1,320
fa = 25,570,992.4717 Pa or 25.5709 MPa
fbx = Mmax / rft-S
fbx = 2,738.2146 / 0.00005296
fbx = 51,703,449.6267 Pa or 51.7034 MPa
Criteria = fa / Fa + fbx / Fbx
Criteria = 25,570,992.4717 / 160,000,000 + 51,703,449.6267 / 160,000,000
Criteria = 0.4829
Long & Garner - Guide to Storage Tanks & Equipment (Page 126)
Area-Crown = 0.0066 m^2 or 6,617 mm^2
Z-Crown = 0.0001 m^3 or 149,123.9932 mm^3
phi = 360/n/2
phi = 360/12/2
phi = 15 (degrees)
phi = 0.2617 (radians)
Force Between the Rafters
Mo = Hmax * CRR/2 * (1 / SIN(phi) - 1 / phi)
Mo = 33,438.9411 * 664.9707/2 * (1 / SIN(0.2617) - 1 / 0.2617)
Mo = 98,175.955 N-mm
No = Hmax / 2 * (1 / SIN(phi))
No = 33,438.9411 / 2 * (1 / SIN(0.2617))
No = 64,599.0738 N
S-actual-between-rafters = Mo / Z-Crown + No / Area-Crown
S-actual-between-rafters = 98,175.955 / 149,123.9932 + 64,599.0738 / 6,617
S-actual-between-rafters = 10.4209 MPa
Force-Between-Rafters-Test = S-Actual-Between-Rafters / Compression-Ring-Sd
Force-Between-Rafters-Test = 10.4209 / 160
Force-Between-Rafters-Test = 0.0651 <= 1.0 => Crown ring size is acceptable
Cross-Sectional-Area-Required = No / (Compression-Ring-Sd - Mo / Z-Crown)
Cross-Sectional-Area-Required = 64,599.0738 / (160 - 98.1759 / 149,123.9932)
Cross-Sectional-Area-Required = 405.4123 mm^2
Section-Modulus-Required = Mo / (Compression-Ring-Sd - No / Area-Crown)
Section-Modulus-Required = 98.1759 / (160 - 64,599.0738 / 6,617)
Section-Modulus-Required = 653.4721 mm^3
Forces at rafters
Mi = Hmax * CRR / 2 * (1 / phi - 1 / TAN(phi))
Mi = 33,438.9411 * 664.9707 / 2 * (1 / 0.2617 - 1 / TAN(0.2617))
Mi = 195,678.9132 N-mm
Ni = Hmax / 2 * (1 / TAN(phi))
Page: 11/53
Ni = 33,438.9411 / 2 * (1 / TAN(0.2617))
Ni = 62,397.9137 N
Total-Tensile-Stress = Mi / Z-Crown + Ni / A-Crown
Total-Tensile-Stress = 195,678.9132 / 149,123.9932 + 62,397.9137 / 6,617
Total-Tensile-Stress = 10.7421 Mpa
Forces-at-Rafters-Test = Total-Tensile-Stress / Sd
Forces-at-Rafters-Test = 10.7421 / 160
Forces-at-Rafters-Test = 0.0671 <= 1.0 => Crown ring size is acceptable
Cross-Sectional-Area-Required = Ni / (Sd - Mi / Z-Crown)
Cross-Sectional-Area-Required = 62,397.9137 / (160 - 195,678.9132 / 149,123.9932)
Cross-Sectional-Area-Required = 393.2117 mm^2
Section-Modulus-Required = Mi / (Sd - Ni / Area-Crown)
Section-Modulus-Required = 195,678.9132 / (160 - 62,397.9137 / 6,617)
Section-Modulus-Required = 1,299.5871 mm^3
TOP MEMBER DESIGN
CA_roof (Thickness of roof plate) = 1 mm
CA_shell (Thickness of shell plate) = 1.7 mm
D (Shell nominal diameter) = 7.708 m
ID (Shell inside diameter) = 7.7 m
Theta angle (Angle between the roof and a horizontal plane at the roof-to-shell junction) = 3.5763 deg
tc (Thickness of shell plate) = 6 mm
th (Thickness of roof plate) = 6 mm
Shell inside radius
Rc = ID / 2 = 7700.0 / 2 = 3850.0 mm
Shell nominal diameter (D) = 7.708 m
Length of normal to roof
R2 = Rc / SIN(Theta angle) = 3850.0 / SIN(3.5763) = 61720.1952 mm
Thickness of corroded roof plate
th_corroded = th - CA_roof = 6 - 1 = 5 mm
Thickness of corroded shell plate
tc_corroded = tc - CA_shell = 6 - 1.7 = 4.3 mm
CA_stiff > 0
Note: The calculation does not take into account the stiffener corrosion allowance, make sure to pick
a stiffener size that make up the difference in the thicknesses (corroded vs nominal).
Maximum width of participating roof API-650 Figure F-2
Wh = MIN((0.3 * SQRT((R2 * th_corroded))) , 300)
= MIN((0.3 * SQRT((61720.1952 * 5))) , 300)
= 166.6556 mm
Maximum width of participating shell API-650 Figure F-2
Wc = 0.6 * SQRT((Rc * tc_corroded)) = 0.6 * SQRT((3850.0 * 4.3)) = 77.1997 mm
Nominal weight of shell plates and framing
DLS = Ws + W_framing = 177316.3902 + 21705.7193 = 199022.1094 N
Nominal weight of roof plates and attached structural
Page: 12/53
DLR = Wr + W_structural = 22201.2901 + 7522.843 = 29724.1331 N
Compression Ring Detail b Properties
ID (Shell inside diameter) = 7.7 m
Size (Compression ring size) = l200x200x15
Wc (Length of contributing shell) = 77.1997 mm
Wh (Length of contributing roof) = 166.6556 mm
h (Top angle to top shell distance) = 4.3 mm
tc (Thickness of shell plate) = 4.3 mm
th (Thickness of roof plate) = 5 mm
Angle vertical leg size (l_vert) = 200 mm
Angle horizontal leg size (l_horz) = 200 mm
Angle thickness (t_angle) = 15.0 mm
Angle area (A_angle) = 5810.0 mm^2
Angle centroid (c_angle) = 54.8 mm
Angle moment of inertia (I_angle) = 2.209E7 mm^4
Length of contributing shell reduced
wc_reduced = Wc - h = 77.1997 - 4.3 = 72.8997 mm
Contributing shell moment of inertia
I_shell = (wc_reduced * (tc_corroded^3)) / 12
= (72.8997 * (4.3^3)) / 12
= 483.0033 mm^4
Contributing shell area
A_shell = wc_reduced * tc_corroded = 72.8997 * 4.3 = 313.4689 mm^2
Contributing roof area
A_roof = Wh * th_corroded = 166.6556 * 5 = 833.278 mm^2
Detail total area
A_detail = A_shell + A_roof + A_angle
= 313.4689 + 833.278 + 5810.0
= 6956.7469 mm^2
Find combined moment of inertia about shell inside axis with negative value toward center
Description
Variable
Equation
Value
Unit
Shell centroid
d_shell
tc_corroded / 2
2.1500
mm
Stiffener centroid
d_stiff
c_angle + tc_corroded
59.1000
mm
moment of inertia of
first body
I_1
I_angle + (A_angle * (d_stiff^2)) 42383226.1000 mm^4
moment of inertia of
second body
I_2
I_shell + (A_shell * (d_shell^2)) 1932.0132
mm^4
Total area
A_sum
A_angle + A_shell
6123.4689
mm^2
Sum of moments of
inertia's
I_sum
I_1 + I_2
42385158.1132 mm^4
Combined centroid
c_combined
((d_stiff * A_angle) + (d_shell *
56.1847
A_shell)) / (A_angle + A_shell)
Page: 13/53
mm
Combined moment of
I_sum - (A_sum *
I_combined
inertia
(c_combined^2))
23055112.4478 mm^4
Distance from neutral
e1
axis to edge 1 (inside)
c_combined
56.1847
mm
Distance from neutral
e2
axis to edge 2 (outside)
(tc_corroded + l_horz) - e1
148.1153
mm
Combined stiffener
shell section modulus
I_combined / MAX(e1 , e2)
155656.4698
mm^3
S
Roof Design Requirements
Appendix F Requirements
A_actual (Area resisting compressive force) = 6956.7469 mm^2
D (Tank nominal diameter) = 7.708 m
DLR (Nominal weight of roof plates and attached structural) = 29724.1331 N
DLS (Nominal weight of shell plates and framing) = 199022.1094 N
Fy (Minimum specified yield-strength of the materials in the roof-to-shell junction) = 205 MPa
ID (Tank inside diameter) = 7.7 m
Mw (Wind moment) = 388376.1052 N.m
P (Design pressure) = 7.5 kPa
Theta angle (Angle between the roof and a horizontal plane at the roof-to-shell junction) = 3.5763 deg
W_framing (Weight of framing supported by the shell and roof) = 21705.7193 N
W_structural (Weight of roof attached structural) = 7522.843 N
Wr (Roof plates weight) = 22201.2901 N
Ws (Shell plates weight) = 177316.3902 N
Uplift due to internal pressure API-650 F.1.2
P_uplift = P * pi * ((ID^2) / 4) = 7500.0 * pi * ((7.7^2) / 4) = 349246.9283 N
Weight of roof shell and attached-framing
W_total = Wr + Ws + W_framing
= 22201.2901 + 177316.3902 + 21705.7193
= 221223.3996 N
Net uplift due to internal pressure
Net_uplift = MAX((P_uplift - W_total) , 0)
= MAX((349246.9283 - 221223.3996) , 0)
= 128023.5287 N
P_uplift > W_total , Tank design should meet F.2 and F.7 requirements.
Required area API 650 F.5.1
A_F51 = ((200 * (D^2)) * (P - ((0.00127 * DLR) / (D^2)))) / (Fy * TAN(Theta angle))
= ((200 * (7.708^2)) * (7.5 - ((0.00127 * 29724.1331) / (7.708^2)))) / (205 * TAN(3.5763))
= 6366.4364 mm^2
A_actual >= A_F51 ==> Compression region actual cross sectional area is sufficient.
Maximum allowable internal pressure for the actual resisting area API 650 F.5.1
P_F51 = ((Fy * TAN(Theta angle) * A_actual) / (200 * (D^2))) + ((0.00127 * DLR) / (D^2))
= ((205 * TAN(3.5763) * 6956.7469) / (200 * (7.708^2))) + ((0.00127 * 29724.1331) / (7.708^2))
= 8.1365 kPa
Page: 14/53
Maximum allowable internal pressure
P_max_internal = MIN(P_std , P_F51) = MIN(18 , 8.1365) = 8.1365 kPa
SUMMARY OF ROOF RESULTS Back
Material = A283M-C
Structural Material = A36M
t-actual = 6 mm
t-required = 6 mm
t-calc = 5.4177 mm
P-Max-Internal = 8.1365 kPa
P-Max-External = 0 kPa
Roof Plates Weight = 22,201.2901 N
Weight of Rafters = 4,313.3802 N
Weight of Girders = 0 N
Weight of Columns = 0 N
Page: 15/53
SHELL COURSE DESIGN (Bottom course is #1) Back
API-650 ONE FOOT METHOD
D = Tank Nominal diameter (m) per API-650 5.6.1.1 Note 1
H = Max liquid level (m)
I-p = Design internal pressure (kPa)
L = Factor
I-p = 7.5 kPa
D = 7.7 m
H = 13.9 m
L = (500 * D (t-1 - Ca-1))^0.5
L = (500 * 7.7 (8 - 1.7))^0.5 = 155.7402
Course # 1
Ca-1 = Corrosion allowance per API-650 5.3.2 (mm)
G = Design specific gravity of the liquid to be stored
H' = Effective liquid head at design pressure (m)
hmax-1 = Max liquid level based on shell thickness (m)
JE = Joint efficiency
pmax-1 = Max pressure at design (kPa)
pmax-int-shell-1 = Max internal pressure at design (kPa)
Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa)
St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa)
t-1 = Shell actual thickness (mm)
t-calc-1 = Shell thickness design condition td (mm)
t-seismic-1 = See E.6.2.4 table in SEISMIC calculations.
t-test-1 = Shell thickness hydrostatic test condition (mm)
Material = A283M-C
Width = 1.8 m
Ca-1 = 1.7 mm
JE = 0.85
t-1 = 8 mm
Sd = 137 MPa
St = 154 MPa
Design Condition G = 1 (per API-650)
H' = H + (I-p/(9.8 * G)) (per API-650 F.2)
H' = 13.9 + (7.5 / (9.8 * 1))
H' = 14.6653 m
t-calc-1 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-1 (per API-650 5.6.3.2)
t-calc-1 = (4.9 * 7.7 * (14.6653 - 0.3) * 1)/137 + 1.7
t-calc-1 = 5.6562 mm
hmax-1 = Sd * (t-1 - CA-1)/(2.6 * D * G) + 1
hmax-1 = 137 * (8 - 1.7)/(2.6 * 7.7 * 1) + 1
hmax-1 = 23.1752 m
pmax-1 = (hmax-1 - H) * 9.8 * G
pmax-1 = (23.1752 - 14.6653) * 9.8 * 1
pmax-1 = 90.8972 kPa
pmax-int-shell-1 = pmax-1
Page: 16/53
pmax-int-shell-1 = 90.8972 kPa
Hydrostatic Test Condition G = 1
H' = H + (I-p/(9.8 * 1))
H' = 13.9 + (7.5/(9.8 * 1))
H' = 13.9008 m
t-test-1 = (* 4.9 D (H' - 0.3))/St
t-test-1 = (* 4.9 7.7 (13.9008 - 0.3))/154
t-test-1 = 3.3322 mm
Course # 2
Ca-2 = Corrosion allowance per API-650 5.3.2 (mm)
G = Design specific gravity of the liquid to be stored
H' = Effective liquid head at design pressure (m)
hmax-2 = Max liquid level based on shell thickness (m)
JE = Joint efficiency
pmax-2 = Max pressure at design (kPa)
pmax-int-shell-2 = Max internal pressure at design (kPa)
Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa)
St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa)
t-2 = Shell actual thickness (mm)
t-calc-2 = Shell thickness design condition td (mm)
t-seismic-2 = See E.6.2.4 table in SEISMIC calculations.
t-test-2 = Shell thickness hydrostatic test condition (mm)
Material = A283M-C
Width = 1.8 m
Ca-2 = 1.7 mm
JE = 0.85
t-2 = 8 mm
Sd = 137 MPa
St = 154 MPa
Design Condition G = 1 (per API-650)
H' = H + (I-p/(9.8 * G)) (per API-650 F.2)
H' = 12.1 + (7.5 / (9.8 * 1))
H' = 12.8653 m
t-calc-2 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-2 (per API-650 5.6.3.2)
t-calc-2 = (4.9 * 7.7 * (12.8653 - 0.3) * 1)/137 + 1.7
t-calc-2 = 5.1605 mm
hmax-2 = Sd * (t-2 - CA-2)/(2.6 * D * G) + 1
hmax-2 = 137 * (8 - 1.7)/(2.6 * 7.7 * 1) + 1
hmax-2 = 23.1752 m
pmax-2 = (hmax-2 - H) * 9.8 * G
pmax-2 = (23.1752 - 12.8653) * 9.8 * 1
pmax-2 = 108.5372 kPa
pmax-int-shell-2 = MIN(pmax-int-shell-1 pmax-2)
pmax-int-shell-2 = MIN(90.8972 108.5372)
pmax-int-shell-2 = 90.8972 kPa
Page: 17/53
Hydrostatic Test Condition G = 1
H' = H + (I-p/(9.8 * 1))
H' = 12.1 + (7.5/(9.8 * 1))
H' = 12.1008 m
t-test-2 = (* 4.9 D (H' - 0.3))/St
t-test-2 = (* 4.9 7.7 (12.1008 - 0.3))/154
t-test-2 = 2.8912 mm
Course # 3
Ca-3 = Corrosion allowance per API-650 5.3.2 (mm)
G = Design specific gravity of the liquid to be stored
H' = Effective liquid head at design pressure (m)
hmax-3 = Max liquid level based on shell thickness (m)
JE = Joint efficiency
pmax-3 = Max pressure at design (kPa)
pmax-int-shell-3 = Max internal pressure at design (kPa)
Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa)
St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa)
t-3 = Shell actual thickness (mm)
t-calc-3 = Shell thickness design condition td (mm)
t-seismic-3 = See E.6.2.4 table in SEISMIC calculations.
t-test-3 = Shell thickness hydrostatic test condition (mm)
Material = A283M-C
Width = 1.8 m
Ca-3 = 1.7 mm
JE = 0.85
t-3 = 6 mm
Sd = 137 MPa
St = 154 MPa
Design Condition G = 1 (per API-650)
H' = H + (I-p/(9.8 * G)) (per API-650 F.2)
H' = 10.3 + (7.5 / (9.8 * 1))
H' = 11.0653 m
t-calc-3 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-3 (per API-650 5.6.3.2)
t-calc-3 = (4.9 * 7.7 * (11.0653 - 0.3) * 1)/137 + 1.7
t-calc-3 = 4.6648 mm
hmax-3 = Sd * (t-3 - CA-3)/(2.6 * D * G) + 1
hmax-3 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1
hmax-3 = 15.9148 m
pmax-3 = (hmax-3 - H) * 9.8 * G
pmax-3 = (15.9148 - 11.0653) * 9.8 * 1
pmax-3 = 55.0248 kPa
pmax-int-shell-3 = MIN(pmax-int-shell-2 pmax-3)
pmax-int-shell-3 = MIN(90.8972 55.0248)
pmax-int-shell-3 = 55.0248 kPa
Hydrostatic Test Condition G = 1
Page: 18/53
H' = H + (I-p/(9.8 * 1))
H' = 10.3 + (7.5/(9.8 * 1))
H' = 10.3008 m
t-test-3 = (* 4.9 D (H' - 0.3))/St
t-test-3 = (* 4.9 7.7 (10.3008 - 0.3))/154
t-test-3 = 2.4502 mm
Course # 4
Ca-4 = Corrosion allowance per API-650 5.3.2 (mm)
G = Design specific gravity of the liquid to be stored
H' = Effective liquid head at design pressure (m)
hmax-4 = Max liquid level based on shell thickness (m)
JE = Joint efficiency
pmax-4 = Max pressure at design (kPa)
pmax-int-shell-4 = Max internal pressure at design (kPa)
Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa)
St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa)
t-4 = Shell actual thickness (mm)
t-calc-4 = Shell thickness design condition td (mm)
t-seismic-4 = See E.6.2.4 table in SEISMIC calculations.
t-test-4 = Shell thickness hydrostatic test condition (mm)
Material = A283M-C
Width = 1.8 m
Ca-4 = 1.7 mm
JE = 0.85
t-4 = 6 mm
Sd = 137 MPa
St = 154 MPa
Design Condition G = 1 (per API-650)
H' = H + (I-p/(9.8 * G)) (per API-650 F.2)
H' = 8.5 + (7.5 / (9.8 * 1))
H' = 9.2653 m
t-calc-4 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-4 (per API-650 5.6.3.2)
t-calc-4 = (4.9 * 7.7 * (9.2653 - 0.3) * 1)/137 + 1.7
t-calc-4 = 4.1691 mm
hmax-4 = Sd * (t-4 - CA-4)/(2.6 * D * G) + 1
hmax-4 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1
hmax-4 = 15.9148 m
pmax-4 = (hmax-4 - H) * 9.8 * G
pmax-4 = (15.9148 - 9.2653) * 9.8 * 1
pmax-4 = 72.6648 kPa
pmax-int-shell-4 = MIN(pmax-int-shell-3 pmax-4)
pmax-int-shell-4 = MIN(55.0248 72.6648)
pmax-int-shell-4 = 55.0248 kPa
Hydrostatic Test Condition G = 1
H' = H + (I-p/(9.8 * 1))
H' = 8.5 + (7.5/(9.8 * 1))
Page: 19/53
H' = 8.5008 m
t-test-4 = (* 4.9 D (H' - 0.3))/St
t-test-4 = (* 4.9 7.7 (8.5008 - 0.3))/154
t-test-4 = 2.0092 mm
Course # 5
Ca-5 = Corrosion allowance per API-650 5.3.2 (mm)
G = Design specific gravity of the liquid to be stored
H' = Effective liquid head at design pressure (m)
hmax-5 = Max liquid level based on shell thickness (m)
JE = Joint efficiency
pmax-5 = Max pressure at design (kPa)
pmax-int-shell-5 = Max internal pressure at design (kPa)
Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa)
St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa)
t-5 = Shell actual thickness (mm)
t-calc-5 = Shell thickness design condition td (mm)
t-seismic-5 = See E.6.2.4 table in SEISMIC calculations.
t-test-5 = Shell thickness hydrostatic test condition (mm)
Material = A283M-C
Width = 1.5 m
Ca-5 = 1.7 mm
JE = 0.85
t-5 = 6 mm
Sd = 137 MPa
St = 154 MPa
Design Condition G = 1 (per API-650)
H' = H + (I-p/(9.8 * G)) (per API-650 F.2)
H' = 6.7 + (7.5 / (9.8 * 1))
H' = 7.4653 m
t-calc-5 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-5 (per API-650 5.6.3.2)
t-calc-5 = (4.9 * 7.7 * (7.4653 - 0.3) * 1)/137 + 1.7
t-calc-5 = 3.6733 mm
hmax-5 = Sd * (t-5 - CA-5)/(2.6 * D * G) + 1
hmax-5 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1
hmax-5 = 15.9148 m
pmax-5 = (hmax-5 - H) * 9.8 * G
pmax-5 = (15.9148 - 7.4653) * 9.8 * 1
pmax-5 = 90.3048 kPa
pmax-int-shell-5 = MIN(pmax-int-shell-4 pmax-5)
pmax-int-shell-5 = MIN(55.0248 90.3048)
pmax-int-shell-5 = 55.0248 kPa
Hydrostatic Test Condition G = 1
H' = H + (I-p/(9.8 * 1))
H' = 6.7 + (7.5/(9.8 * 1))
H' = 6.7008 m
Page: 20/53
t-test-5 = (* 4.9 D (H' - 0.3))/St
t-test-5 = (* 4.9 7.7 (6.7008 - 0.3))/154
t-test-5 = 1.5682 mm
Course # 6
Ca-6 = Corrosion allowance per API-650 5.3.2 (mm)
G = Design specific gravity of the liquid to be stored
H' = Effective liquid head at design pressure (m)
hmax-6 = Max liquid level based on shell thickness (m)
JE = Joint efficiency
pmax-6 = Max pressure at design (kPa)
pmax-int-shell-6 = Max internal pressure at design (kPa)
Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa)
St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa)
t-6 = Shell actual thickness (mm)
t-calc-6 = Shell thickness design condition td (mm)
t-seismic-6 = See E.6.2.4 table in SEISMIC calculations.
t-test-6 = Shell thickness hydrostatic test condition (mm)
Material = A283M-C
Width = 1.5 m
Ca-6 = 1.7 mm
JE = 0.85
t-6 = 6 mm
Sd = 137 MPa
St = 154 MPa
Design Condition G = 1 (per API-650)
H' = H + (I-p/(9.8 * G)) (per API-650 F.2)
H' = 5.2 + (7.5 / (9.8 * 1))
H' = 5.9653 m
t-calc-6 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-6 (per API-650 5.6.3.2)
t-calc-6 = (4.9 * 7.7 * (5.9653 - 0.3) * 1)/137 + 1.7
t-calc-6 = 3.2602 mm
hmax-6 = Sd * (t-6 - CA-6)/(2.6 * D * G) + 1
hmax-6 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1
hmax-6 = 15.9148 m
pmax-6 = (hmax-6 - H) * 9.8 * G
pmax-6 = (15.9148 - 5.9653) * 9.8 * 1
pmax-6 = 105.0048 kPa
pmax-int-shell-6 = MIN(pmax-int-shell-5 pmax-6)
pmax-int-shell-6 = MIN(55.0248 105.0048)
pmax-int-shell-6 = 55.0248 kPa
Hydrostatic Test Condition G = 1
H' = H + (I-p/(9.8 * 1))
H' = 5.2 + (7.5/(9.8 * 1))
H' = 5.2008 m
t-test-6 = (* 4.9 D (H' - 0.3))/St
t-test-6 = (* 4.9 7.7 (5.2008 - 0.3))/154
Page: 21/53
t-test-6 = 1.2007 mm
Course # 7
Ca-7 = Corrosion allowance per API-650 5.3.2 (mm)
G = Design specific gravity of the liquid to be stored
H' = Effective liquid head at design pressure (m)
hmax-7 = Max liquid level based on shell thickness (m)
JE = Joint efficiency
pmax-7 = Max pressure at design (kPa)
pmax-int-shell-7 = Max internal pressure at design (kPa)
Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa)
St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa)
t-7 = Shell actual thickness (mm)
t-calc-7 = Shell thickness design condition td (mm)
t-seismic-7 = See E.6.2.4 table in SEISMIC calculations.
t-test-7 = Shell thickness hydrostatic test condition (mm)
Material = A283M-C
Width = 1.5 m
Ca-7 = 1.7 mm
JE = 0.85
t-7 = 6 mm
Sd = 137 MPa
St = 154 MPa
Design Condition G = 1 (per API-650)
H' = H + (I-p/(9.8 * G)) (per API-650 F.2)
H' = 3.7 + (7.5 / (9.8 * 1))
H' = 4.4653 m
t-calc-7 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-7 (per API-650 5.6.3.2)
t-calc-7 = (4.9 * 7.7 * (4.4653 - 0.3) * 1)/137 + 1.7
t-calc-7 = 2.8471 mm
hmax-7 = Sd * (t-7 - CA-7)/(2.6 * D * G) + 1
hmax-7 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1
hmax-7 = 15.9148 m
pmax-7 = (hmax-7 - H) * 9.8 * G
pmax-7 = (15.9148 - 4.4653) * 9.8 * 1
pmax-7 = 119.7048 kPa
pmax-int-shell-7 = MIN(pmax-int-shell-6 pmax-7)
pmax-int-shell-7 = MIN(55.0248 119.7048)
pmax-int-shell-7 = 55.0248 kPa
Hydrostatic Test Condition G = 1
H' = H + (I-p/(9.8 * 1))
H' = 3.7 + (7.5/(9.8 * 1))
H' = 3.7008 m
t-test-7 = (* 4.9 D (H' - 0.3))/St
t-test-7 = (* 4.9 7.7 (3.7008 - 0.3))/154
t-test-7 = 0.8332 mm
Page: 22/53
Course # 8
Ca-8 = Corrosion allowance per API-650 5.3.2 (mm)
G = Design specific gravity of the liquid to be stored
H' = Effective liquid head at design pressure (m)
hmax-8 = Max liquid level based on shell thickness (m)
JE = Joint efficiency
pmax-8 = Max pressure at design (kPa)
pmax-int-shell-8 = Max internal pressure at design (kPa)
Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa)
St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa)
t-8 = Shell actual thickness (mm)
t-calc-8 = Shell thickness design condition td (mm)
t-seismic-8 = See E.6.2.4 table in SEISMIC calculations.
t-test-8 = Shell thickness hydrostatic test condition (mm)
Material = A283M-C
Width = 1.5 m
Ca-8 = 1.7 mm
JE = 0.85
t-8 = 6 mm
Sd = 137 MPa
St = 154 MPa
Design Condition G = 1 (per API-650)
H' = H + (I-p/(9.8 * G)) (per API-650 F.2)
H' = 2.2 + (7.5 / (9.8 * 1))
H' = 2.9653 m
t-calc-8 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-8 (per API-650 5.6.3.2)
t-calc-8 = (4.9 * 7.7 * (2.9653 - 0.3) * 1)/137 + 1.7
t-calc-8 = 2.434 mm
hmax-8 = Sd * (t-8 - CA-8)/(2.6 * D * G) + 1
hmax-8 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1
hmax-8 = 15.9148 m
pmax-8 = (hmax-8 - H) * 9.8 * G
pmax-8 = (15.9148 - 2.9653) * 9.8 * 1
pmax-8 = 134.4048 kPa
pmax-int-shell-8 = MIN(pmax-int-shell-7 pmax-8)
pmax-int-shell-8 = MIN(55.0248 134.4048)
pmax-int-shell-8 = 55.0248 kPa
Hydrostatic Test Condition G = 1
H' = H + (I-p/(9.8 * 1))
H' = 2.2 + (7.5/(9.8 * 1))
H' = 2.2008 m
t-test-8 = (* 4.9 D (H' - 0.3))/St
t-test-8 = (* 4.9 7.7 (2.2008 - 0.3))/154
t-test-8 = 0.4657 mm
Course # 9
Page: 23/53
Ca-9 = Corrosion allowance per API-650 5.3.2 (mm)
G = Design specific gravity of the liquid to be stored
H' = Effective liquid head at design pressure (m)
hmax-9 = Max liquid level based on shell thickness (m)
JE = Joint efficiency
pmax-9 = Max pressure at design (kPa)
pmax-int-shell-9 = Max internal pressure at design (kPa)
Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa)
St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa)
t-9 = Shell actual thickness (mm)
t-calc-9 = Shell thickness design condition td (mm)
t-seismic-9 = See E.6.2.4 table in SEISMIC calculations.
t-test-9 = Shell thickness hydrostatic test condition (mm)
Material = A283M-C
Width = 1.5 m
Ca-9 = 1.7 mm
JE = 0.85
t-9 = 6 mm
Sd = 137 MPa
St = 154 MPa
Design Condition G = 1 (per API-650)
H' = H + (I-p/(9.8 * G)) (per API-650 F.2)
H' = 0.7 + (7.5 / (9.8 * 1))
H' = 1.4653 m
t-calc-9 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-9 (per API-650 5.6.3.2)
t-calc-9 = (4.9 * 7.7 * (1.4653 - 0.3) * 1)/137 + 1.7
t-calc-9 = 2.0209 mm
hmax-9 = Sd * (t-9 - CA-9)/(2.6 * D * G) + 1
hmax-9 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1
hmax-9 = 15.9148 m
pmax-9 = (hmax-9 - H) * 9.8 * G
pmax-9 = (15.9148 - 1.4653) * 9.8 * 1
pmax-9 = 149.1048 kPa
pmax-int-shell-9 = MIN(pmax-int-shell-8 pmax-9)
pmax-int-shell-9 = MIN(55.0248 149.1048)
pmax-int-shell-9 = 55.0248 kPa
Hydrostatic Test Condition G = 1
H' = H + (I-p/(9.8 * 1))
H' = 0.7 + (7.5/(9.8 * 1))
H' = 0.7008 m
t-test-9 = (* 4.9 D (H' - 0.3))/St
t-test-9 = (* 4.9 7.7 (0.7008 - 0.3))/154
t-test-9 = 0.0982 mm
SUMMARY OF SHELL RESULTS Back
t-min-Seismic = See API-650 E.6.1.4, table in SEISMIC calculations.
Page: 24/53
Shell API-650 Summary (Bottom is 1)
Shell Width
CA
Material
# (mm)
(mm)
Min
t-min
Tensile
t-min
t-min
Yield
Sd
St Weight Weight
t-Des t-Test
ExtJE
Strength
Erection
Seismic
Strength
(MPa) (MPa)
(N) CA (N)
(mm) (mm)
Pe
(MPa)
(mm)
(mm)
(MPa)
(mm)
1
1800
A283MC
1.7 0.85
205
380
137
154 26,759 21,078
6 5.6562 3.3322
4.384
2
1800
A283MC
1.7 0.85
205
380
137
154 26,759 21,078
5 5.1605 2.8912
3
1800
A283MC
1.7 0.85
205
380
137
154 20,075 14,390
4
1800
A283MC
1.7 0.85
205
380
137
5
1500
A283MC
1.7 0.85
205
380
6
1500
A283MC
1.7 0.85
205
7
1500
A283MC
1.7 0.85
8
1500
A283MC
9
1500
A283MC
6
8
OK
4.0317
NA 5.1605
8
OK
5 4.6648 2.4502
3.5017
NA
5
6
OK
154 20,075 14,390
5 4.1691 2.0092
3.1821
NA
5
6
OK
137
154 16,729 11,991
5 3.6733 1.5682
2.8632
NA
5
6
OK
380
137
154 16,729 11,991
5 3.2602 1.2007
2.5977
NA
5
6
OK
205
380
137
154 16,729 11,991
5 2.8471 0.8332
2.3284
NA
5
6
OK
1.7 0.85
205
380
137
154 16,729 11,991
5 2.434 0.4657
2.0551
NA
5
6
OK
1.7 0.85
205
380
137
154 16,729 11,991
5 2.0209 0.0982
1.7851
NA
5
6
OK
Total Weight = 177,316.3901 N
INTERMEDIATE STIFFENER CALCULATIONS PER API-650 Section 5.9.7
D = Nominal diameter of the tank shell (m)
Hu = Vertical Distance Between the Intermediate Stiffener (Per API-650 5.9.7) (m)
L_act = Actual Transform Height Spacing between Stiffeners (m)
L_0 = Uniform Maximum Transform Height Spacing between Stiffineres (m)
V = Design wind speed (km/h)
Wtr = Transposed width of each shell course (m)
Zi = Required Intermediate Stiffener Section Modulus (per API-650 5.9.6.1) (cm^3)
Zi-actual = Actual Top Comp Ring Section Modulus (cm^3)
D = 7.7 m
V = 120 km/h
ME = 1
Hu = ME * 9.47 * tsmin * (SQRT (tsmin / D)^3) * (190 / V)^2
Hu = 1 * 9.47 * 6 * (SQRT (6 / 7.7)^3) * (190 / 120)^2
Hu = 97.9798 m (Maximum Height of Unstiffened Shell)
Transforming courses (1) to (9)
Wtr = Course-width * (SQRT (t-uniform / t-course)^5)
Wtr-1 = 1.8 * (SQRT (6 / 8)^5) = 0.8769 m
Wtr-2 = 1.8 * (SQRT (6 / 8)^5) = 0.8769 m
Wtr-3 = 1.8 * (SQRT (6 / 6)^5) = 1.8 m
Wtr-4 = 1.8 * (SQRT (6 / 6)^5) = 1.8 m
Wtr-5 = 1.5 * (SQRT (6 / 6)^5) = 1.5 m
Wtr-6 = 1.5 * (SQRT (6 / 6)^5) = 1.5 m
Wtr-7 = 1.5 * (SQRT (6 / 6)^5) = 1.5 m
Wtr-8 = 1.5 * (SQRT (6 / 6)^5) = 1.5 m
Page: 25/53
NA
tt-min
Actual Status
(mm)
(mm)
Wtr-9 = 1.5 * (SQRT (6 / 6)^5) = 1.5 m
Wtr = SUM(Wtr-n)
Wtr = 12.8537 m
For uniformly spaced stiffeners
L_0 = Hts/# of Stiffeners + 1
L_0 = 12.8537/(2 + 1)
L_0 = 4.2846 m
Actual Stiffener Elevations:
Stiffener
Size Elevation (m) Transformed Elevation (m)
1 l76x76x12.7
8
6.1537
2 l76x76x12.7
11
9.1537
L_act = Max((Wrt - Elev-trans-n) , (Elev-trans-n - Elev-trans-n-1) , Elev-trans-n-1)
L_act = Max((12.8537 - 9.1537) , (9.1537 - 6.1537) , 6.1537)
L_act = 6.1537 m
Number of Intermediate Stiffeners Sufficient Since Hu >= L_act
Required section modulus:
Size
Spacing below (m)
(transformed height)
1 l76x76x12.7
2 l76x76x12.7
Stiffener
Spacing above (m)
(transformed height)
Average spacing (m)
(transformed height)
Required Zi (cm3)
(D^2*H/17 )*(V/190)^2
6.1537
3
4.5768
6.3673
3
3.7
3.35
4.6605
SUMMARY OF SHELL STIFFENING RESULTS
Stiffener
Size Elevation (m) Z-Req'd (cm3) Z-Actual (cm3) Weight (N)
1 l76x76x12.7
8
6.3673
48.5332 3,349.1878
2 l76x76x12.7
11
4.6605
48.5332 3,349.1878
FLAT BOTTOM: NON ANNULAR PLATE DESIGN Back
Ba = Area of bottom (cm^2)
Bottom-OD = Bottom diameter (m)
c = Factor
ca-1 = Bottom (1st) shell course corrosion allowance (mm)
Ca-bottom = Bottom corrosion allowance (mm)
D-bottom = Density of bottom (kg/mm3)
G = Design specific gravity of the liquid to be stored
H = Max liquid level (m)
H' = Effective liquid head at design pressure (m)
JE = Bottom joint efficiency
S = Maximum Stress in first shell course per API 650 Table 5.1.a
S1 = Product stress in the first shell course per API 650 Table 5.1.a
S2 = Hydrostatic test stress in the first shell course per API 650 Table 5.1.a
t-1 = Bottom (1st) shell course thickness (mm)
Page: 26/53
t-actual = Actual bottom thickness (mm)
t-calc = Minimum nominal bottom plates thickness per API-650 5.4.1 (mm)
t-min = Minimum nominal bottom plates thickness per API-650 5.4.1 (mm)
t-test-1 = Bottom (1st) shell course test thickness (mm)
t-vac = Vacuum calculations per ASME section VIII Div. 1 (mm)
td-1 = Bottom (1st) shell course design thickness (mm)
Material = A283M-C
t-actual = 8 mm
t-min = 6.0 + Ca-bottom
t-min = 6.0 + 1.7
t-min = 7.7 mm
t-calc = t-min
t-calc = 7.7 mm
Calculation of Hydrostatic Test Stress & Product Stress (per API-650 Section 5.5.1)
Bottom-OD = 7.816 m
JE = 0.85
D-bottom = 0.00000784 kg/mm3
t-1 = 8 mm
ca-1 = 1.7 mm
G=1
H = 13.9 m
H' = 14.6653 m
St = 154 MPa
Sd = 137 MPa
Ca-bottom = 1.7 mm
Product stress in first shell course
S1 = ((td-1 - ca-1) / (t-1 - ca-1)) * Sd
S1 = ((5.6562 - 1.7) / (8 - 1.7)) * 137
S1 = 86.0322 MPa
Hydrostatic test stress in first shell course
S2 = (t-test-1 / t-1) * St
S2 = (3.3322 / 8) * 154
S2 = 64.1446 MPa
S = Max (S1, S2)
S = Max (86.0322 , 64.1446)
S = 86.0322 MPa
ABS(E-p) < P-btm Then there is no uplift
SUMMARY OF BOTTOM RESULTS Back
Material = A283M-C
t-actual = 8 mm
t-req = 7.7 mm
NET UPLIFT DUE TO INTERNAL PRESSURE
Page: 27/53
Net-Uplift = 128,023.5287 N, (See roof report for calculations)
WIND MOMENT (Per API-650 SECTION 5.11) Back
A = Area resisting the compressive force, as illustrated in Figure F.1
P-F41 = Design pressure determined in F.4.1
P-v = Internal pressure
Wind Velocity per API-650 ASCE 7-05
V_entered = 120 kph
I=1
Vs (Wind Velocity) = SQRT(I) * V_entered = 120 kph
Vf = (Vs / 190)^2
Vf = (120 / 190)^2
Vf (Velocity Factor) = 0.3989
PWS = 0.86 * Vf
PWS = 0.343 kPa
PWR = 1.44 * Vf
PWR = 0.5744 kPa
API-650 5.2.1.k Uplift Check
P-F41 = (A * Fy * TAN(Theta))/(200 * D^2) + (0.00127 * DLR)/D^2
P-F41 = (6956.75 * 205 * TAN(3.5763))/(200 * 7.7^2) + ((0.00127 * 29724) / 7.7^2)
P-F41 = 8.1534 kPa
Wind-Uplift = MIN(PWR , (1.6 * P-F41 - Pv))
Wind-Uplift = MIN(0.5744 , 5.5455)
Wind-Uplift = 0.5744 kPa
Ap-Vert (Vertical Projected Area of Roof) = 0.9264 m^2
Horizontal Projected Area of Roof (Per API-650 5.2.1.f)
Xw (Moment Arm of UPLIFT wind force on roof) = 3.85 m
Ap (Projected Area of roof for wind moment) = 46.5663 m^2
M-roof (Moment Due to Wind Force on Roof) = Wind-Uplift * Ap * Xw
M-roof = (574.4044 * 46.5663 * 3.85)
M-roof = 102,979 N-m
Xs (Height from bottom to the Shell's center of gravity) = Shell Height/2
Xs = (14.7/2)
Xs = 7.35 m
As (Projected Area of Shell) = Shell Height * (D + 2 * t-ins)
As = 14.7 * (7.7 + 2 * 0)
As = 113.19 m^2
M-Shell (Moment Due to Wind Force on Shell) = (PWS * As * (Shell Height / 2))
M-Shell = (0.343 * 113.19 * (14.7 / 2))
Page: 28/53
M-Shell = 285,397 N-m
Mw (Wind moment) = M-roof + M-shell
Mw = 102,979 + 285,397
Mw = 388,376.1052 N-m
RESISTANCE TO OVERTURNING (per API-650 5.11.2)
DLR = Nominal weight of roof plate plus weight of roof plates overlap plus any attached structural.
DLS = Nominal weight of the shell and any framing (but not roof plates) support by the shell and roof.
F-friction = Maximum of 40% of weight of tank
MDL = Moment about the shell-to-bottom joint from the nominal weight of the shell
MDLR = Moment about the shell-to-bottom joint from the nominal weight of the roof plate plus any
attached structural.
MF = Stabilizing moment due to bottom plate and liquid weight
MPi = Destabilizing moment about the shell-to-bottom joint from design pressure
Mw = Destabilizing wind moment
tb = Bottom plate thickness less C.A.
wl = Circumferential loading of contents along shell-to-bottom joint
An unanchored tank must meet these three criteria:
Mw = 388,376 m-N
DLS = 199,022.1094 N
DLR = 29,724.1331 N
MPi = P * (Pi * D^2 / 4) * (D / 2)
MPi = 7.5 * (3.1416 * 7.7^2 / 4) * (7.7 / 2)
MPi = 1,344.6007 m-N
MDL = DLS * (D/2)
MDL = 199,022.1094 * 7.7/2
MDL = 766,235 N-m
MDLR = DLR * (D/2)
MDLR = 29,724.1331 * 7.7/2
MDLR = 114,438 N-m
tb = 6.3 mm
wl = (min [59 * tb * SQRT(fy-btm * H-liq)] [140.8 * H-liq * D])
wl = (min [59 * 6.3 * SQRT(205 * 13.9)] [140.8 * 13.9 * 7.7])
wl = 15,069.824 N/m
MF = (D/2) * wl * Pi * D
MF = 3.85 * 15,069.824 * 3.1416 * 7.7
MF = 1,403,491 m-N
Criteria 1
0.6 * Mw + MPi < MDL / 1.5 + MDLR
0.6 * 388,376 + 1,344.6007 < 766,235 / 1.5 + 114,438
Since 234,370 < 625,261, Tank is stable
Criteria 2
Page: 29/53
Mw + Fp * MPi < (MDL + MF) / 2 + MDLR
388,376 + 0.4 * 1,344.6007 < (766,235 + 1,403,491) / 2 + 114,438
Since 388,914 < 1,199,301, Tank is stable
Criteria 3
M-shell + Fp * Mpi < MDL /1.5 + MDLR
285,396.827 + 0.4 * 1,344.6007 < 766,235 / 1.5 + 114,438
Since 285,935 < 625,261, Tank is stable
RESISTANCE TO SLIDING (per API-650 5.11.4)
F-wind = Vf * 18 * As
F-wind = 0.3989 * 18 * 113.19
F-wind = 37,665 N
F-friction = 0.4 * [(W-roof-corroded * g) + (W-shell-corroded * g) + (W-btm-corroded * g) + (W-roofstruct * g)]
F-friction = 0.4 * [(1,886.5846 * 9.8) + (13,348 * 9.8) + (2,370.3441 * 9.8) + (2,963.9383 * 9.8)]
F-friction = 80,684 N
No anchorage needed to resist sliding since
F-friction > F-wind
Anchorage Requirement
Tank must be anchored by The design load, per API 650 Table E-6
Page: 30/53
Back
SITE GROUND MOTION CALCULATIONS
Anchorage_System (Anchorage System) = mechanically anchored
D (Nominal Tank Diameter) = 7.7 m
Fa (Site Acceleration Coefficient) = 2.5
Fv (Site Velocity Coefficient) = 3.5
H (Maximum Design Product Level) = 13.9 m
I (Importance Factor) = 1.25
K (Spectral Acceleration Adjustment Coefficient) = 1.5
Q (MCE to Design Level Scale Factor) = 0.6667
Rwc (Convective Force Reduction Factor) = 2
Rwi (Impulsive Force Reduction Factor) = 4
S1 (Spectral Response Acceleration at a Period of One Second) = 0.05
Seismic_Site_Class (Seismic Site Class) = seismic site class e
Seismic_Use_Group (Seismic Use Group) = seismic use group ii
Ss (Spectral Response Acceleration Short Period) = 0.12
TL (Regional Dependent Transistion Period for Longer Period Ground Motion) = 4 sec
Design Spectral Response Acceleration at Short Period API 650 Sections E.4.6.1 and E.2.2
SDS = Q * Fa * Ss = 0.6667 * 2.5 * 0.12 = 0.2
Design Spectral Response Acceleration at a Period of One Second API 650 Sections E.4.6.1 and
E.2.2
SD1 = Q * Fv * S1 = 0.6667 * 3.5 * 0.05 = 0.1167
Sloshing Coefficient API 650 Section E.4.5.2
Ks = 0.578 / SQRT(TANH(((3.68 * Liq_max) / D)))
= 0.578 / SQRT(TANH(((3.68 * 13.9) / 7.7)))
= 0.578
Convective Natural Period API 650 Section E.4.5.2
Tc = 1.8 * Ks * SQRT(D) = 1.8 * 0.578 * SQRT(7.7) = 2.887 sec
Impulsive Design Response Spectrum Acceleration Coefficient API 650 Sections E.4.6.1
Ai = SDS * (I / Rwi) = 0.2 * (1.25 / 4) = 0.0625
API 650 Sections E.4.6.1
Ai = MAX(Ai , 0.007) = MAX(0.0625 , 0.007) = 0.0625
Tc <= TL
Convective Design Response Spectrum Acceleration Coefficient API 650 Sections E.4.6.1
Ac = K * SD1 * (1 / Tc) * (I / Rwc)
= 1.5 * 0.1167 * (1 / 2.887) * (1.25 / 2)
= 0.0379
Ac = MIN(Ac , Ai) = MIN(0.0379 , 0.0625) = 0.0379
Vertical Ground Acceleration Coefficient API 650 Section E.6.1.3 and E.2.2
Av = (2 / 3) * 0.7 * SDS = (2 / 3) * 0.7 * 0.2 = 0.0933
Vertical Ground Acceleration Coefficient Specified by user (Av) = 0.0933
Page: 31/53
SEISMIC CALCULATIONS Back
< Mapped ASCE7 Method >
Ac = Convective spectral acceleration parameter
Ai = Impulsive spectral acceleration parameter
Av = Vertical Earthquake Acceleration Coefficient
Ci = Coefficient for impulsive period of tank system (Fig. E-1)
D/H = Ratio of Tank Diameter to Design Liquid Level
Density = Density of tank product (SG * 62.42786)
Fc = Allowable longitudinal shell-membrane compressive stress
Fty = Minimum specified yield strength of shell course
Fy = Minimum yield strength of bottom annulus
Ge = Effective specific gravity including vertical seismic effects
I = Importance factor defined by Seismic Use Group
k = Coefficient to adjust spectral acceleration from 5% - 0.5% damping
L = Required Annular Ring Width
Ls = Actual Annular Plate Width
Mrw = Ringwall moment-portion of the total overturning moment that acts at the base of the tank shell
perimeter
Ms = Slab moment (used for slab and pile cap design)
Pa = Anchorage chair design load
Pab = Anchor seismic design load
Q = Scaling factor from the MCE to design level spectral accelerations
RCG = Height from Top of Shell to Roof Center of Gravity
Rwc = Force reduction factor for the convective mode using allowable stress design methods (Table
E-4)
Rwi = Force reduction factor for the impulsive mode using allowable stress design methods (Table E4)
S0 = Design Spectral Response Param. (5% damped) for 0-second Periods (T = 0.0 sec)
Sd1 = The design spectral response acceleration param. (5% damped) at 1 second based on ASCE7
methods per API 650 E.2.2
Sds = The design spectral response acceleration param. (5% damped) at short periods (T = 0.2 sec)
based on ASCE7 methods per API 650 E.2.2
SigC = Maximum longitudinal shell compression stress
SigC-anchored = Maximum longitudinal shell compression stress
SUG = Seismic Use Group (Importance factors depends on SUG)
T-L = Regional Dependent Transition Period for Long Period Ground Motion (Per ASCE 7-05, fig. 2215)
ta = Actual Annular Plate Thickness less C.A.
ts1 = Thickness of bottom Shell course minus C.A.
tu = Equivalent uniform thickness of tank shell
V = Total design base shear
Vc = Design base shear due to convective component from effective sloshing weight
Vi = Design base shear due to impulsive component from effective weight of tank and contents
wa = Force resisting uplift in annular region
Wab = Design uplift load on anchor per unit circumferential length
Wc = Effective Convective (Sloshing) Portion of the Liquid Weight
Weff = Effective Weight Contributing to Seismic Response
Wf = Weight of Floor (Incl. Annular Ring)
Wi = Effective Impulsive Portion of the Liquid Weight
wint = Uplift load due to design pressure acting at base of shell
Wp = Total weight of Tank Contents based on S.G.
Wr = Weight Fixed Roof, framing and 10 % of Design Snow Load & Insul.
Wrs = Roof Load Acting on Shell, Including 10% of Snow Load
Ws = Weight of Shell (Incl. Shell Stiffeners & Insul.)
wt = Shell and roof weight acting at base of shell
Xc = Height to center of action of the lateral seismic force related to the convective liquid force for
ringwall moment
Xcs = Height to center of action of the lateral seismic force related to the convective liquid force for
the slab moment
Page: 32/53
Xi = Height to center of action of the lateral seismic force related to the impulsive liquid force for
ringwall moment
Xis = Height to center of action of the lateral seismic force related to the impulsive liquid force for the
slab moment
Xr = Height from Bottom of Shell to Roof Center of Gravity
Xs = Height from Bottom to the Shell's Center of Gravity
g = 9.8 m/s^2
WEIGHTS
Ws = 19,855 kgf or 194,708.7291 N
Wf = 3,009.9607 kgf or 29,517.6312 N
Wr = 2,263.9016 kgf or 22,201.2901 N
EFFECTIVE WEIGHT OF PRODUCT
D/H = 0.554
Wp = 647,271 kgf
Wi = (1 - (0.218 * D/H)) * Wp
Wi = (1 - (0.218 * 0.554)) * 647,271
Wi = 569,105 kgf
Wc = 0.23 * D/H * TANH (3.67 * H/D) * Wp
Wc = 0.23 * 0.554 * TANH (3.67 * 1.8052) * 647,271
Wc = 82,469 kgf
Weff = Wi + Wc
Weff = 569,105 + 82,469
Weff = 651,573.432 kgf
Wrs = 2,263.9016 kgf
DESIGN LOADS
Vi = Ai * (Ws + Wr + Wf + Wi)
Vi = 0.0625 * (19,855 + 2,263.9016 + 3,009.9607 + 569,105)
Vi = 37,140 kgf
Vc = Ac * Wc
Vc = 0.0379 * 82,469
Vc = 3,125.5582 kgf
V = SQRT (Vi^2 + Vc^2)
V = SQRT (37,140^2 + 3,125.5582^2)
V = 37,270.8808 kgf
CENTER OF ACTION FOR EFFECTIVE LATERAL FORCES
Xs = 6.95 m
RCG = 1/3 * R * (TAND (Theta))
RCG = 1/3 * 3909.75 * (TAND (3.5763))
RCG = 81.4531 mm or 0.0815 m
Xr = Shell Height + RCG
Xr = 14.7 + 0.0815
Xr = 14.7815 m
Page: 33/53
CENTER OF ACTION FOR RINGWALL OVERTURNING MOMENT
Xi = (0.5 - (0.094 * D/H)) * H
Xi = (0.5 - (0.094 * 0.554)) * 13.9
Xi = 6.2262 m
Xc = (1 - (COSH (3.67 * H/D) - 1) / ((3.67 * H/D) * SINH (3.67 * H/D))) * H
Xc = (1 - (COSH (3.67 * 1.8052) - 1) / ((3.67 * 1.8052) * SINH (3.67 * 1.8052))) * 13.9
Xc = 11.8075 m
CENTER OF ACTION FOR SLAB OVERTURNING MOMENT
Xis = (0.5 + (0.06 * D/H)) * H)
Xis = (0.5 + (0.06 * 0.554)) * 13.9)
Xis = 7.412 m
Xcs = (1 - (COSH (3.67 * H/D) - 1.937) / ((3.67 * H/D) * SINH(3.67 * H/D))) * H
Xcs = (1 - (COSH (3.67 * 1.8052) - 1.937) / ((3.67 * 1.8052) * SINH(3.67 * 1.8052))) * 13.9
Xcs = 11.8127 m
Dynamic Liquid Hoop Forces
SHELL
Width
(m)
Y (m) Ni (N/mm)
Nc (N/mm)
Nh (N/mm)
= 1.85 * Ac * G * D^2 *
= 2.6 * Ai *
= 4.9011293 *
(COSH (3.68 * (H - Y)) / D) /
G * D^2
Y*D*G
(COSH (3.68 * H / D))
SUMMARY
SigT+ (MPa)
SigT- (MPa)
= (+ Nh (SQRT (Ni^2 = (- Nh (SQRT (Ni^2 +
+ Nc^2 + (Av * Nh /
Nc^2 + (Av * Nh /
2.5)^2))) / t-n
2.5)^2))) / t-n
Shell 1
1.8 13.5952
9.6346
0.0109
513.0651
66.8125
61.4537
Shell 2
1.8 11.7952
9.6346
0.0167
445.1354
58.0424
53.2414
Shell 3
1.8 9.9952
9.6346
0.0358
377.2058
65.7107
60.0245
Shell 4
1.8 8.1952
9.6346
0.0831
309.2761
54.0518
49.0401
Shell 5
1.5 6.3952
9.6346
0.1957
241.3465
42.4228
38.0259
Shell 6
1.5 4.8952
9.4472
0.4007
184.7384
32.7401
28.8393
Shell 7
1.5 3.3952
8.0292
0.8205
128.1304
22.9186
19.7915
Shell 8
1.5 1.8952
5.3063
1.6804
71.5223
12.9492
10.8915
Shell 9
1.5 0.3952
1.2784
3.4416
14.9143
3.1046
1.8668
Overturning Moment
Mrw = ((Ai * [(Wi * g) * Xi + (Ws * g) * Xs + (Wr * g) * Xr])^2 + [Ac * (Wc * g) * Xc]^2)^0.5
Mrw = ((0.0625 * [(569,105 * 9.8) * 6.2262 + (19,855 * 9.8) * 6.95 + (2,263.9016 * 9.8) * 14.7815])^2 +
[0.0379 * (82,469 * 9.8) * 11.8075]^2)^0.5
Mrw = 2,305,452.3565 N-m
Ms = ((Ai * [(Wi * g) * Xis + (Ws * g) * Xs + (Wr * g) * Xr])^2 + [Ac * (Wc * g) * Xcs]^2)^0.5
Ms = ((0.0625 * [(569,105 * 9.8) * 7.412 + (19,855 * 9.8) * 6.95 + (2,263.9016 * 9.8) * 14.7815])^2 +
[0.0379 * (82,469 * 9.8) * 11.8127]^2)^0.5
Ms = 2,714,744.7893 N-m
RESISTANCE TO DESIGN LOADS
Fy = 205 MPa
Ge = S.G. * (1- 0.4 * Av)
Page: 34/53
Ge = 1 * (1- 0.4 * 0.0933)
Ge = 0.9627
wa = MIN (99 * ta * (Fy * H * Ge)^0.5 , 201.1 * H * D * Ge)
wa = MIN (99 * 6.3 * (205 * 13.9 * 0.9627)^0.5) , 201.1 * 13.9 * 7.7 * 0.9627)
wa = MIN ( 32,666.3829 , 20,720.4672)
wa = 20,720.4672 N/m
wt = (Wrs + Ws) / (Pi * D)
wt = (2,263.9016 + 19,855) / (3.1416 * 7.7)
wt = 8,966.8316 N/m
wint = P * (Pi * D^2 / 4) / (Pi * D)
wint = 7500 * (3.1416 * 7.7^2 / 4) / (3.1416 * 7.7)
wint = 14438 N/m
Anchorage Ratio
J = Mrw / (D^2 * [wt * (1 - 0.4 * Av)] + wa - 0.4 * wint
J = 2,305,452.3565 / (7.7^2 * [8,966.8316 * (1 - 0.4 * 0.0933)] + 20,720.4672 - 0.4 * 14,438
J = 1.6492
Since J > 1.54 The tank is not stable and cannot be self-anchored for the design load, per API 650
Table E-6
Maximum Longitudinal Shell-Membrane Compressive Stress
ts1 = 6.3 mm
SigC = ((wt * (1 + (0.4 * Av)) + wa) / (0.607 - (0.18667 * J^2.3)) - wa) * (1 / (1,000 * ts))
SigC = ((8,966.8316 * (1 + (0.4 * 0.0933)) + 20,720.4672) / (0.607 - (0.18667 * 1.6492^2.3)) 20,720.4672) * (1 / (1,000 * 6.3))
SigC = 275.9758 MPa
Allowable Longitudinal Shell-Membrane Compression Stress
Fty = 205 MPa
Criteria for Fc
Since [G * H * D^2 / ts1^2] < 44
Since [1 * 13.9 * 7.7^2 / 6.3^2] < 44
Since 20.7642 < 44 Then Fc = (83 * ts) / (2.5 * D) + (7.5 * SQRT(G * H))
Fc = (83 * ts) / (2.5 * D) + (7.5 * SQRT(SG * H))
Fc = (83 * 6.3) / (2.5 * 7.7) + (7.5 * SQRT(1 * 13.9))
Fc = 55.1256 MPa
Hoop Stresses
SHELL SUMMARY SigT+ Sd * 1.333 Fy * 0.9 * E Allowable Membrane t-Min Shell Ok
Shell 1 66.8125 182.621
156.825
156.825 4.384
OK
Shell 2 58.0424 182.621
156.825
156.825 4.0316
OK
Page: 35/53
Shell 3
Shell 4
Shell 5
Shell 6
Shell 7
Shell 8
Shell 9
65.7107
54.0518
42.4228
32.7401
22.9186
12.9492
3.1046
182.621
182.621
182.621
182.621
182.621
182.621
182.621
156.825
156.825
156.825
156.825
156.825
156.825
156.825
156.825
156.825
156.825
156.825
156.825
156.825
156.825
3.5017
3.182
2.8631
2.5977
2.3284
2.055
1.7851
OK
OK
OK
OK
OK
OK
OK
Mechanically Anchored
Number of anchor = 10
Max spacing = 3 m
Actual spacing = 2.4969 m
Minimum # anchor = 9
Wab = (1.273 * Mrw) / D^2 - wt * (1 - 0.4 * Av) + wint
Wab = (1.273 * 2,305,452.3565) / 7.7^2 - 8,966.8316 * (1 - 0.4 * 0.0933) + 14438
Wab = 55,305 N/m
Pab = Wab * Pi * D / Na
Pab = 55,305 * 3.1416 * 7.7 / 10
Pab = 133,784.4257 N
Pa = 3 * Pab
Pa = 3 * 133,784.4257
Pa = 401,353.2772 N
Shell Compression in Mechanically-Anchored Tanks
SigC-anchored = [Wt * (1 + (0.4 * Av)) + (1.273 * Mrw) / D^2] * (1 / (1,000 * ts))
SigC-anchored = [8,966.8316 * (1 + (0.4 * 0.0933)) + (1.273 * 2,305,452.3565) / 7.7^2] * (1 / (1,000 *
6.3))
SigC-anchored = 9.3335 MPa
Fc = 55.1256 MPa
SigC-anchored <= Fc Then the design is acceptable.
Detailing Requirements (Anchorage)
SUG = II
Sds = 0.2 g or 20 %g
Freeboard - Sloshing
TL-sloshing = 4 sec
I-sloshing = 1.25
Tc = 2.887
k = 1.5
Sd1 = 0.1167 g or 11.67 %g
Af = 0.0758 g per API 650 E.7.2
Delta-s = 0.42 * D * Af
Delta-s = 0.42 * 7.7 * 0.0758
Page: 36/53
Delta-s = 0.2451 m
0.7 * Delta-s = 0.1716 m
Since Sds < 0.33g and SUG = II per API 650 Table E-7.
a. A freeboard of O.7*Delta-s is recommended for economic considerations but not required.
Sliding Resistance
mu = 0.4 (friction coefficient)
V = 37,270.8808 kgf
Vs = mu * (Ws + Wr + Wf + Wp) * (1 - 0.4 * Av)
Vs = 0.4 * (19,855 + 2,263.9016 + 3,009.9607 + 647,271) * (1 - 0.4 * 0.0933)
Vs = 258,922.2691 kgf
Since V <= Vs Then the tank will not experience major sliding and does not require additional lateral
anchorage, per API 650 E.7.6.
Local Shear Transfer
Vmax = 2 * V / (Pi * D)
Vmax = 2 * 37,270.8808 / (3.1416 * 7.7)
Vmax = 3,081.4778 kgf/m
Page: 37/53
ANCHOR BOLT DESIGN Back
Bolt Material : A36M
Sy = 250 MPa
UPLIFT LOAD CASES, PER API-650 TABLE 5-21b
A-s-r = Bolt Root Area Req'd
bt = Uplift load per bolt
D = Tank D (m)
Fp = Pressure Combination Factor
Mrw = Seismic Ringwall Moment (Nm)
N = Anchor bolt quantity
P = Design pressure (pa)
Pf = Failure pressure per F.6 (KPa)
Pt = Test pressure per F.7.6 = 1.25 * P = 9.375 (pa)
sd = Allowable Anchor Bolt Stress (MPa)
Shell-sd-at-anchor = Allowable Shell Stress at Anchor Attachment (MPa)
t-actual = Actual Roof plate thickness (mm)
t-h = Roof plate thickness less CA (mm)
Vf = Velocity factor (kph)
W1 = Dead Load of Shell minus C.A. and Any Dead Load minus C.A. other than Roof Plate Acting on
Shell
W2 = Dead Load of Shell minus C.A. and Any Dead Load minus C.A. including Roof Plate minus C.A.
Acting on Shell
W3 = Dead Load of New Shell and Any Dead Load other than Roof Plate Acting on Shell
For Tank with Structural Supported Roof
W1 = W-shell-corroded + Shell Insulation
W1 = 130,896.6472 + 0
W1 = 130,896.6472 N
W2 = W-shell-corroded + Shell Insulation + Corroded Roof Plates Supported by Shell + Roof Dead
Load Supported by Shell
W2 = 130,896.6472 + 0 + 18,501.0751 + 0
W2 = 149,397.7223 N
W3 = New Shell + Shell Insulation
W3 = 177,316.3901 + 0
W3 = 177,316.3901 N
Uplift Case 1: Design Pressure Only
U = [(P - 0.08 * t-h) * D^2 * 785] - W1
U = [(7.5 - 0.08 * 5) * 7.7^2 * 785] - 130,896.6472
U = 199,556.1677 N
bt = U/N
bt = 19,955.6167 N
sd = 104.1666 MPa
Shell-sd-at-anchor = 136.6666 MPa
A-s-r = bt / sd
A-s-r = 19,955.6167 / 104.1666
A-s-r = 191.5739 mm^2
Page: 38/53
Uplift Case 2: Test Pressure Only
U = [(Pt - 0.08 * t-h) * D^2 * 785] - W1
U = [(9.375 - 0.08 * 5) * 7.7^2 * 785] - 130,896.6472
U = 286,823.6365 N
bt = U/N
bt = 28,682.3636 N
sd = 138.8888 MPa
Shell-sd-at-anchor = 170.8333 MPa
A-s-r = bt / sd
A-s-r = 28,682.3636 / 138.8888
A-s-r = 206.513 mm^2
Uplift Case 3: Failure Pressure Only
Not applicable since if there is a knuckle on tank roof, or tank roof is not frangible.
Pf (failure pressure per F.6) = N.A.
Uplift Case 4: Wind Load Only
PWR = Wind-Uplift per API 650 Table 5-21a, 5-21b
PWS = Wind-Pressure per API 650 Table 5-21a, 5-21b
PWR = 0.5744 KPa
PWS = 343.047 N/m^2
MWH = PWS * D * (H^2 / 2) per API 650 Table 5-21a, 5-21b
MWH = 343.047 * 7.7 * (14.7^2 / 2)
MWH = 285,396.827 Nm
U = PWR * D^2 * 785 + (4 * MWH / D) - W2
U = 0.5744 * 7.7^2 * 785 + (4 * 285,396.827 / 7.7) - 149,397.7223
U = 25,594.674 N
bt = U/N
bt = 2,559.4674 N
sd = 200 MPa
Shell-sd-at-anchor = 170.8333 MPa
A-s-r = bt / sd
A-s-r = 2,559.4674 / 200
A-s-r = 12.7973 mm^2
Uplift Case 5: Seismic Load Only
U = [4 * Mrw / D] - W2 * (1 - 0.4 * Av)
U = [4 * 2,305,452 / 7.7] - 149,397.7223 * (1 - 0.4 * 0.0933)
U = 1,053,815.3884 N
bt = U/N
bt = 105,381.5388 N
sd = 200 MPa
Shell-sd-at-anchor = 170.8333 MPa
Page: 39/53
A-s-r = bt / sd
A-s-r = 105,381.5388 / 200
A-s-r = 526.9076 mm^2
Uplift Case 6: Design Pressure + Wind Load
U = [(Fp * P + PWR - 0.08 * t-h) * D^2 * 785] + [4 * MWH / D] - W1
U = [(0.4 * 7.5 + 0.5744 - 0.08 * 5) * 7.7^2 * 785] + [4 * 285,396.827 / 7.7] - 130,896.6472
U = 165,106.6391 N
bt = U/N
bt = 16,510.6639 N
sd = 138.8888 MPa
Shell-sd-at-anchor = 170.8333 MPa
A-s-r = bt / sd
A-s-r = 16,510.6639 / 138.8888
A-s-r = 118.8767 mm^2
Uplift Case 7: Design Pressure + Seismic Load
U = [(Fp * P - 0.08 * t-h) * D^2 * 785] + [4 * Mrw / D] - W1 * (1 - 0.4 * Av)
U = [(0.4 * 7.5 - 0.08 * 5) * 7.7^2 * 785] + [4 * 2,305,452 / 7.7] - 130,896.6472 * (1 - 0.4 * 0.0933)
U = 1,192,636.8934 N
bt = U/N
bt = 119,263.6893 N
sd = 200 MPa
Shell-sd-at-anchor = 170.8333 MPa
A-s-r = bt / sd
A-s-r = 119,263.6893 / 200
A-s-r = 596.3184 mm^2
Uplift Case 8: Frangibility Pressure
Not applicable since if there is a knuckle on tank roof, or tank roof is not frangible.
Pf (failure pressure per F.6) = N.A.
Page: 40/53
ANCHOR BOLT SUMMARY Back
Bolt Root Area Req'd = 596.3184 mm^2
Bolt Diameter (d) = 33 mm (M33)
Threads per centimeters (n) = 0.2857
A-s = Actual Bolt Root Area
A-s = (pi / 4) * (d - 33.02 / n)^2
A-s = 0.7854 * (33 - 33.02 / 0.2857)^2
A-s = 635.7047 mm^2
Exclusive of Corrosion
Bolt Diameter Req'd = 31.8486 mm (per ANSI B1.1)
Actual Bolt Diameter = 33 mm (M33)
Bolt Diameter Meets Requirements
ANCHORAGE REQUIREMENTS
Wind or Uplift calculations require anchorage
Minimum # Anchor Bolts = 9
per API-650 5.12.3
Actual # Anchor Bolts = 10
Anchorage Meets Spacing Requirements
ANCHOR CHAIR DESIGN
(from AISI 'Steel Plate Engr Data' Dec. 92, Vol. 2, Part VII)
Entered Parameters
Chair Material : A36M
Top Plate Type : DISCRETE
Chair Style : VERT. TAPERED
Top Plate Width (a) : 300 mm
Top Plate Length (b) : 200 mm
Vertical Plate Width (k) : 125 mm
Top Plate Thickness (c) : 22 mm
Bolt Eccentricity (e) : 102 mm
Outside of Top Plate to Hole Edge (f) : 74.5 mm
Distance Between Vertical Plates (g) : 100 mm
Chair Height (h) : 400 mm
Vertical Plates Thickness (j) : 16 mm
Bottom Plate thickness (m) : 8 mm
Shell Course + Repad Thickness (t) : 22 mm
Nominal Radius to Tank Centerline (r) : 3854 mm
Design Load per Bolt (P) : 178896 N
Bolt Diameter (d) = 33 mm (M33)
Threads per unit length (n) = 0.2857
Bolt Yield Load = A-s * Sy
Bolt Yield Load = 635.7047 * 250
Bolt Yield Load = 158,926.1809 N
Seismic Design Bolt Load (Pa) = 401,353.2772 N
Anchor Chairs will be designed to withstand
Design Load per Bolt
Anchor Chair Design Load, (P) : 178,895.534 N
Page: 41/53
For anchor Chair Material: A36M
(per API-650 Table 5-2b, Sd-Chair = 160 MPa
Since bottom t <= 10 mm, and Seismic anchorage required (J) > 1.45,
or Wind Speed is > 160.9344 kph,
h-min is 305 mm.
For Discrete Top Plate,
Max. Chair Height Recommended : h <= 3 * a
h-max = 3 * a
h-max = 3 * 300 = 900 mm.
h-actual = 400 mm.
e-min = 0.886 * d + 15
e-min = 0.886 * 33 + 15 = 44.238 mm.
e-actual = 102 mm.
g-min = d + 26
g-min = 33 + 26 = 59 mm.
g-actual = 100 mm.
f-min = d/2 + 4
f-min = 33/2 + 4 = 20.5 mm.
c-min = SQRT[P / Sd-Chair / f * (0.375 * g - 0.22 * d)]
c-min = SQRT[178,895.534 / 160 / 74.5 * (0.375 * 100 - 0.22 * 33)] = 21.3035 mm.
c-actual = 22 mm.
j-min = MAX(13, [0.04 * (h - c)])
j-min = MAX(13, [0.04 * (400 - 22)]) = 15.12 mm.
j-actual = 16 mm.
b-min = e-min + d + 7
b-min = 44.238 + 33 + 7 = 84.238 mm.
Stress due to Top Plate Thickness
S-actual-Top-Plate = P / (f * c^2) * (0.375 * g - 0.22 * d)
S-actual-Top-Plate = 178,895.534 / (74.5 * 22^2) * (0.375 * 100 - 0.22 * 33) = 150.0305 MPa
Repad-t = 14 mm
t-shell-1 = 8 mm
ClearX = Minimum Clearance of Repad from Anchor chair
ClearX = MAX(51, 6 * Repad-t, 6 * t-shell-1)
ClearX = MAX(51, 6 * 14, 6 * 8) = 84 mm
Minimum Height = h + ClearX
Minimum Height = 400 + 84 = 484 mm
Page: 42/53
Minimum Width = a + 2 * ClearX
Minimum Width = 300 + 2 * 84 = 468 mm
Shell Stress due to Chair Height (For discrete Top Plate)
S-actual-ChairHeight = P * e / t^2 * F3
Where F3 = F1 + F2
now F1 = (1.32 * z) / (F6 + F7)
where F6 = (1.43 * a * h^2) / (r * t)
and F7 = (4 * a * h^2)^(1/3)
and z = 26 / (F4 * F5 + 26)
where F4 = (0.177 * a * m) / SQRT(r * t)
and F5 = (m / t)^2
yields F5 = (8 / 22)^2
F5 = 0.1322
yields F4 = (0.177 * 300 * 8) / SQRT(3,850 * 22)
F4 = 1.4596
yields z = 26 / (1.4596 * 0.1322 + 26)
z = 0.9926
yields F7 = (4 * 300 * 400^2)^(1/3)
F7 = 576.8998
yields F6 = (1.43 * 300 * 400^2) / (3,850 * 22)
F6 = 810.3896
yields F1 = (1.32 * 0.9926) / (810.3896 + 576.8998)
F1 = 0.0009
now F2 = 0.031 / SQRT(r * t)
yields F2 = 0.031 / SQRT(3,850 * 22)
F2 = 0.0034
yields F3 = 0.0009 + 0.0034
F3 = 0.0043
yields S-actual-ChairHeight = 178,895.534 * 102 / 22^2 * 0.0043
yields S-actual-ChairHeight = 165.1507 MPa
Maximum Recommended Stress is 170 MPa for the Shell
(per API-650 E.6.2.1.2)
Sd-ChairHeight = 170 MPa
ANCHOR CHAIR SUMMARY
S-actual-Top-Plate Meets Design Calculations
(within 105% of Sd-Chair)
S-actual-Top-Plate/Sd-Chair
150.0305/160 = 93.76%
S-actual-ChairHeight Meets Design Calculations
(within 105% of Sd-ChairHeight)
S-actual-ChairHeight/Sd-ChairHeight
165.1507/170 = 97.14%
Page: 43/53
Page: 44/53
PLAN VIEW APPURTENANCE
MARK
CUST.
MARK
DESCRIPTION
1 1/2" 3000#
LIQUID LEVEL
GAUGE
24" ROOF
MANWAY
4" ROOF NOZZLE
8" ROOF NOZZLE
2" ROOF NOZZLE
10" GOOSENECK
ROOF VENT
WINGRAIL
LLG01A
RM01
RN01
RN02
RN03
RV01
WR01A
INSIDE
RADIUS
REF
PROJ ORIENT
REMARKS
(mm)
DWG
(mm)
OUTSIDE
PROJ (mm)
--
--
317' 3398mm
280mm
0mm
0' 3300mm
178mm
203mm
152mm
0mm
0mm
0mm
65' 3400mm
308.5' 3300mm
222.5' 3350mm
229mm
0mm
--
--
0'
RM99
0mm
0' 3773mm
ELEVATION VIEW APPURTENANCE
MARK
CUST.
DESCRIPTION
MARK
AC01A
NP01A
SM01
SN01
SN01
OUTSIDE
PROJ
(mm)
ANCHOR
CHAIRS
STD API
24" SHELL
MANWAY
3" SHELL
NOZZLE
3" SHELL
NOZZLE
---
INSIDE
ELEVATION
REF
PROJ ORIENT
REMARKS
(mm)
DWG
(mm)
SEE
--TABLE
-0'
1016mm
271mm
0mm
225'
750mm W/ DAVIT
175mm
0mm
[0']
240mm HILLSIDE
175mm
0mm
[0']
450mm HILLSIDE
Nozzle Nozzle-0001 Reinforcement Requirements
(Per API-650 and other references below)
NOZZLE Description : 4 in SCH 80 TYPE RFSO
t_rpr = (Re Pad Required Thickness)
t_n = (Thickness of Neck)
Sd_n = (Stress of Neck Material)
Sd_s = (Stress of Roof Material)
CA = (Corrosion Allowance of Neck)
MOUNTED ON ROOF: Elevation = 14.742 ft
ROOF PARAMETERS:
t-calc = 6 mm
t_cr = 5 mm (Roof t-calc less C.A)
t_c = 6 mm
Page: 45/53
t_Basis = 5 mm
(FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or
API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15)
Required Area = t_Basis * D
Required Area = 5 * 114.3
Required Area = 571.5 mm^2
Available Roof Area = (t_c - t_Basis) * D
Available Roof Area = (6 - 5) * 114.3
Available Roof Area = 114.3 mm^2
Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1)
Available Nozzle Neck Area = [4 * (8.5598 - 1.7) + 6] * (8.5598 - 1.7) * MIN((103.4213/137) 1)
Available Nozzle Neck Area = 266.3762 mm^2
A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area)
A-rpr = 571.5 - 114.3 - 266.3762
A-rpr = 190.8238 mm^2
t_rpr = (A_rpr / D) + repad_CA
t_rpr = (190.8238 / 114.3) + 1.7
t_rpr = 3.3695 mm
Reinforcement Pad is required.
Based on Roof Nozzle Size of 4 in
Repad Size (OD) Must be 275 mm
Nozzle sampling Reinforcement Requirements
(Per API-650 and other references below)
NOZZLE Description : 8 in SCH 80 TYPE RFSO
t_rpr = (Re Pad Required Thickness)
t_n = (Thickness of Neck)
Sd_n = (Stress of Neck Material)
Sd_s = (Stress of Roof Material)
CA = (Corrosion Allowance of Neck)
MOUNTED ON ROOF: Elevation = 14.748 ft
ROOF PARAMETERS:
t-calc = 6 mm
t_cr = 5 mm (Roof t-calc less C.A)
t_c = 6 mm
t_Basis = 5 mm
(FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or
API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15)
Required Area = t_Basis * D
Required Area = 5 * 219.075
Required Area = 1095.375 mm^2
Available Roof Area = (t_c - t_Basis) * D
Page: 46/53
Available Roof Area = (6 - 5) * 219.075
Available Roof Area = 219.075 mm^2
Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1)
Available Nozzle Neck Area = [4 * (12.7 - 1.7) + 6] * (12.7 - 1.7) * MIN((103.4213/137) 1)
Available Nozzle Neck Area = 564.6656 mm^2
A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area)
A-rpr = 1095.375 - 219.075 - 564.6656
A-rpr = 311.6344 mm^2
t_rpr = (A_rpr / D) + repad_CA
t_rpr = (311.6344 / 219.075) + 1.7
t_rpr = 3.1225 mm
Reinforcement Pad is required.
Based on Roof Nozzle Size of 8 in
Repad Size (OD) Must be 450 mm
Nozzle LSHL Reinforcement Requirements
(Per API-650 and other references below)
NOZZLE Description : 2 in SCH 80 TYPE RFSO
t_rpr = (Re Pad Required Thickness)
t_n = (Thickness of Neck)
Sd_n = (Stress of Neck Material)
Sd_s = (Stress of Roof Material)
CA = (Corrosion Allowance of Neck)
MOUNTED ON ROOF: Elevation = 14.7451 ft
ROOF PARAMETERS:
t-calc = 6 mm
t_cr = 5 mm (Roof t-calc less C.A)
t_c = 6 mm
t_Basis = 5 mm
(FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or
API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15)
Required Area = t_Basis * D
Required Area = 5 * 60.325
Required Area = 301.625 mm^2
Available Roof Area = (t_c - t_Basis) * D
Available Roof Area = (6 - 5) * 60.325
Available Roof Area = 60.325 mm^2
Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1)
Available Nozzle Neck Area = [4 * (5.5372 - 1.7) + 6] * (5.5372 - 1.7) * MIN((103.4213/137) 1)
Available Nozzle Neck Area = 113.9818 mm^2
A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area)
A-rpr = 301.625 - 60.325 - 113.9818
A-rpr = 127.3182 mm^2
Page: 47/53
Since Nozzle size <= NPS 2 (per API-650 5.7.2), t_rpr = 0
No Reinforcement Pad required.
Nozzle outlet Reinforcement Requirements
NOZZLE Description : 3 in SCH 80 TYPE RFSO
t_rpr = (Re Pad Required Thickness)
t_n = (Thickness of Neck)
Sd_n = (Stress of Neck Material)
Sd_s = (Stress of Shell Course Material)
CA = (Corrosion Allowance of Neck)
MOUNTED ON SHELL 1 : Elevation = 0.45 ft
COURSE PARAMETERS:
t-calc = 6 mm
t_cr = 4.3 mm (Course t-calc less C.A)
t_c = 6.3 mm (Course t less C.A.)
t_Basis = 4.3 mm
(SHELL NOZZLE REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7)
Required Area = t_Basis * D
Required Area = 4.3 * 88.9
Required Area = 382.27 mm^2
Available Shell Area = (t_c - t_Basis) * D
Available Shell Area = (6.3 - 4.3) * 88.9
Available Shell Area = 177.8 mm^2
Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1)
Available Nozzle Neck Area = [4 * (7.62 - 1.7) + 6.3] * (7.62 - 1.7) * MIN((103.4213/137) 1)
Available Nozzle Neck Area = 218.4453 mm^2
A-rpr = (Required Area - Available Shell Area - Available Nozzle Neck Area)
A-rpr = 382.27 - 177.8 - 218.4453
A-rpr = -13.9753 mm^2
Since A-rpr <= 0, t_rpr = 0
No Reinforcement Pad required.
Nozzle drawoff Reinforcement Requirements
NOZZLE Description : 3 in SCH 80 TYPE RFSO
t_rpr = (Re Pad Required Thickness)
t_n = (Thickness of Neck)
Sd_n = (Stress of Neck Material)
Sd_s = (Stress of Shell Course Material)
Page: 48/53
CA = (Corrosion Allowance of Neck)
MOUNTED ON SHELL 1 : Elevation = 0.24 ft
COURSE PARAMETERS:
t-calc = 6 mm
t_cr = 4.3 mm (Course t-calc less C.A)
t_c = 6.3 mm (Course t less C.A.)
t_Basis = 4.3 mm
(SHELL NOZZLE REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7)
Required Area = t_Basis * D
Required Area = 4.3 * 88.9
Required Area = 382.27 mm^2
Available Shell Area = (t_c - t_Basis) * D
Available Shell Area = (6.3 - 4.3) * 88.9
Available Shell Area = 177.8 mm^2
Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1)
Available Nozzle Neck Area = [4 * (7.62 - 1.7) + 6.3] * (7.62 - 1.7) * MIN((103.4213/137) 1)
Available Nozzle Neck Area = 218.4453 mm^2
A-rpr = (Required Area - Available Shell Area - Available Nozzle Neck Area)
A-rpr = 382.27 - 177.8 - 218.4453
A-rpr = -13.9753 mm^2
Since A-rpr <= 0, t_rpr = 0
No Reinforcement Pad required.
Manway Circular-Manway-0001 Reinforcement Requirements
MANWAY Description : 24 in SCH -t_rpr = (Re Pad Required Thickness)
t_n = (Thickness of Neck)
Sd_n = (Stress of Neck Material)
Sd_s = (Stress of Shell Course Material)
CA = (Corrosion Allowance of Neck)
MOUNTED ON SHELL 1 : Elevation = 0.75 ft
COURSE PARAMETERS:
t-calc = 6 mm
t_cr = 4.3 mm (Course t-calc less C.A)
t_c = 6.3 mm (Course t less C.A.)
t_Basis = 4.3 mm
(SHELL MANWAY REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7)
Required Area = t_Basis * D
Required Area = 4.3 * 635
Required Area = 2730.5 mm^2
Page: 49/53
Available Shell Area = (t_c - t_Basis) * D
Available Shell Area = (6.3 - 4.3) * 635
Available Shell Area = 1270 mm^2
Available Manway Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1)
Available Manway Neck Area = [4 * (12.7 - 1.7) + 6.3] * (12.7 - 1.7) * MIN((137/137) 1)
Available Manway Neck Area = 761.2 mm^2
A-rpr = (Required Area - Available Shell Area - Available Manway Neck Area)
A-rpr = 2730.5 - 1270 - 761.2
A-rpr = 699.3 mm^2
t_rpr = (A_rpr / D) + repad_CA
t_rpr = (699.3 / 635) + 1.7
t_rpr = 2.8013 mm
Reinforcement Pad is required.
Based on Shell Manway Size of 24 in
Repad Size (L x W) Must be 1257.3 x 1524 mm
Manway Circular-Manway-0001 Reinforcement Requirements
(Per API-650 Section 5.8.4 and other references below)
MANWAY Description : 24 in SCH -- TYPE
t_rpr = (Re Pad Required Thickness)
MOUNTED ON ROOF: Elevation = 14.7473 ft
ROOF PARAMETERS:
t-calc = 6 mm
t_cr = 5 mm (Roof t-calc less C.A)
t_c = 6 mm
t_Basis = 5 mm
(FOR ROOF MANWAY,REF. API-650 FIG 5-16, TABLE 5-13)
Required Area = t_Basis * D
Required Area = 5 * 623.6
Required Area = 3118 mm^2
Available Roof Area = (t_c - t_Basis) * D
Available Roof Area = (6 - 5) * 623.6
Available Roof Area = 623.6 mm^2
Available Manway Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1)
Available Manway Neck Area = [4 * (7 - 1.7) + 6] * (7 - 1.7) * MIN((137/137) 1)
Available Manway Neck Area = 198.09 mm^2
A-rpr = (Required Area - Available Roof Area - Available Manway Neck Area)
A-rpr = 3118 - 623.6 - 198.09
A-rpr = 2296.31 mm^2
t_rpr = (A_rpr / D) + repad_CA
t_rpr = (2296.31 / 623.6) + 1.7
t_rpr = 5.3823 mm
Page: 50/53
Reinforcement Pad is required.
Based on Roof Manway Size of 24 in
Repad Size (OD) Must be 1150 mm
Page: 51/53
CAPACITIES and WEIGHTS Back
Maximum Capacity (to Max Liq Level) : 644 M^3
Capacity to Top of Shell (to Tank Height) : 682 M^3
Working Capacity (to Normal Working Level) : 584 M^3
Net working Capacity (Working Capacity - Min Capacity) : 558 M^3
Minimum Capacity (to Min Liq Level) : 25 M^3
Component New Condition (N) New Condition (Kg) Corroded (N) Corroded (Kg)
SHELL
177,317
18,082
130,897
13,348
ROOF
22,202
2,264
18,502
1,887
RAFTERS
4,314
440
4,314
440
GIRDERS
0
0
0
0
FRAMING
0
0
0
0
COLUMNS
0
0
0
0
BOTTOM
29,518
3,010
23,246
2,371
STAIRWAYS
20,359
2,076
20,359
2,076
STIFFENERS
17,802
1,817
17,801
1,816
WIND GIRDERS
0
0
0
0
ANCHOR CHAIRS
2,942
300
2,942
300
INSULATION
0
0
0
0
TOTAL
274,454
27,989
218,061
22,238
Weight of Tank, Empty : 274,454 N
Weight of Tank, Full of Product (SG = 1) : 6,622,014.1521 N
Weight of Tank, Full of Water : 6,622,013.8952 N
Net Working Weight, Full of Product : 6,348,018.504 N
Net Working Weight Full of Water : 6,348,018.504 N
Foundation Area Req'd : 47.9798 m^2
Foundation Loading, Empty : 5,720.1916 N/m^2
Foundation Loading, Full of Product : 132,296.3439 N/m^2
Foundation Loading, Full of Water : 132,296.3385 N/m^2
SURFACE AREAS
Roof : 48.1165 m^2
Shell : 355.5968 m^2
Bottom : 47.9798 m^2
Wind Moment : 388,376.1052 N-m
Seismic Moment : 2,714,744.7893 N-m
MISCELLANEOUS ATTACHED ROOF ITEMS
MISCELLANEOUS ATTACHED SHELL ITEMS
Page: 52/53
MAWP & MAWV SUMMARY Back
MAWP = Maximum calculated internal pressure
MAWV = Maximum calculated external pressure
MAXIMUM CALCULATED INTERNAL PRESSURE
MAWP = 18 kPa or 1,835.658 mmh2o (per API-650 App. F.1.3 & F.7)
MAWP = 90.8972 kPa or 9,269.7874 mmh2o (due to shell)
MAWP = 8.1534 kPa or 831.4919 mmh2o (due to roof)
TANK MAWP = 8.1534 kPa or 831.4939 mmh2o
MAXIMUM CALCULATED EXTERNAL PRESSURE
MAWV = -6.9 kPa or -703.6689 mmh2o (per API-650 V.1)
MAWV = N/A (due to shell) (API-650 App.V not applicable)
MAWV = -1.015 kPa or -103.5107 mmh2o (due to roof)
TANK MAWV = -1.015 kPa or -103.5101 mmh2o
Page: 53/53