IEC 61400 JUSTIFICATION
E30/70 PRO
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INDEX
1.- SCOPE...................................................................................................................... 3
2.- REFERENCES ............................................................................................................. 3
3.- WIND TURBINE DESCRIPTION..................................................................................... 3
3.1.-DATA SHEET ....................................................................................................... 4
3.2.-PMG DATA SHEET ................................................................................................ 4
4.- SIMPLE LOAD MODEL ................................................................................................ 7
4.1.- CALCULATION OF EQUIVALENT STRESSES ......................................................... 12
4.2.-MATERIAL CHARACTERIZATION ......................................................................... 14
4.3.-SAFETY FACTORS .............................................................................................. 15
ANNEX A ..................................................................................................................... 18
FEM ANALYSIS ............................................................................................................ 18
A.1.-EPRO_BASE ....................................................................................................... 19
A.2.-EPRO_ BIELA ..................................................................................................... 24
A.3.-EPRO_CORREDERA ............................................................................................. 30
A.4.-EPRO_CUCHARA ................................................................................................ 35
A.5.-EPRO_GIRATORIA .............................................................................................. 41
A.6.-EPRO_GONDOLA ................................................................................................ 47
A.7.-EPRO_PLATO ..................................................................................................... 55
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1.- SCOPE
This part of IEC 61400 deals w ith safety philosophy, quality assurance, and
engineering integrity and specifies requirements for the safety of Small Wind Turbines
(SWTs) including design, installation, maintenance and operation under specified
external conditions. Its purpose is to provide the appropriat e level of protection against
damage from hazards from these systems during their planned lifetime.
This part of IEC 61400 is concerned w ith all subsystems of SWT such as protection
mechanisms, internal electrical systems, mechanical systems, support structures,
foundations and the electrical interconnection w ith the load.
While this part of IEC 61400 is similar to IEC 61400-1, it does simplify and make
significant changes in order to be applicable to small turbines.
This part of IEC 61400 applies to w ind turbines w ith a rotor sw ept area smaller t han
200 m 2 generating at a voltage below 1 000 V a.c. or 1 5 00 V d.c. .
This part of IEC 61400 should be used together w ith the appropriate IEC and ISO
standards.
2.- REFERENCES
Basis reference
“ IEC 61400-2 Design requirements for small w ind turbines”
3.- WIND TURBINE DESCRIPTION
The EPRO70 w ind turbine is a w ind turbine of 3,5 kW in nominal pow er, w ith a
permanent magnet generator and a passive variable pitch syst em to control the pow er
output and it can w ork as in isolated installations as in grid connected. In the next
point some of the most important charact eristics are specified.
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3.1.-DATA SHEET
GENERAL
Configuration
Pow er [W]
Rated speed [m/s]
Diameter [m]
Sw ept area [m2]
Annual energy yield [kWh] at 5ms
Max. pow er [W]
IEC Turbine Class
Wind class
Start rotation w ind speed [m/s]
Cut-in w ind speed [m/s]
Cut-out w ind speed [m/s]
Noise [dB]
Nacelle w eight [kg]
Operating temp. range [ºC]
Nominal rotation speed [rpm]
Passive pitch start [rpm]
Design lifetime [years]
Supported speed [m/s]
3 blades, horizontal axis, clockw ise, upw ind, passive yaw ,
variable pitch
5000
11
4.25
14.2
6000
5500
Class IV
IEC / NVN I -A
1.8
2.8
n/a
44
185
-25/50
225
260
25
> 60
GENERATOR
Type
Generator
Direct drive permanent magnet synchronous
250 rpm | 24 poles | neodymium magnets
Material
Fiberglass epoxy resins and polyurethane core
BLADES
CONVERTER
Nominal efficiency [% ]
Point tracking
95
MPPT algorithm
OTHER INFO
Applications
Brake
Controller
Noise
Anti-corrosive protection
Isolated connection batteries, electric grid connection
Electrical
Optional grid connection and battery charging
1% more than the environmental noise of the w ind.
Cataphoresis, epoxy painting
TOWER
Configuration
12, 15 y 18m, folding, cable-stayed or lattice.
Table 1 – Data sheet
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3.2.-PMG DATA SHEET
ELECTRICAL SPECIFICATION
Rated output pow er [W]
Rated rotation speed [rpm]
Rectified DC current at rated output [A]
Number of poles
Required torque at rated pow er [Nm]
Phase resistance [Ohm]
Output w ire square section [mm2]
Output w ire length [mm]
Insulation
Generator configuration
Design lifetime
3500
250
ND
30
164
1
2.5
700
F
Horizontal
15
MECHANICAL SPECIFICATION
Weight [kg]
Starting torque [Nm]
Rotor inertia [kg m2]
Front bearing
Rear bearing
100
< 1
0.2
SKF 6309-2rsr
SKF 6207-2rsr
MATERIAL SPECIFICATION
Shaft material
Outer frame material
Fasteners
Windings temperature rating [ºC]
Magnets material
Magnets temperature rating [ºC]
Magnets temperature until demagnetization [ºC]
Lamination stack
F1252
Aluminum alloy
Inox
130
Nd
100
150
Non oriented magnet ic steal
Table 2 – PMG Data sheet
PMG PERFORMANCE
The permanent magnet generator performance curves are next:
The open circuit voltage show s a linear behavior:
Figure 1 – PMG open circuit voltage
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The output pow er is approximat ed by a straight line:
Figure 2 – PMG output pow er
The input torque needed for the continuous movement at the revolutions show n
below :
Figure 3 – PMG input torque
Figure 4 – PMG Schematic design
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4.- SIMPLE LOAD MODEL
It has been performed a SLM (Simple Load Model) analysis according to the IEC
61400-2.
This is useful to get t he real forces that appear in the w ind turbine.
For certain turbine configurations, the loads can be derived using simple, conservative
equations for a limited set of load cases. If the turbine configuration does not meet
those configuration requirements, the simple equations cannot be used, instead the
alternative aero elastic modelling or load measurements shall be used.
In Table 3 there are w ritten all the necessary data to initialize the equations. All the
parameters are about the geometry of the w ind turbine and the operational behavior.
The Drag, Lift and Thrust coefficients are obtained according to t he IEC 61400 -2.
Along the overall process the equations used have been gotten from the IEC 61400 -2
and each one is named before its use.
Table 1 Input data in the SLM method
INPUT DATA IN THE SLM METHOD
Description
Input value
Air density
Gravitational acceleration
Reference w ind speed
Average w ind speed
Number of blades
Blade tip radius
Total planform area of the blade
Drag coefficient of the blades
Max lift coefficient of the blades
Thrust coefficient
Maximum rotor speed
Design rotor speed
Second moment of inertia for each blade
Single blade mass
Rotor mass (All blades plus hub)
Distance from blade centre of gravity to rotor axis
Distance betw een rotor centre and the first bearing
Distance betw een the rotor centre and the yaw axis
Gearbox ratio
Brake torque
Design pow er
Short circuit torque factor
1.225
9.81
30.0
6.0
3
2.135
0.349
1.5
2.0
0.5
400
250
0.123
4.95
59.34
0.86
0.28
0.26
1.0
0
3.5
2.0
Units
Symbol
kg/m 3
m/s2
m/s
m/s
n/a
m
m2
n/a
n/a
n/a
rpm
rpm
kg m 2
kg
kg
m
m
m
n/a
Nm
kW
n/a
ρ
g
V_ref
V_ave
B
R
A_proj,B
C_d
C_l,max
C_T
n_max
n_design
I_B
m_B
m_r
R_cog
L_rb
L_rt
Gear
M_brake
P_design
G
Table 3 – Input data in the SLM method
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The next paramet ers are intermediate data needed for the calculations of the loads in
the SLM method. All of this paramet ers give us much informat ion about the behavior
of the w ind turbine like the maximum w ind speeds that are t aking like a point of design
for survival, not for operation.
PARAMETERS CALCULATED FROM THE INPUT DATA
Description
Equation
Design w ind speed
50 year extreme w ind speed
50 year extreme tip speed ratio
Design tip speed ratio
Drive train efficiency
Design torque
Projected area (turbine sw ept area)
Design rotational speed of the rotor
Maximum possible rotor speed
Max yaw rate
Eccentricity of the rotor centre of mass
Effective brake torque
IEC F
IEC 10
IEC F.2
IEC F.2
-
Value
8.4
42.0
2.13
6.65
0.62
216.5
14.32
26.18
41.89
2.88
0.0107
0.0
Units
Symbol
m/s
m/s
n/a
n/a
n/a
Nm
m2
rad/s
rad/s
rad/s
m
Nm
Table 4 – Intermediate parameters calculates from the input data
Figure 5 – Coordinate system
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V_design
V_e50
λ_e50
λ_design
η
Q_design
A_proj
ω_n,design
ω_n,max
ω_yaw ,max
e_r
M_brake
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For the calculations it must be taken into account that there are different loads
hypothesis. The IEC 61400-2 consider eight different load cases.
Load case A: Normal operation.
The design load for “ normal operation” is a fatigue load. The load case assumes
constant range fatigue loading for the blade and shaft, these ranges are given below .
The ranges are to be considered in the fatigue assessment as peak-to-peak values. The
mean values of the load ranges can be ignored.
The fatigue loading on the blade w ould be considered to occur at the airfoil – root
junction or at the root – hub junction, w hichever is determined to have the low est
ultimate strength. The calculated stresses are the combinat ion of the centrifugal
loading (FZB) and the bending moments (M XB and M YB).
The fatigue load on t he rotor shaft shall be considered at the rot or shaft at the first
bearing (nearest to t he rotor). The range of the stress shall be calculated from t he
combination of the thrust loading (Fx-shaf t ), t he torsion moment (M x-shaf t ) and the bending
moment (M shaft ).
Load case B: Yawing
For this load case, the ultimate loads (gyroscopic forces and moments) shall be
calculated assuming t he maximum yaw speed ωyaw ,max occurring w ith n design.
Load case C: Yaw error
All turbines operate w ith a cert ain yaw error. In this load case, a yaw error of 30° is
assumed.
Load case D: Maximum thrust
The SWT can be exposed to high thrust loads on the rotor. The thrust load act s
parallel to the rotor shaft and has a maximum value.
The trust coefficient is equal to 0,5 by normative.
Load case E: Maximum rotational speed
The centrifugal load in the blade root FZB and the shaft bending moment M SHAFT due t o
centrifugal load and rotor unbalance shall be calculated. The maximum possible rotor
speed is directly relat ed to the maximum rotational speed revolutions.
Load case F: Short at load connection
In the case of a direct electrical short at the output of the SWT or internal short in the
generator, high moment is creat ed about t he rotor shaft due to the short circuit torque
of the alternator. In the absence of any values proven to be more accurat e, tw o times
the QDESIGN is to be taken as the short circuit torque acting on the generat or shaft.
In the absence of any values proven to be more accurate, G shall be 2,0.
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Load case G: Shutdown (braking)
In the case of w ind t urbines w ith a mechanical or electrical braking system in the drive
train, the braking moment can be greater than the maximum driving moment. In these
cases, the braking moment M brake, derived from testing or calculations, shall be used in
the design calculations of the SWT. The maximum shaft torque is assumed to be equal
to the brake plus the design torque (thus assuming that the brake is applied w hile t he
generator still delivers design torque).
Mbrake shall be multiplied by the gearbox ratio if the brake is on the high speed shaft.
Load case H: Parked wind loading
In this load case, the w ind turbine is parked in the normal w ay. The loads on t he
exposed
parts of the SWT shall be calculated assuming w ind speed of V e50
The maximum tow er bending moment shall be calculated using the thrust force. The
drag or lift force on t he tow er and nacelle need to be t aken int o account as w ell. For
free standing tow ers the maximum bending moment w ill occur at the tow er base. For
guyed tow ers, the maximum bending moment w ill occur at the upper guy w ire
attachment.
Load case I: Parked w ind loading, maximum exposure
In the case of a failure in the yaw mechanism, the SWT can be exposed to the w ind
from all directions. Thus, for design purposes, the forces on the SWT blades, nacelle,
tow er, and t ail (if applicable) shall be calculated for all possible exposures including
w inds from the front, side or rear of the rot or.
Load case J: Transportation, assembly, maintenance and repair
The manufacturer shall consider loads on the turbine system caused by t he
transportation, assembly, installation, and maintenance and repair of the system.
Examples of such loads are:
– gravity loads on turbine during transportation in other than upright position
– loads caused by special installation tools
– w ind loads during installation
– loads introduced by hoisting the turbine onto the foundation
– loads on a tilt up tow er during erection
– load on a support structure from climbing it
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LOADS FROM SLM
Description
Equation
SLM value Units Symbol
Load case A – Fatigue loads on blades and rotor shaft
Blade loads
Centrifugal force at the blade root (z-axis)
Lead-lag root bending moment (x-axis)
Flapw ise root bending moment (y-axis)
IEC 21
IEC 22
IEC 23
5304.91
148.10
480.21
N
Nm
Nm
ΔF_zB
ΔM_xB
ΔM_yB
IEC 24
IEC 25
IE 26
1012.15
228.93
686.15
N
Nm
Nm
ΔF_x-shaft
ΔM_x-shaft
ΔM_shaft
IEC 28
IEC 29, 30
266.96
550.94
Nm
Nm
M_yB
M_shaft
IEC 31
871.86
Nm
M_yB
IEC 32
986.74
N
F_x-shaft
IEC 33
IEC 34
6790.29
474.20
N
Nm
F_zB
M_shaft
IEC 35
IEC 36
433.00
144.33
Nm
Nm
M_x-shaft
M_xB
IEC 37
IEC 38
n/a
n/a
Nm
Nm
M_x-shaft
M_xB
603.79
1696.85
Nm
N
M_yB
F_x-shaft
Shaft loads
Thrust on shaft (x-axis)
Shaft moment about x-axis
Shaft moment
Load case B – Blade and rotor shaft loads during yaw
Flapw ise root bending moment (y-axis)
Bending moment on the shaft
Load case C – Yaw error loads on blades
Flapw ise root bending moment (y-axis)
Load case D – Maximum thrust on shaft
Maximum thrust on shaft
Load case E – Maximum rotational speed
Centrifugal force at the blade root (z-axis)
Bending moment on the shaft
Load case F – Short at load connection
Bending moment on shaft
Lead-lag root bending moment (x-axis)
Load case G – Shutdow n braking
Bending moment on shaft
Lead-lag root bending moment (x-axis)
Load case H – Parked w ind loads during idling
Flapw ise root bending moment (y-axis)
Maximum thrust on shaft
IEC 39, 40
IEC 41, 42
Table 5 – Loads from SML
In Table 6 there are considered the highest values for each part in w hich w e must pay
attention. The highest betw een all the load hypothesis have been taken. These values
w ill be the input data for the FEM (Finit e Element Method analysis)
MAXIMUM LOADS
Description
Blades loads
Hypothesis
Centrifugal force at
the blade root (z-axis)
Lead-lag root bending
moment (x-axis)
Flapw ise root bending
moment (y-axis)
Value
Symbol
Load case E – Maximum rotational speed
6790.29N
F_zB
Load case A – Fatigue loads on blades and rotor
shaft
148.10Nm
ΔM_xB
Load case C – Yaw error on blades
871.86Nm
My_B
Load case H – Parked w ind loads during idling
1696.85 N
F_x-shaft
Load case F – Short at load connection
433.00 N m
M_x-shaft
Load case A - Fatigue loads on blades and rotor
shaft
686.15 N m
ΔM_shaft
Shaft loads
Maximum thrust on
shaft
Bending moment on
shaft
Shaft moment
Table 6 – Maximum loads
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4.1.- CALCULATION OF EQUIVALENT STRESSES
Handmade calculations w ere done before the FEM analysis for the different load
hypothesis.
In Table 7 there are some necessary data for the calculations to the stresses w hich
appear on the most critical parts in the w ind turbine as the blades and the shaft are.
Other data that w e have to fix are the f atigue parameters that w e w ant the w ind
turbine to resist.
ADDITIONAL MECHANICAL DATA
Description
Value
Diameter of the shaft
Cross sectional area of the shaft
Second moment of inertia for the shaft
Section modulus for the shaft
Cross sectional area of the blade root
Ixx for the blade
x-distance from blade centroid to the maximum stress point
Iyy for the blade
y-distance from blade ent roid to the maximum stress point
Blade x-section modulus
Blade y-section modulus
Ultimate material strength for the blades
Ultimate material strength for the shaft
Units
Symbol
0.05
1.9635E-3
3.068E-7
1.2272E-5
3.85E-3
3E-7
5E-3
4E-5
3E-2
6E-5
1.33E-3
3445
207
m
m2
m4
m3
m2
m4
m
m4
m
m3
m3
MPa
MPa
n/a
A_shaft
I_x-shaft
W_shaft
A_B
I_xxB
c_xB
I_yyB
c_yB
W_xB
W_yB
f_kb
f_k-shaft
25
788940000
9.86E+ 9
1E+ 10
1.23E+ 3
Years
s
n/a
n/a
n/a
T_d
n_i
N_shaft
N_blade
Additional dat a for fat igue calculations
Design life of the turbine
Number of fatigue cycles
Number of cycles to failure as a function of stress (shaft)
Number of cycles to failure as a function of stress (blade)
Table 7 – Additional mechanical data
Where
⁄
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Now w e proceed to the calculations of the equivalent stress in the blade root and in
the axis in the diff erent load hypothesis.
The calculation method is alw ays the same but changing the loads in each hypothesis.
ADDITIONAL MECHANICAL DATA
Description
Equivalent stress [MPa]
Load case A – Fatigue loads on blades and rotor shaft
Blades
Shaft
4.21
58.69
Load case B – Blade and rotor shaft loads during yaw
Blades
Shaft
0.20
44.89
Load case C – Yaw error loads on blades
Blades
0.65
Load case D – Maximum thrust on shaft
Shaft
0.50
Load case E – Maximum rot ational speed
Shaft
Blades
1.76
38.64
Load case F – Short load connection
Blades
Shaft
2.41
30.56
Load case G – Shutdow n braking
Blades
Shaft
-
Load case H – Parked w ind loads during idling
Blades
Shaft
0.45
0.86
Table 8 – Equivalent stresses
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4.2.-MATERIAL CHARACTERIZATION
One of the most important things to guarantee the correct behavior of the w ind turbine
is to use the correct materials, and the mechanical properties of them.
In that point w e have made the decision to full characterize all the mat erials f or
know ing the real properties of them and after that to oversize the w ind turbine for
getting more reliabilit y.
For all the materials that w e use w e ask f or the data sheet w hich has the full analysis
to check if the material is the one w e need for guarant eeing the mechanical
performance that is needed and the safety factors.
ALUMINUM 356 T6
Properties
Value
Modulus of elasticity
Poisson coefficient in XY
Shear modulus XY
Mass density
Traction limit X
Traction limit Y
Elastic limit
Coefficient of thermal expansion X
Thermal conductivity X
Specific heat
Units
4.21
58.69
0.20
44.89
0.65
0.50
1.76
38.64
2.41
30.56
Table 9 – Aluminum 356 T6
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N/m^ 2
N/D
N/m^ 2
Kg/m^ 3
N/m^ 2
N/m^ 2
N/m^ 2
/K
W/(m K)
J/(kg K)
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STEEL F 114
Properties
Value
Modulus of elasticity
Poisson coefficient in XY
Shear modulus XY
Mass density
Traction limit X
Compression limit X
Elastic limit
Coefficient of thermal expansion X
Thermal conductivity X
Specific heat
Damping coefficient
Units
2.05 + 011
0.29
8e+ 010
7850
665000000
400000000
1.15e-005
49.8
486
N/m^ 2
N/D
N/m^ 2
Kg/m^ 3
N/m^ 2
N/m^ 2
N/m^ 2
/K
W/(m K)
J/(kg K)
N/D
Table 10 – Steel F114
4.3.-SAFETY FACTORS
The most important parameters in a small w ind turbine are saf et y and reliabilit y.
According to IEC 61400-2 safety factors for this machines must be higher than 9 if
the material properties are not charact erized but if the mat erial is full characterized as
w e have made w ith ours the safety factor must not be less than 3.
We have made the choice to full characterize the materials and despite of that w e also
get higher safety fact ors.
In the next tables the comparison betw een the safety factors w hich w ere obtained and
the ones w hich are needed is done.
It is clear that each part of the w ind turbine is according to the IEC 61400 -2 and the
safety factors are bigger than the mandat ories ones because of w e w ant to increase
the safety of the machine.
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According to the simple load model:
The safety study w as first done using the simple load model to ensure that the
IEC61400-2 w as covered.
Simple Load Model Results
Load Case A - Fatigue Loads on Blades and Rotor Shaft
Blades
Shaft
Fatigue Damage Limit
1,00
1,00
Fatigue Damage
1,01E-06
Infinite Life
Conclusion
SAFE
SAFE
Load Case B - Blade and Rotor Shaft Loads during Yaw
Blades
Shaft
Material Stress Limit (MPa)
382,78
205,00
Calculated Stress (MPa)
0,20
48,9
Conclusion
SAFE
SAFE
Calculated Stress (MPa)
0,65
Conclusion
SAFE
Calculated Stress (MPa)
0,50
Conclusion
SAFE
Calculated Stress (MPa)
38,64
17,6
Conclusion
SAFE
SAFE
Calculated Stress (MPa)
2,41
35,6
Conclusion
SAFE
SAFE
Calculated Stress (MPa)
n/a
n/a
Conclusion
n/a
n/a
Load Case C - Yaw Error Load on Blades
Blades
Material Stress Limit (MPa)
382,78
Load Case D - Maximum Thrust on Shaft
Shaft
Material Stress Limit (MPa)
382,78
Load Case E - Maximum Rotational Speed
Blades
Shaft
Material Stress Limit (MPa)
382,78
205,00
Load Case F - Short at Load Connection
Blades
Shaft
Material Stress Limit (MPa)
382,78
205,00
Load Case G - Shutdow n Braking
Blades
Shaft
Material Stress Limit (MPa)
382,78
205,00
Load Case H - Parked Wind Loads during Idling
Blades
Shaft
Material Stress Limit (MPa)
382,78
205,00
Calculated Stress (MPa)
0,86
4,5
Table 11 – Simple Load Model Results
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Conclusion
SAFE
SAFE
ENAIR ENERGY S.L.
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According to the Annex A and the Finite Element Method for the maximum loads.
In the IEC 61400-2 the FEM analysis is not mandatory, but w e have decided to full
study our w ind turbine to ensure that not only in the parts w hich is mandatory to
study the loads the safe factor is the correct one. We w ant to know all about our w ind
turbine and w e w ant it to me as safe as w e can, and the finite element method
analysis reveals that the safety f actors in every part of the w ind turbine are higher
than the mandatories as it could be seen in the next table.
Part
Material stress
limit [MPa]
Calculated
stress [MPa]
Safety
factor
Conclusion
Framew ork
Nacelle
Blade holder
Yaw axe
Variable pitch support
Rod
Slider
272
272
205
205
272
205
205
33.3
45.3
59.4
51.9
68.5
34.6
24.1
8.17
6.01
3.45
3.95
3.97
5.92
8.5
SAFE
SAFE
SAFE
SAFE
SAFE
SAFE
SAFE
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
ANNEX A
FEM ANALYSIS
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
A.1.-EPRO_BASE
Analyzed File:
EPRO_BASE.ipt
Autodesk Inventor Version:
Creation Date:
Simulation Author:
Summary:
2015 (Build 190159000, 159)
09/05/2016, 9:54
Román Dato Cuadrado
Project Info (iProperties)
Physical
The most significant material specifications of this parts w ere defined below
Material
Aluminum 356 T6
Density
Mass
Area
Volume
2,8384 g/cm^ 3
8,09196 kg
402876 mm^ 2
2850890 mm^ 3
x= 0,0569934 mm
y= 73,0483 mm
z= -0,0503049 mm
Center of Gravity
Data
General objective and settings: This kind of analysis is the necessary to get the
strengths that appear in the studied part of the full w ind turbine
The single point objective is for solving every point in the part, and the static analysis
is opposite to the fatigue one, so the maximum loads act in certain moments.
Design Objective
Single Point
Simulation Type
Last Modification Date
Detect and Eliminate Rigid Body Modes
Static Analysis
09/05/2016, 9:51
No
Mesh settings: These mesh settings w ere chosen according w ith the standards for that
kind of analysis
Avg. Element Size (fraction of model diameter)
Min. Element Size (fraction of avg. size)
Grading Factor
Max. Turn Angle
Create Curved Mesh Elements
0,05
0,05
1,1
60 deg
Yes
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Operating conditions
In the next st eps it is show n w hat and w here the loads are put. The pictures are clear
enough to understand w hat kind of loads are actuating in its face.
Pressure: 1
Load Type
Pressure
Magnitude
4.880 MPa
Load Type
Force
Magnitude
Vector X
Vector Y
Vector Z
452.000 N
0.000 N
452.000 N
0.000 N
Selected Face(s)
Force: 1
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Force: 2
Load Type
Force
Magnitude
Vector X
Vector Y
Vector Z
113.000 N
0.000 N
113.000 N
0.000 N
Selected Face(s)
Fixed Constraint: 1
Constraint Type
Fixed Constraint
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Results
The results obtained are show n using three magnitudes of control
-Von Mises Stress: It reveals a combination of all kind of tensions that appear in each
point of the part
-Displacement: It show s how much the part is deformed
-Safety factor: Using the mat erial given as a reference it makes the comparison
betw een the maximum stress admitted and the stress obtained in each point
Result Summary
Name
Minimum
Volume
Mass
Von Mises Stress
Displacement
Safety Factor
Maximum
2850890 mm^ 3
8,09196 kg
0,00104139 MPa
0 mm
8,16687 ul
33,6726 MPa
0,0406143 mm
15 ul
Figures
Von Mises Stress
Maximum combined stress point
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Displacement
Points w hich w ill be deformed w hen the maximum loads are applied
Safety Factor
The most important parameter, it show s the safety factor in each point of the part
w hen the maximum loads are applied. That analysis does not make difference
betw een the most critical points like the SLM because it takes the overall points of
the part to make the analysis.
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
A.2.-EPRO_ BIELA
Analyzed File:
EPRO_BIELA.ipt
Autodesk Inventor Version:
Creation Date:
Simulation Author:
Summary:
2015 (Build 190159000, 159)
09/05/2016, 13:07
Román Dato Cuadrado
Project Info (iProperties)
Physical
The most significant material specifications of this parts w ere defined below
Material
Steel F114
Density
Mass
Area
Volume
Center of Gravity
7,85 g/cm^ 3
0,328713 kg
11015,6 mm^ 2
41874,3 mm^ 3
x= 7,5 mm
y= 12,104 mm
z= -15,5365 mm
Simulation: 1
General objective and settings: This kind of analysis is the necessary to get the
strengths that appear in the studied part of the full w ind turbine
The single point objective is for solving every point in the part, and the static analysis
is opposite to the fatigue one, so the maximum loads act in certain moments.
Design Objective
Single Point
Simulation Type
Last Modification Date
Detect and Eliminate Rigid Body Modes
Static Analysis
09/05/2016, 13:06
No
Mesh settings: These mesh settings w ere chosen according w ith the standards for that
kind of analysis
Avg. Element Size (fraction of model diameter)
Min. Element Size (fraction of avg. size)
Grading Factor
Max. Turn Angle
Create Curved Mesh Elements
0,01
0,01
1,1
60 deg
Yes
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Material(s)
Name
Steel, Cast
Mass Density
Yield Strength
Ultimate Tensile Strength
Young' s Modulus
Poisson' s Ratio
Shear Modulus
EPRO_BIELA
General
Stress
Part Name(s)
7,85 g/cm^ 3
250 MPa
300 MPa
210 GPa
0,3 ul
80,7692 GPa
Operating conditions
In the next steps it is show n w hat and w here the loads are put. The pictures are clear
enough to understand w hat kind of loads are actuating in its f ace.
Force: 1
Load Type
Force
Magnitude
Vector X
Vector Y
Vector Z
1255.000 N
0.000 N
1255.000 N
0.000 N
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Frictionless Constraint: 1
Constraint Type
Frictionless Constraint
Selected Face(s)
Frictionless Constraint: 2
Constraint Type
Frictionless Constraint
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Results
Reaction Force and Moment on Constraints
Constraint Name
Reaction Force
Magnitude
Component
(X,Y,Z)
Frictionless
Constraint:1
14,6695 N
Frictionless
Constraint:2
1240,25 N
0 N
-14,6695 N
0 N
0 N
-1240,25 N
0 N
Reaction Moment
Magnitude
Component
(X,Y,Z)
0,531348 N m
80,4596 N m
-0,531348 N m
0 Nm
0 Nm
-80,4596 N m
0 Nm
0 Nm
Result Summary
The results obtained are show n using three magnitudes of control
-Von Mises Stress: It reveals a combination of all kind of tensions that appear in
each point of the part
-Displacement: It show s how much the part is deformed
-Safety factor: Using the mat erial given as a reference it makes the comparison
betw een the maximum stress admitted and the stress obtained in each point.
Name
Volume
Mass
Von Mises Stress
1st Principal Stress
3rd Principal Stress
Displacement
Safety Factor
Minimum
Maximum
41874,3 mm^ 3
0,328713 kg
0,0310979 MPa
42,1988 MPa
-47,4164 MPa
93,4125 MPa
-93,5576 MPa
49,06 MPa
0,000646734 mm
0,0189292 mm
5,92433 ul
15 ul
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Figures
Von Mises Stress
Maximum combined stress point
Displacement
Points w hich w ill be deformed w hen the maximum loads are applied
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Safety Factor
The most important parameter, it show s the safety factor in each point of the part
w hen the maximum loads are applied. That analysis does not make difference
betw een the most critical points like the SLM because it takes the overall points of
the part to make the analysis.
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
A.3.-EPRO_CORREDERA
Analyzed File:
EPRO_CORREDERA.ipt
Autodesk Inventor Version:
Creation Date:
Simulation Author:
Summary:
2015 (Build 190159000, 159)
09/05/2016, 15:46
Román Dato Cuadrado
Project Info (iProperties)
Physical
The most significant material specifications of this parts w ere defined below
Material
Steel F114
Density
Mass
Area
Volume
7,85 g/cm^ 3
2,44378 kg
63602,1 mm^ 2
311309 mm^ 3
x= 80,0001 mm
y= 24,3562 mm
z= -46,188 mm
Center of Gravity
3070V2_Análisis_Deslizadora
General objective and settings: This kind of analysis is the necessary to get the
strengths that appear in the studied part of the full w ind turbine
The single point objective is for solving every point in the part, and the static analysis
is opposite to the fatigue one, so the maximum loads act in certain moments.
Design Objective
Single Point
Simulation Type
Last Modification Date
Detect and Eliminate Rigid Body Modes
Static Analysis
09/05/2016, 15:44
No
Mesh settings: These mesh settings w ere chosen according w ith t he standards for that
kind of analysis
Avg. Element Size (fraction of model diameter)
Min. Element Size (fraction of avg. size)
Grading Factor
Max. Turn Angle
Create Curved Mesh Elements
0,01
0,05
1,2
60 deg
Yes
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Material(s)
Name
Steel, Cast
Mass Density
Yield Strength
Ultimate Tensile Strength
Young' s Modulus
Poisson' s Ratio
Shear Modulus
EPRO_BIELA
General
Stress
Part Name(s)
7,85 g/cm^ 3
250 MPa
300 MPa
210 GPa
0,3 ul
80,7692 GPa
Operating conditions
In the next steps it is show n w hat and w here the loads are put. The pictures are
clear enough to understand w hat kind of loads are actuating in its face.
Force: 1
Load Type
Force
Magnitude
Vector X
Vector Y
Vector Z
9145.000 N
-0.000 N
-9145.000 N
0.000 N
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Fixed Constraint: 1
Constraint Type
Fixed Constraint
Selected Face(s)
Frictionless Constraint: 1
Constraint Type
Frictionless Constraint
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Results
The results obtained are show n using three magnitudes of control
-Von Mises Stress: It reveals a combination of all kind of tensions that appear in each
point of the part
-Displacement: It show s how much the part is deformed
-Safety factor: Using the material given as a reference it makes the comparison
betw een the maximum stress admitted and the stress obtained in each point.
Result Summary
Name
Volume
Mass
Von Mises Stress
Displacement
Safety Factor
Minimum
Maximum
311309 mm^ 3
2,44378 kg
0,0104964 MPa
92,0673 MPa
0 mm
0,0110634 mm
2,7154 ul
15 ul
Figures
Von Mises Stress
Maximum combined stress point
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Displacement
Points w hich w ill be deformed w hen the maximum loads are applied
Safety Factor
The most important parameter, it show s the safety factor in each point of the part
w hen the maximum loads are applied. That analysis does not make difference betw een
the most critical points like the SLM because it takes the overall points of the part to
make the analysis.
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
A.4.-EPRO_CUCHARA
Analyzed File:
EPRO_CUCHARA.ipt
Autodesk Inventor Version:
Creation Date:
Simulation Author:
Summary:
2015 (Build 190159000, 159)
09/05/2016, 11:42
Román Dato Cuadrado
Project Info (iProperties)
Physical
The most significant material specifications of this parts w ere defined below
Material
Steel F114
Density
Mass
Area
Volume
7,15 g/cm^ 3
3,52544 kg
63907 mm^ 2
493069 mm^ 3
x= 17,5713 mm
y= -0,00144994 mm
z= 145,664 mm
Center of Gravity
Simulation: 1
General objective and settings: This kind of analysis is the necessary to get the
strengths that appear in the studied part of the full w ind turbine
The single point objective is for solving every point in the part, and the static analysis
is opposite to the fatigue one, so the maximum loads act in certain moments.
Design Objective
Single Point
Simulation Type
Last Modification Date
Detect and Eliminate Rigid Body Modes
Static Analysis
09/05/2016, 11:42
No
Mesh settings: These mesh settings w ere chosen according w ith the standards for that
kind of analysis
Avg. Element Size (fraction of model diameter)
Min. Element Size (fraction of avg. size)
Grading Factor
Max. Turn Angle
Create Curved Mesh Elements
0,02
0,05
1,1
60 deg
Yes
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Material(s)
Name
Steel F 114
Mass Density
Yield Strength
Ultimate Tensile Strength
Young' s Modulus
Poisson' s Ratio
Shear Modulus
EPRO_CUCHARA
General
Stress
Part Name(s)
7,15 g/cm^ 3
758 MPa
884 MPa
120,5 GPa
0,3 ul
46,3462 GPa
Operating conditions
In the next steps it is show n w hat and w here the loads are put. The pictures are clear
enough to understand w hat kind of loads are actuating in its face.
Force: 1
Load Type
Magnitude
Vector X
Vector Y
Vector Z
Force
339.000 N
0.000 N
0.000 N
339.000 N
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Force: 2
Load Type
Force
Magnitude
Vector X
Vector Y
Vector Z
679.000 N
0.000 N
0.000 N
679.000 N
Load Type
Force
Magnitude
Vector X
Vector Y
Vector Z
1764.000 N
1764.000 N
0.000 N
0.000 N
Selected Face(s)
Force: 3
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Fixed Constraint: 1
Constraint Type
Fixed Constraint
Selected Face(s)
Pin Constraint: 1
Constraint Type
Pin Constraint
Fix Radial Direction
Fix Axial Direction
Fix Tangential Direction
Yes
Yes
No
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Results
The results obtained are show n using three magnitudes of control
-Von Mises Stress: It reveals a combination of all kind of tensions that appear in each
point of the part
-Displacement: It show s how much the part is deformed
-Safety factor: Using the material given as a reference it makes the comparison
betw een the maximum stress admitted and the stress obtained in each point.
Result Summary
Name
Volume
Mass
Von Mises Stress
Displacement
Safety Factor
Minimum
Maximum
493055 mm^ 3
3,52534 kg
0,00000425949 MPa
307,96 MPa
0 mm
0,0703671 mm
2,46135 ul
15 ul
Figures
Von Mises Stress
Maximum combined stress point
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Displacement
Points w hich w ill be deformed w hen the maximum loads are applied
Safety Factor
The most important parameter, it show s the safety factor in each point of the part
w hen the maximum loads are applied. That analysis does not make difference
betw een the most critical points like the SLM because it takes the overall points of
the part to make the analysis.
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
A.5.-EPRO_GIRATORIA
Analyzed File:
EPRO_GIRATORIATESTS.ipt
Autodesk Inventor Version:
Creation Date:
Simulation Aut hor:
Summary:
2015 (Build 190159000, 159)
09/05/2016, 10:17
Román Dato Cuadrado
Project Info (iProperties)
Physical
The most significant material specifications of this parts w ere defined below
Mass
Area
Volume
Center of Gravity
7,48794 kg
172973 mm^ 2
983138 mm^ 3
x= 0,00000486377 mm
y= 43,8377 mm
z= -0,15053 mm
Simulation: 1
General objective and settings: This kind of analysis is the necessary to get the
strengths that appear in the studied part of the full w ind turbine
The single point objective is for solving every point in the part, and the st atic analysis
is opposite to the fatigue one, so the maximum loads act in certain moments.
Design Objective
Single Point
Simulation Type
Last Modification Date
Detect and Eliminate Rigid Body Modes
Separate Stresses Across Contact Surfaces
Motion Loads Analysis
Static Analysis
09/05/2016, 15:47
Yes
No
No
Mesh settings: These mesh settings w ere chosen according w ith the standards for that
kind of analysis
Avg. Element Size (fraction of model diameter)
Min. Element Size (fraction of avg. size)
Grading Factor
Max. Turn Angle
Create Curved Mesh Elements
Use part based measure for Assembly mesh
0,01
0,1
1,1
60 deg
Yes
Yes
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Material(s)
Name
Acero S355
Mass Density
7,73 g/cm^ 3
Yield Strength
355 MPa
Ultimate Tensile Strength
600 MPa
Young' s Modulus
205 GPa
Poisson' s Ratio
0,3 ul
Shear Modulus
78,8462 GPa
EPRO_BRIDA EPRO_EJEGIRATORIA
General
Stress
Part Name(s)
Operating conditions
In the next st eps it is show n w hat and w here the loads are put. The pictures are
clear enough to understand w hat kind of loads are actuating in its face.
Force: 1
Load Type
Force
Magnitude
Vector X
Vector Y
Vector Z
1873,700 N
-0,000 N
-1873,700 N
0,000 N
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Force: 2
Load Type
Force
Magnitude
Vector X
Vector Y
Vector Z
1360,000 N
1360,000 N
0,000 N
0,000 N
Selected Face(s)
Force: 3
Load Type
Force
Magnitude
Vector X
Vector Y
Vector Z
339,000 N
339,000 N
0,000 N
0,000 N
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Fixed Constraint: 1
Constraint Type
Fixed Constraint
Selected Face(s)
Results
The results obtained are show n using three magnitudes of control
-Von Mises Stress: It reveals a combination of all kind of tensions that appear in each
point of the part
-Displacement: It show s how much the part is deformed
-Safety factor: Using the material given as a reference it makes the comparison
betw een the maximum stress admitted and the stress obtained in each point.
Result Summary
Name
Volume
Mass
Von Mises Stress
Displacement
Safety Factor
Minimum
Maximum
983137 mm^ 3
7,48794 kg
0,0232978 MPa
89,8774 MPa
0 mm
0,113105 mm
3,94982 ul
15 ul
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Figures
Von Mises Stress
Maximum combined stress point
Displacement
Points w hich w ill be deformed w hen the maximum loads are applied
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Safety Factor
The most important parameter, it show s the safety factor in each point of the
part w hen the maximum loads are applied. That analysis does not make
difference betw een t he most critical points like the SLM because it takes the
overall points of the part to make the analysis.
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
A.6.-EPRO_GONDOLA
Analyzed File:
EPRO_GONDOLA.ipt
Autodesk Inventor Version:
Creation Date:
Simulation Author:
Summary:
2015 (Build 190159000, 159)
09/05/2016, 12:30
Román Dato Cuadrado
Project Info (iProperties)
Physical
The most significant material specifications of this parts w ere defined below
Material
Aluminum 356T6
Density
Mass
Area
Volume
2,7 g/cm^ 3
34,1382 kg
979287 mm^ 2
12643800 mm^ 3
x= -139,85 mm
y= -14,6386 mm
z= -0,0667279 mm
Center of Gravity
Simulation: 1
General objective and settings: This kind of analysis is the necessary to get the
strengths that appear in the studied part of the full w ind turbine
The single point objective is for solving every point in the part, and the static analysis
is opposite to the fatigue one, so the maximum loads act in certain moments.
Design Objective
Single Point
Simulation Type
Last Modification Date
Detect and Eliminate Rigid Body Modes
Static Analysis
09/05/2016, 12:37
No
Mesh settings:
These mesh settings w ere chosen according w ith the standards for that kind of
analysis
Avg. Element Size (fraction of model diameter)
Min. Element Size (fraction of avg. size)
Grading Factor
Max. Turn Angle
Create Curved Mesh Elements
0,051
0,092
1,5
60 deg
Yes
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Material(s)
Name
Aluminum 6061
Mass Density
Yield Strength
Ultimate Tensile Strength
Young' s Modulus
Poisson' s Ratio
Shear Modulus
EPRO_GONDOLA
General
Stress
Part Name(s)
2,7 g/cm^ 3
275 MPa
310 MPa
68,9 GPa
0,33 ul
25,9023 GPa
Operating conditions
In the next steps it is show n w hat and w here the loads are put. The pictures are
clear enough to understand w hat kind of loads are actuating in its face.
Moment: 1
Load Type
Moment
Magnitude
Vector X
Vector Y
Vector Z
170000.000 N mm
0.000 N mm
0.000 N mm
-170000.000 N mm
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
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Moment: 2
Load Type
Moment
Magnitude
Vector X
Vector Y
Vector Z
2205000.000 N mm
2205000.000 N mm
0.000 N mm
0.000 N mm
Load Type
Magnitude
Vector X
Vector Y
Vector Z
Force
702.000 N
-702.000 N
0.000 N
0.000 N
Selected Face(s)
Force: 1
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
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Force: 2
Load Type
Force
Magnitude
Vector X
Vector Y
Vector Z
702.000 N
702.000 N
0.000 N
0.000 N
Selected Face(s)
Fixed Constraint: 1
Constraint Type
Fixed Constraint
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
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Fixed Constraint: 1
Constraint Type
Fixed Constraint
Selected Face(s)
Pin Constraint: 1
Constraint Type
Pin Constraint
Fix Radial Direction
Fix Axial Direction
Fix Tangential Direction
Yes
Yes
No
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Results
The results obtained are show n using three magnitudes of control
-Von Mises Stress: It reveals a combination of all kind of tensions that appear in each
point of the part
-Displacement: It show s how much the part is deformed
-Safety factor: Using the material given as a reference it makes t he comparison
betw een the maximum stress admitted and the stress obtained in each point.
Reaction Force and Moment on Constraints
Constraint Name
Reaction Force
Magnitude
Component
(X,Y,Z)
Fixed restricction:1
1070,47 N
Fixed Constraint:1
9121,15 N
Pin Constraint:1
8625,66 N
-257,835 N
-849,721 N
597,822 N
-512,129 N
-396,492 N
-9098,12 N
769,795 N
1246,81 N
8500,29 N
Reaction Moment
Magnitude
Component
(X,Y,Z)
-781,212 N m
273,347 N m
33,7967 N m
-1423,61 N m
397,153 N m
41,6967 N m
0 Nm
446,117 N m
83,2969 N m
828,343 N m
1478,56 N m
453,827 N m
Result Summary
Name
Volume
Mass
Von Mises Stress
1st Principal Stress
3rd Principal Stress
Displacement
Safety Factor
Minimum
Maximum
12644300 mm^ 3
34,1396 kg
0,00286847 MPa
45,7223 MPa
-31,9007 MPa
53,2738 MPa
-78,6908 MPa
21,1258 MPa
0 mm
0,104102 mm
6,01457 ul
15 ul
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Figures
Von Mises Stress
Maximum combined stress point
Displacement
Points w hich w ill be deformed w hen the maximum loads are applied
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Safety Factor
The most important parameter, it show s the safety factor in each point of the part
w hen the maximum loads are applied. That analysis does not make difference
betw een the most critical points like the SLM because it takes the overall points of
the part to make the analysis.
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
A.7.-EPRO_PLATO
Analyzed File:
EPRO_PLATO.ipt
Autodesk Inventor Version:
Creation Date:
Simulation Author:
Summary:
2015 (Build 190159000, 159)
09/05/2016, 12:54
Román Dato Cuadrado
Project Info (iProperties)
Physical
The most significant mat erial specifications of this parts w ere defined below
Material
Aluminum 356T6
Density
Mass
Area
Volume
2,7 g/cm^ 3
3,33473 kg
150680 mm^ 2
1235090 mm^ 3
x= -0,0600538 mm
y= -0,00108793 mm
z= -17,0923 mm
Center of Gravity
Simulation: 1
General objective and settings: This kind of analysis is the necessary to get the
strengths that appear in the studied part of the full w ind turbine
The single point objective is for solving every point in the part, and the static analysis
is opposite to the fatigue one, so the maximum loads act in certain moments.
Design Objective
Single Point
Simulation Type
Last Modification Date
Detect and Eliminate Rigid Body Modes
Static Analysis
09/05/2016, 12:54
No
Mesh settings: These mesh settings w ere chosen according w ith the standards for that
kind of analysis
Avg. Element Size (fraction of model diameter)
Min. Element Size (fraction of avg. size)
Grading Factor
Max. Turn Angle
Create Curved Mesh Elements
0,05
0,05
1,1
60 deg
Yes
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Material(s)
Name
Aluminum 6061
Mass Density
Yield Strength
Ultimate Tensile Strength
Young' s Modulus
Poisson' s Ratio
Shear Modulus
EPRO_PLATO
General
Stress
Part Name(s)
2,7 g/cm^ 3
275 MPa
310 MPa
68,9 GPa
0,33 ul
25,9023 GPa
Operating conditions
In the next steps it is show n w hat and w here t he loads are put. The pictures are clear
enough to understand w hat kind of loads are actuating in its face.
Moment: 1
Load Type
Magnitude
Vector X
Vector Y
Vector Z
Moment
433000,000 N mm
0,000 N mm
0,000 N mm
433000,000 N mm
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Fixed Constraint: 1
Constraint Type
Fixed Constraint
Selected Face(s)
Frictionless Constraint: 1
Constraint Type
Frictionless Constraint
Selected Face(s)
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Results
The results obtained are show n using three magnitudes of control
-Von Mises Stress: It reveals a combination of all kind of tensions that appear in each
point of the part
-Displacement: It show s how much the part is deformed
-Safety factor: Using the material given as a reference it makes the comparison
betw een the maximum stress admitted and the stress obtained in each point.
Reaction Force and Moment on Constraints
Constraint Name
Reaction Force
Magnitude
Component
(X,Y,Z)
Fixed Constraint:1
17620,1 N
Frictionless
Constraint:1
17623,4 N
2736,19 N
-17406,3 N
34,8316 N
-2733,21 N
17410,1 N
-35,4464 N
Reaction Moment
Magnitude
Component
(X,Y,Z)
135,509 N m
134,927 N m
129,943 N m
24,8565 N m
-29,3202 N m
-130,347 N m
-24,1337 N m
25,1464 N m
Result Summary
Name
Volume
Mass
Von Mises Stress
1st Principal Stress
3rd Principal Stress
Displacement
Safety Factor
Minimum
Maximum
1235130 mm^ 3
3,33485 kg
0,00410328 MPa
0,00410328 MPa
-10,2799 MPa
83,8409 MPa
-96,7552 MPa
18,5053 MPa
0 mm
0,0596551 mm
2,96667 ul
15 ul
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Figures
Von Mises Stress
Maximum combined stress point
Displacement
Points w hich w ill be deformed w hen the maximum loads are applied
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18
ENAIR ENERGY S.L.
info@enair.es - www.enair .es
Safety Factor
The most important parameter, it show s the safety factor in each point of the part
w hen the maximum loads are applied. That analysis does not make difference
betw een the most critical points like the SLM because it takes the overall points of
the part to make the analysis.
ENAIR ENERGY S.L. CIF- B54483656 C/Campello,19 Castalla (Alicante) +34 96 556 00 18