DESIGN IMPROVISATION OF ELECTROMECHANICAL ACTUATORS FOR OPERATION AT SUB ZERO...ijmech
Control surface actuators are the key systems in any flight vehicle for enabling a strict control on the flight
parameters. The electromechanical actuator developed for an Unmanned aerial vehicle (UAV) is subjected
to sub-zero temperatures due to the altitude of operation. This paper discusses on how an actuator
developed is studied experimentally and improvised in design to ensure performance at -40oC. The
experimental observations are reasoned and supported by theoretical studies and remedial measures
incorporated to improve the actuator performance.
Experimental and numerical stress analysis of a rectangular wing structureLahiru Dilshan
Structures of an aircraft can be categorised as primary structural components and secondary structure components. Primary structure components are the components which lead to failure of the aircraft if such component is failed during the flight cycle. Secondary components are load sharing components in an aircraft but will not pave the way to catastrophic failure.
Designing aircraft structures should follow several strategies to assure safety. For that, there are three main methods used in designing and maintenance procedures. First one is the safe flight, which an aircraft component has a lifetime. That component is not used beyond that limit and should replace though it is not failed. The fail-safe method is another one that redundant systems or components are there to ensure there is another way to carry the load or do necessary control. The final one is the damage tolerance which measures the current damages are within acceptable limit and carry out the main functions until the next main maintenance process.
To determine the safety of a structure component load distribution, stress and strain variation, deflection can be used as parameters to make sure that component can withstand maximum allowable load with safety factor. There are several techniques used to get accurate results as numerical methods, Finite Element Method (FEM) and experimental methods. In the design process, those three steps are followed in an orderly manner to ensure the safety of an aircraft.
Fatigue Life Assessment for Power Cables in Floating Offshore Wind TurbinesFranco Bontempi
https://www.mdpi.com/journal/energies/special_issues/Wave_Tidal_Wind_Converters
Abstract: In this paper, a procedure is proposed to determine the fatigue life of the electrical cable connected to a 5MWfloating offshore wind turbine, supported by a spar-buoy at a water depth of 320 m, by using a numerical approach that takes into account site-specific wave and wind characteristics.
The efect of the intensity and the simultaneous actions of waves and wind are investigated and the outcomes for specific cable configurations are shown. Finally, the fatigue life of the cable is
evaluated. All analyses have been carried out using the Ansys AQWA computational code, which is a commercial code for the numerical investigation of the dynamic response of floating and fixed marine structures under the combined action of wind, waves and current. Furthermore, this paper applies the FAST NREL numerical code for comparison with the ANSYS AQWA results.
Keywords: wind energy; floating offshore wind turbine; dynamic analysis; fatigue life assessment; flexible power cables.
DESIGN IMPROVISATION OF ELECTROMECHANICAL ACTUATORS FOR OPERATION AT SUB ZERO...ijmech
Control surface actuators are the key systems in any flight vehicle for enabling a strict control on the flight
parameters. The electromechanical actuator developed for an Unmanned aerial vehicle (UAV) is subjected
to sub-zero temperatures due to the altitude of operation. This paper discusses on how an actuator
developed is studied experimentally and improvised in design to ensure performance at -40oC. The
experimental observations are reasoned and supported by theoretical studies and remedial measures
incorporated to improve the actuator performance.
Experimental and numerical stress analysis of a rectangular wing structureLahiru Dilshan
Structures of an aircraft can be categorised as primary structural components and secondary structure components. Primary structure components are the components which lead to failure of the aircraft if such component is failed during the flight cycle. Secondary components are load sharing components in an aircraft but will not pave the way to catastrophic failure.
Designing aircraft structures should follow several strategies to assure safety. For that, there are three main methods used in designing and maintenance procedures. First one is the safe flight, which an aircraft component has a lifetime. That component is not used beyond that limit and should replace though it is not failed. The fail-safe method is another one that redundant systems or components are there to ensure there is another way to carry the load or do necessary control. The final one is the damage tolerance which measures the current damages are within acceptable limit and carry out the main functions until the next main maintenance process.
To determine the safety of a structure component load distribution, stress and strain variation, deflection can be used as parameters to make sure that component can withstand maximum allowable load with safety factor. There are several techniques used to get accurate results as numerical methods, Finite Element Method (FEM) and experimental methods. In the design process, those three steps are followed in an orderly manner to ensure the safety of an aircraft.
Fatigue Life Assessment for Power Cables in Floating Offshore Wind TurbinesFranco Bontempi
https://www.mdpi.com/journal/energies/special_issues/Wave_Tidal_Wind_Converters
Abstract: In this paper, a procedure is proposed to determine the fatigue life of the electrical cable connected to a 5MWfloating offshore wind turbine, supported by a spar-buoy at a water depth of 320 m, by using a numerical approach that takes into account site-specific wave and wind characteristics.
The efect of the intensity and the simultaneous actions of waves and wind are investigated and the outcomes for specific cable configurations are shown. Finally, the fatigue life of the cable is
evaluated. All analyses have been carried out using the Ansys AQWA computational code, which is a commercial code for the numerical investigation of the dynamic response of floating and fixed marine structures under the combined action of wind, waves and current. Furthermore, this paper applies the FAST NREL numerical code for comparison with the ANSYS AQWA results.
Keywords: wind energy; floating offshore wind turbine; dynamic analysis; fatigue life assessment; flexible power cables.
Longitudinal static stability of boeing 737 max 8Lahiru Dilshan
Recently there were two aircraft crashes, Lion Air and Ethiopian airline crash with 346 people with the flight crew. Ethiopian aircraft incident is currently under investigation and the final report will be published in near future and the Lion Air incident report was published.
Both these aircrafts were in the same type aircraft, Boeing 737 MAX 8, brand new aircraft that introduced very recently for commercial use. There several design modifications and several new systems were included for that aircraft by the designers and manufacturers.
EFFECTS OF TRANSIENT LOAD ONGASTURBINE BLADE STRESS AND FATIGUE LIFE CHARACTE...Barhm Mohamad
The turbine blade is the most important component in the jet engine gas turbine. The common fatigue
failures of the blade include the thermo-mechanical fatigue. Firstly, the finite element simulation of
the blade is carried out in the working condition including the centrifugal load and mechanical load.
The aim of this work was to develop and implement methods for the resource calculation of the jet
turbine blade in which fatigue zone were detected during the load. The approach is based on a directstep
simulation of the load point based on the finite-element method (FEM).According to the
simulation results of the thermos-mechanical load, the stress distribution of the blade body is
reasonable in the working condition load; the stress level on the blade suction surface is higher than
the pressure surface; in the blade body, the maximum Von Mises stress is 126 MPa, and the location
of the minimum fatigue life is close to the blade shroud. Above simulation results is very useful for
the structural design and fatigue experiment. Secondly, the stress and thermo-mechanical fatigue life
characteristic are both analyzed with ANSYS software. Through the transient structure stress analysis,
the stress-time history in the blade body is obtained; through the thermo-mechanical fatigue analysis,
the fatigue zone of the blade first appears in the middle of the blade exhaust side. Based on these
virtual results. These results are significant for the blade fatigue failure in the future.
Transient three dimensional cfd modelling of ceilng fanLahiru Dilshan
Ceiling fans are used to get thermal comfort, especially in tropical countries. With the increment of the usage of air conditioners, the emission of CO2 is increased. But ceiling fans are a limited solution, that saves much energy compared to air conditioners. Ceiling fans generate a non-uniform velocity profile, so that, there is a non-uniform thermal environment. That non-uniform environment does not imply lower thermal comfort, that will give enough thermal comfort with low energy cost by air velocity. Hence, there will be difficulties of analysing with simple modelling techniques in that environment. So, to predict the performance of the ceiling fan required more accurate models.
The accurate model of a ceiling fan will generate complex geometry that makes difficulties for the simulation process and requires higher computational power. Because of that, there are several methods used to predict the performance of the ceiling fan using mathematical techniques but that will give an estimated value of properties in the surrounding.
Fighter Performance in Practice: F-4 Phantom vs MiG-21mishanbgd
Book Reviews -
If you want to know who really has the better performance F-4 or MiG-21, who is more maneuverable or faster, you can find it only in this book based on official aircraft manuals.
Who is faster or more agile operationaly and who is on paper can be seen only in this book.
I'm working like performance test engineer for Airbus, after work for Lockheed Martin.
I congratulate you for your book. It's good and specially there are not another book like this in the market.
What I read is very good, with precision, you have focused in a good point of view of analysis. I would like to be so good as you to compare 2 aircraft !!! )
It's really a good job.
I hope 2012. will be the year when you will offer a new and excellent publication about aircraft !! )
Whiskey Golf
Fighter jet design and performance calculations by using the case studies.Mani5436
1.Fighter jet theoretical calculations by using previous calculations.
2. Case study of the fighter jet
3. Configuration selection of the fighter jet
4. Aircraft Performance
The International Journal of Engineering and Science (The IJES)theijes
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
Effect of Spray Quenching Rate on Distortion and Residual Stresses during Ind...Fluxtrol Inc.
http://fluxtrol.com
Computer simulation is used to predict the residual stresses and distortion of a full-float truck axle that has been
induction scan hardened. Flux2D® is used to model the electromagnetic behavior and the power distributions inside
the axle in terms of time. The power distributions are imported and mapped into DANTE® model for thermal, phase
transformation and stress analysis. The truck axle has three main geometrical regions: the flange/fillet, the shaft, and
the spline. Both induction heating and spray quenching processes have significant effect on the quenching results: distortion and residual stress distributions. In this study, the effects of spray quenching severity on residual stresses and distortion are investigated using modeling.
This document presents an example of analysis design of slab using ETABS. This example examines a simple single story building, which is regular in plan and elevation. It is examining and compares the calculated ultimate moment from CSI ETABS & SAFE with hand calculation. Moment coefficients were used to calculate the ultimate moment. However it is good practice that such hand analysis methods are used to verify the output of more sophisticated methods.
Also, this document contains simple procedure (step-by-step) of how to design solid slab according to Eurocode 2.The process of designing elements will not be revolutionised as a result of using Eurocode 2. Due to time constraints and knowledge, I may not be able to address the whole issues.
This paper explores the fundamental characteristics of medium to high capacity load cells and how they are affected by the types and implementation of strain gages.
Longitudinal static stability of boeing 737 max 8Lahiru Dilshan
Recently there were two aircraft crashes, Lion Air and Ethiopian airline crash with 346 people with the flight crew. Ethiopian aircraft incident is currently under investigation and the final report will be published in near future and the Lion Air incident report was published.
Both these aircrafts were in the same type aircraft, Boeing 737 MAX 8, brand new aircraft that introduced very recently for commercial use. There several design modifications and several new systems were included for that aircraft by the designers and manufacturers.
EFFECTS OF TRANSIENT LOAD ONGASTURBINE BLADE STRESS AND FATIGUE LIFE CHARACTE...Barhm Mohamad
The turbine blade is the most important component in the jet engine gas turbine. The common fatigue
failures of the blade include the thermo-mechanical fatigue. Firstly, the finite element simulation of
the blade is carried out in the working condition including the centrifugal load and mechanical load.
The aim of this work was to develop and implement methods for the resource calculation of the jet
turbine blade in which fatigue zone were detected during the load. The approach is based on a directstep
simulation of the load point based on the finite-element method (FEM).According to the
simulation results of the thermos-mechanical load, the stress distribution of the blade body is
reasonable in the working condition load; the stress level on the blade suction surface is higher than
the pressure surface; in the blade body, the maximum Von Mises stress is 126 MPa, and the location
of the minimum fatigue life is close to the blade shroud. Above simulation results is very useful for
the structural design and fatigue experiment. Secondly, the stress and thermo-mechanical fatigue life
characteristic are both analyzed with ANSYS software. Through the transient structure stress analysis,
the stress-time history in the blade body is obtained; through the thermo-mechanical fatigue analysis,
the fatigue zone of the blade first appears in the middle of the blade exhaust side. Based on these
virtual results. These results are significant for the blade fatigue failure in the future.
Transient three dimensional cfd modelling of ceilng fanLahiru Dilshan
Ceiling fans are used to get thermal comfort, especially in tropical countries. With the increment of the usage of air conditioners, the emission of CO2 is increased. But ceiling fans are a limited solution, that saves much energy compared to air conditioners. Ceiling fans generate a non-uniform velocity profile, so that, there is a non-uniform thermal environment. That non-uniform environment does not imply lower thermal comfort, that will give enough thermal comfort with low energy cost by air velocity. Hence, there will be difficulties of analysing with simple modelling techniques in that environment. So, to predict the performance of the ceiling fan required more accurate models.
The accurate model of a ceiling fan will generate complex geometry that makes difficulties for the simulation process and requires higher computational power. Because of that, there are several methods used to predict the performance of the ceiling fan using mathematical techniques but that will give an estimated value of properties in the surrounding.
Fighter Performance in Practice: F-4 Phantom vs MiG-21mishanbgd
Book Reviews -
If you want to know who really has the better performance F-4 or MiG-21, who is more maneuverable or faster, you can find it only in this book based on official aircraft manuals.
Who is faster or more agile operationaly and who is on paper can be seen only in this book.
I'm working like performance test engineer for Airbus, after work for Lockheed Martin.
I congratulate you for your book. It's good and specially there are not another book like this in the market.
What I read is very good, with precision, you have focused in a good point of view of analysis. I would like to be so good as you to compare 2 aircraft !!! )
It's really a good job.
I hope 2012. will be the year when you will offer a new and excellent publication about aircraft !! )
Whiskey Golf
Fighter jet design and performance calculations by using the case studies.Mani5436
1.Fighter jet theoretical calculations by using previous calculations.
2. Case study of the fighter jet
3. Configuration selection of the fighter jet
4. Aircraft Performance
The International Journal of Engineering and Science (The IJES)theijes
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
Effect of Spray Quenching Rate on Distortion and Residual Stresses during Ind...Fluxtrol Inc.
http://fluxtrol.com
Computer simulation is used to predict the residual stresses and distortion of a full-float truck axle that has been
induction scan hardened. Flux2D® is used to model the electromagnetic behavior and the power distributions inside
the axle in terms of time. The power distributions are imported and mapped into DANTE® model for thermal, phase
transformation and stress analysis. The truck axle has three main geometrical regions: the flange/fillet, the shaft, and
the spline. Both induction heating and spray quenching processes have significant effect on the quenching results: distortion and residual stress distributions. In this study, the effects of spray quenching severity on residual stresses and distortion are investigated using modeling.
This document presents an example of analysis design of slab using ETABS. This example examines a simple single story building, which is regular in plan and elevation. It is examining and compares the calculated ultimate moment from CSI ETABS & SAFE with hand calculation. Moment coefficients were used to calculate the ultimate moment. However it is good practice that such hand analysis methods are used to verify the output of more sophisticated methods.
Also, this document contains simple procedure (step-by-step) of how to design solid slab according to Eurocode 2.The process of designing elements will not be revolutionised as a result of using Eurocode 2. Due to time constraints and knowledge, I may not be able to address the whole issues.
This paper explores the fundamental characteristics of medium to high capacity load cells and how they are affected by the types and implementation of strain gages.
Principles of Cable Sizing; current carrying capacity, voltage drop, short circuit.
Cables are often the last component considered during system design even if in many situations cables are the true system’s lifeline: if a cable fails, the entire system may stop. Cable reliability is therefore extremely important, then a cable system should be engineered to last the life of the system in the installation environment for the required application. Environments in which cable systems are being used are often challenging, as extreme temperatures, chemicals, abrasion, and extensive flexing. These variables have a direct impact on the materials used for cable insulation and jacketing as well as the construction of the cable. Using a systematic approach will help ensure that designer select the best cable for the required application in the installation environment. This lessons will provide students main guidelines for perform this approach.
Proper derating can mitigate premature wear-out of electronic components in the power circuits.
Recommended standard derating factors outlined in IPC-9592B Section 4.3 and Appendix A.
Wear out and examples of life estimation for MLCC and aluminum electrolytic capacitors used in filter applications will be discussed
ASTM developed a collection of documents called material specifications for
standardizing materials of large use in the industry.
• Specifications starting with “A” are for steel.
• Specifications starting with “B” are for non-ferrous alloys (bronze, brass,
copper nickel alloys, aluminum alloys and so on).
• Specifications starting with “D” are for plastic material, as PVC.
An ASTM specification specifies the basic chemical composition of material and the
process through which the material is shaped into the final product. Some of the
common material standards are
This paper compares the performances of standard surrogate models in the development of an optimal control framework. The optimal control strategy is implemented on an Active Thermoelectric (ATE) window design. The ATE window design uses thermoelectric units to actively regulate the overall thermodynamic properties of the windows. The optimization of the design is a multiobjective problem, where both the heat transferred through the window and electric power consumption are minimized. The power supplies and the heat transfer are optimized under a reasonable number of randomly sampled environmental conditions. The subsequent optimal designs obtained are represented as functions of the corresponding environmental conditions using surrogate models. To this end, four types of surrogate models are used, namely, (i) Quadratic Response Surface Methodology (QRSM), (ii) Radial Basis Functions (RBF), (iii) Extended Radial Basis Functions (E-RBF), and (iv) Kriging. Their performances are compared using two accuracy measurement metrics: Root Mean Squared Error (RMSE) and Maximum Absolute Error (MAE). We found that any one of the surrogate modeling methods is not superior to the others over the whole domain for the optimal control of the ATE window.
1. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
1
ITER MID ELM
FOUNDATION & BOLT LOADS STUDY
Parametric Stress Analysis
February 24, 2011
2. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Objectives
• Determine All Loads & Moments for the Mid Elm
– Summarize all loads at local coordinate systems at each foundation pad
– Repeat the evaluation for each of the three load steps (See PDR Update 12-2-10)
• Provide Tabular summaries of the Foundation loads for all three load cases.
– First Load Step is Thermal Loads
– Second Load Step is combined Thermal + Lorentz Load Toward Reactor Foundation Wall
– Third Load Step is combined Thermal + Lorentz Load Toward Plasma
• Provide a hand calculation of the Poloidal Foundation stress
• Provide Tabular summaries of the loads on the Poloidal & Corner Brackets
– Apply these loads to Sub-Models of the brackets with bolt details defined.
– Evaluate the Current Foundation Rail Stresses with all three load cases
– Evaluate the Bolt loads on these brackets with all three load cases
• Complete a Design of Experiments Optimization of the Poloidal Bracket Rail
– Parametrically adjust the length of the foundation rail width
– Illustrate sensitivity charts and response envelopes of the bolts and rail stresses as a
function of these changes
– Identify several candidate designs that will minimize the rail stresses
• Evaluate the Corner Bracket Rails based on the current design
• Provide conclusions and recommendations
3. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
PDR -ASSUMPTIONS
• The interface between the MGO insulation and the Coil is assumed to be
bonded contact.
– Conservative since transverse Lorentz loads could cycle the coil in tension.
– Additional work to characterize and calibrate the load transfer is in process.
• A reference temperature of 100 C is applied to all materials.
– This accounts for displacements of the reactor to boundary interface.
• Error is small since thermal expansion coefficients are similar
– Future work will map boundary thermal displacements with APDL script
• Additional reactor displacement to be added based on 100 C temperatures.
• Bonded thermal Contact is assumed between the brackets and coils
although mechanical constraint is limited to end points
• Surrounding Blanket and reactor structures are uniform 100 C
• All analysis is steady state
3
4. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Allowables and Acceptance Criteria
100C 200C 100C 200C
Primary Stress (PM, PL, PB)
General Primary Membrane 1.0 K Sm 120 108 147 130
Local primary membrane 1.5 K Sm 180 162 220.5 195
Primary Membrane plus bending 1.5 K Sm 180 162 220.5 195
Secondary (Q) (ie thermal) 3.0 K Sm 360 324 441 390
CuCrZr-IG 316L(N)-IG
Metalic Structure Acceptance Criteria (SDC-IC Appendix D)
Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
ITER_D_3VY7G5 V1.2
Max Shear Strength = 147/2 = 73.5Mpa = 10,660 Psi
5. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
FOUNDATION LOAD ANALYSIS
The PDR version (12-2-10) of the MID ELM is used to evaluate the foundation loads
POLOIDAL BRACKETCORNER BRACKET
Rigid Foundation at all supports
Loads Calculated at the Interface to the reactor vessel
Symmetric Constraint
Symmetric Constraint
5
6. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
ELM LORENTZ LOAD VS POSITION
Applied Maximum Lorentz Loads For Stress Range Calculation
(LFT)
(BOT)
(RHT)(TRC) (BLC)
Critical Quadrant
SECTOR 5 FE MODEL
LOADS in GLOBAL
COORDINATES
Fx Fy Fz
ELM_MD_BOT 121,508 60,907 -32,429
ELM_MD_BLC 105,447 77,208 -41,265
ELM_MD_LFT 236,652 185,166 7,491
OPPOSITE DIRECTION LOADING
ELM_MD_BOT -121,508 -60,907 +32,429
ELM_MD_BLC -105,447 -77,208 +41,265
ELM_MD_LFT -236,652 -185,166 -7491
(BRC)
6
7. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
TOROIDAL BRACKET
Reaction Coordinate Systems
The Toroidal Bolt Reaction Load Coordinate Systems are Defined
+z
+Y
+x
Coordinate System #180
Coordinate System #181
8. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Corner Bracket
Reaction Coordinate Systems
The Corner Bracket Bolt Reaction Load Coordinate Systems are Defined for the Bolt Pad and
on the Foundation
+z
+Y
+x
Lorentz Load
Mxx = 4,463 NM
Load step #3
Mxx = -850 NM
Load step #3
Coordinate System #182Coordinate System #183
9. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Poloidal Bracket
Reaction Coordinate Systems
+z
+Y
+x
The Poloidal Bolt Reaction Load Coordinate Systems are Defined at the Bolt Pad and on
the Foundation
Coordinate System #184Coordinate System #185
10. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Foundation Pad Loads
** All loads are on foundation, reaction loads would have a reversed sign Highest Load Areas
12. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
POLOIDAL FOUNDATION
COMPLEX – BENDING / SHEAR
12
Note: My : references Mz in loads
-7,053 psi = -48.6 Mpa
See Slide 18 for FE
Comparison 39 Mpa – 53 Mpa
13. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
13
POLOIDAL FOUNDATION
COMPLEX – BENDING / SHEAR
Note: Vy : references Vz in loads
Note: My : references Mz in loads
Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
Temperature 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323
Minimum Yield Strength, Sy 253 235
Design Stress Intensity Limit, Sm 120 108
108 97
Stress Limits (SDC -IC), MPa
CuCrZr-IG
Stress Endurance Limit, Se (=30% Su)
Design Stress Limits
The hand calculations Show the Rail Stress is Acceptable
Directly at the foundation interface
14. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Foundation/ Bolt Pad Analysis
14
POLOIDAL LOADS ON TOP OF COMB
CORNER LOADS ON TOP OF COMB
15. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Poloidal Bolt / Foundation
Boundary Conditions
15
OUTSIDEINSIDE
BOLT1
BOLT3
BOLT4
* Preload is 182,000 N = 40,915 Lbf
16. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Poloidal Bolt / Foundation
Thermal Stress
16
The Average Poloidal Foundation Thermal Stresses are in excess of the Material Limits –
primarily around the top section of the rail.
21e6 Pa = 3,045 psi
Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
Temperature 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323
Minimum Yield Strength, Sy 253 235
Design Stress Intensity Limit, Sm 120 108
108 97
Stress Limits (SDC -IC), MPa
CuCrZr-IG
Stress Endurance Limit, Se (=30% Su)
8.5e6 Pa = 1,232 psi
STRESS INTENSITY NORMAL STRESS
133e6 Pa = 19,290 psi 169e6 Pa = 24,511 psi
17. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Poloidal Bolt / Foundation
Thermal Stress + Lorentz Away From Plasma
17
The Average Poloidal Foundation Thermal +Lorentz Stresses are in excess of material
limits – primarily around the top section of the rail.
8e6 Pa = 1,160 psi Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
Temperature 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323
Minimum Yield Strength, Sy 253 235
Design Stress Intensity Limit, Sm 120 108
108 97
Stress Limits (SDC -IC), MPa
CuCrZr-IG
Stress Endurance Limit, Se (=30% Su)
56e6 Pa = 8,122 psi
STRESS INTENSITY NORMAL STRESS
189e6 Pa = 27,412 psi 260e6 Pa = 37,709 psi
18. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Poloidal Bolt / Foundation
Thermal Stress + Lorentz Toward Plasma
18
The Average Poloidal Foundation Thermal +Lorentz Stresses are in excess of the stress
limits – primarily on the top section of the rails.
87e6 Pa = 12,618 psi
Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
Temperature 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323
Minimum Yield Strength, Sy 253 235
Design Stress Intensity Limit, Sm 120 108
108 97
Stress Limits (SDC -IC), MPa
CuCrZr-IG
Stress Endurance Limit, Se (=30% Su)
92e6 Pa = 13,343 psi
STRESS INTENSITY NORMAL STRESS
189e6 Pa = 27,412 psi 272e6 Pa = 39,450 psi
19. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Normal Bolt Stress
19
Thermal + Lorentz
Toward Plasma
Thermal + Lorentz
Away From Plasma
210,000 N = 47,209 Lbf
172,000 N = 38,667 Lbf
The Load on Bolts 2 and 3 has excessive variation (8,542 Lbf) and will require a higher
preload or more bolts –The clamping force is not sufficient
Preload = 182,000 N = 40,915 Lbf
20. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Poloidal Foundation
Parametric Study
20
OBJECTIVES:
1.) Use Load Step #3 (Lorentz Loads Toward Plasma) + Bolt Preloading
2.) Adjust the foundation width parameters and determine the impact on:
a.) The bolt working loads
b.) The foundation interface stress
c.) The rail & Attachment Stresses
3.) Make a recommendation based on these trends to assure an adequate design
21. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Geometric Parameters
21
Smallest Option Evaluated Intermediate Option Evaluated
Largest Option Evaluated
Inside Rail Dimension
0.0 to 15.5 mm
Outside Rail Dimension
55.0 to 65 mm
22. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Sensitivity Charts for Bolt Loading
22
Similar Sensitivity on Bolt 4 and Bolt 3 for both rails
Bolt 1 and Bolt 2 are most influenced by the Inside Rail Length
Inside Rail
Outside Rail
Bolt 1Bolt 2
Bolt 3Bolt 4
Local Sensitivity Chart is based on Outside Rail 60 mm & Inside Rail = 8 mm; Preload = 2.184e5 N
23. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Foundation Stress Sensitivity for Rail Parameter
Changes
23
Out Equiv Stress Inside Equiv Stress
Outside Stress
Intensity
Inside Stress
Intensity
Inside Rail
Outside Rail
The Inside Rail Dimension has the Largest Impact on the Foundation Stresses
Reduce foundation stress by changing inside rail dimensions
Local Sensitivity Chart is based on Outside Rail 60 mm & Inside Rail = 8 mm; Preload = 2.184e5 N
24. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Stress Minimum Value
24
The Rail Dimensions Required to Minimize the Foundation Stress
Outside Rail of 60 mm and inside Rail 10 mm
** Table assumes a bolt preload of 218,400 N (49,098 Lbf) and applied Lorentz load toward plasma
25. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Bolt Load Minimum Value
25
The Rail Dimensions Required to Minimize the Max Working Load of Bolt
Outside Rail of 60 mm and inside Rail 10 mm
** Table assumes a bolt preload of 218,400 N (49,098 Lbf) and applied Lorentz load toward plasma
26. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Bolt #1 Working Load - Response Envelope
Function of Rail Width Changes
26
Inside > 8mm
Outside = anything
Load =2.184 e5 N = 49,098 Lbf
Bolt Pre-Load 2.184 e5 N
Setting Outside Rail to anything if the inside railis greater than 8 mm
Results in all working bolt loads of about 49,098 Lbf (very low fatigue Load range)
Preload = 2.184e5 N = 49,098 Lbf
27. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Bolt #2 Working Load - Response Envelope
Function of Rail Width Changes
27
Inside > 10 mm
Outside > 58 mm
Load =2.189 e5 N = 49,210 Lbf
Bolt Pre-Load 2.184 e5 N
Setting Inside Rail Greater than 10 mm and the Outside Rail 58 mm or greater
Results in all working bolt loads of about 49,210 Lbf (fatigue Load range of 112 Lbf)
Preload = 2.184e5 N = 49,098 Lbf
28. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Bolt #3 Working Load - Response Envelope
Function of Rail Width Changes
28
If Inside = 8 mm then
Outside = 60
Load =2.196 e5 N = 49,368 Lbf
Setting Inside Rail Greater than 8 mm and the Outside Rail 60 mm or greater
Results in all working bolt loads of about 49,368 Lbf ( 270 lbf fatigue Load range)
Bolt Pre-Load 2.185 e5 N
Preload = 2.184e5 N = 49,098 Lbf
29. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Bolt #4 Working Load - Response Envelope
Function of Rail Width Changes
29
Inside = 8 mm
Outside = 60
Load =2.189 e5 N = 49,210 Lbf
Setting Inside Rail is 8 mm and the Outside Rail 60 mm or greater
Results in all working bolt loads of about 49,210 Lbf ( 112 lbs working fatigue load)
Preload = 2.184e5 N = 49,098 Lbf
30. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Inside Foundation Face - Stress Intensity
30
Setting Inside Rail to 8 mm and the Outside Rail 60 mm
Results in a local minimum on the stress intensity of 101 Mpa which meets the criteria
If Inside = 8 mm then
Outside = 60 mm
Stress Intensity = 101 Mpa
100C 200C 100C 200C
nsile Strength, Su 359 323 458 425
th, Sy 253 235 172 144
Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
, Se (=30% Su)
Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
31. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Outside Foundation Face - Stress Intensity
31
Setting Inside Rail Greater to 8 mm and the Outside Rail 60 mm
Results in a local minimum on the stress intensity 77 Mpa which meets the criteria
If Inside = 8 mm
Outside = 60 mm
Stress Intensity = 77 Mpa
100C 200C 100C 200C
nsile Strength, Su 359 323 458 425
th, Sy 253 235 172 144
Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
, Se (=30% Su)
Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
Current Design Approximated by this region 132 Mpa
32. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Optimization Candidates
to Minimize Foundation Rail Stress
32
Rail Dimensions Outside
Foundation Stress
Inside Foundation
Stress
Outside Stress
Intensity
Inside Stress
Intensity
Rail Dimensions Bolt Working Loads
(N)
Three Design Candidates Have Been Identified with the Optimizer
33. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Optimized Poloidal / Foundation
Increased Preload = 2.184e5 N = 49,048 Lbf
Outside Rail = 60 mm Inside Rail = 10 mm
33
34. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Poloidal Bolt / Foundation
Thermal Stress + Lorentz Away from Plasma
(Increased Pre-load)
34
The Average Poloidal Foundation Thermal +Lorentz Stresses are in excess of the stress
limits – primarily on the top section of the rails with Increased preloads
Addition of additional bolt should solve this concentration
290e6 Pa = 42,060 psi
Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
Temperature 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323
Minimum Yield Strength, Sy 253 235
Design Stress Intensity Limit, Sm 120 108
108 97
Stress Limits (SDC -IC), MPa
CuCrZr-IG
Stress Endurance Limit, Se (=30% Su)
22e6 Pa = 3,190 psi
STRESS INTENSITY NORMAL STRESS
153e6 Pa = 22,190 psi
160e6 Pa = 23,206 psi
35. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Poloidal Bolt / Foundation
Thermal Stress + Lorentz Toward Plasma
(Increased Pre-load)
35
The Average Poloidal Foundation Thermal +Lorentz Stresses are in excess of material limits –
primarily around the top section of the rail with increasing preload
Addition of an extra bolt should eliminate the bending issues
211e6 Pa = 30,603 psi
Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
Temperature 100C 20
Minimum Ultimate Tensile Strength, Su 359 32
Minimum Yield Strength, Sy 253 23
Design Stress Intensity Limit, Sm 120 10
108 9
Stress Limits (SDC -IC), MPa
CuCrZr-IG
Stress Endurance Limit, Se (=30% Su)
88e6 Pa = 12,763 psi
STRESS INTENSITY NORMAL STRESS
36. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Poloidal Bolt / Foundation
Thermal Stress + Lorentz Toward Plasma
(Increased Pre-load)
36
The Preload (49,098 lbf or100,828 psi ) is not sufficient to maintain clamp load
Additional bolt will be required for Poloidal Rail
Total Displacement Contact Stress
No Contact
37. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Bolt Load vs. Load Step
37
Thermal + Lorentz
Away From Plasma
234,220 N = 52,654 Lbf
The Load on Bolts 3 and 4 has much lower load variation (3,556 lbf)
From increasing preload as expected
Preload = 218,400 N = 49,098Lbf
Thermal + Lorentz
Toward Plasma
Bolt Load Result is based on Outside Rail 60 mm & Inside Rail = 8 mm; Preload = 2.184e5 N
39. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Rigid Foundation
Corner Bolt / Foundation
Boundary Conditions
40. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Hex Dominant Mesh is complete on the corner Bracket
Corner Bolt / Foundation
Mesh
41. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Corner Bolt / Foundation
Thermal Stress
41
The Average Poloidal Foundation Thermal Stresses are in excess of the material Limits
On the top section of the Rail - See next Slide
106e6 Pa = 15,374 psi Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
Temperature 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323
Minimum Yield Strength, Sy 253 235
Design Stress Intensity Limit, Sm 120 108
108 97
Stress Limits (SDC -IC), MPa
CuCrZr-IG
Stress Endurance Limit, Se (=30% Su)
STRESS INTENSITY NORMAL STRESS
42. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Corner Bolt / Foundation
Thermal Stress
42
The Average Poloidal Foundation Thermal Stresses exceed the material limits
for Stress Intensity and Fatigue Limits
164e6 Pa = 23,786 psi
Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
Temperature 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323
Minimum Yield Strength, Sy 253 235
Design Stress Intensity Limit, Sm 120 108
108 97
Stress Limits (SDC -IC), MPa
CuCrZr-IG
Stress Endurance Limit, Se (=30% Su)
-144e6 Pa = 20,885psi
STRESS INTENSITY NORMAL STRESS
43. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Corner Bolt / Foundation
Thermal Stress + Lorentz Away From Plasma
Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
Temperature 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323
Minimum Yield Strength, Sy 253 235
Design Stress Intensity Limit, Sm 120 108
108 97
Stress Limits (SDC -IC), MPa
CuCrZr-IG
Stress Endurance Limit, Se (=30% Su)
The Corner Foundation has Stress Intensity that is not within the Material Limits
A thicker width rail or gusset will be required
-95e6 Pa = -13,778 psi
196e6 Pa = -28,427 psi
STRESS INTENSITY
NORMAL STRESS
44. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Corner Bolt / Foundation
Thermal Stress + Lorentz Toward Plasma
Temperature 100C 200C 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323 458 425
Minimum Yield Strength, Sy 253 235 172 144
Design Stress Intensity Limit, Sm 120 108 147 130
108 97 137 128
Stress Limits (SDC -IC), MPa
CuCrZr-IG 316L(N)-IG
Stress Endurance Limit, Se (=30% Su)
Temperature 100C 200C
Minimum Ultimate Tensile Strength, Su 359 323
Minimum Yield Strength, Sy 253 235
Design Stress Intensity Limit, Sm 120 108
108 97
Stress Limits (SDC -IC), MPa
CuCrZr-IG
Stress Endurance Limit, Se (=30% Su)
100e6 Pa = 14,503 psi
The Corner Foundation has Stresses that are not within the Material Limits
A thicker width rail or gusset will be required
84e6 Pa = 12,183 psi
STRESS INTENSITY
NORMAL STRESS
45. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Corner Bracket Bolt Load Vs Load Step
45
Thermal + Lorentz
Toward Plasma
Thermal + Lorentz
Away From Plasma
195,000 N = 43,837 Lbf
The Corner Foundation Bolt3 has significant load variation each cycle
Higher Stiffness Pad Similar to Others is Recommended
Preload 182,000 N = 40,915 Lbf
46. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
46
Corner Bracket Max Bolt Stress Vs Load Step
The Corner Foundation Bolt3 has significant Stress variation each cycle
Higher Stiffness Pad and Preload is Recommended
47. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Contact Status
Demonstrates Insufficient Preloading
47
Thermal + Lorentz Away From Plasma Thermal + Lorentz Toward Plasma
The Corner Foundation Contact Status Has Separation at the Contact Interface
Preload of 182,000 N ( 40,915 Lbf) is not sufficient
Clamp Load Separation
48. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Recommended Bolting Materials
48
The recommended preload is 2.184e5 N (49,048 Lbs)
For a bolt with minimum stress area of 0.4869 in^2 this is a 100,828 preload stress
718-Inconel is adequate and provides some margin for localized bolt bending due to eccentricities
49. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Conclusions
• The reactions loads and moments are provided based on the PDR update applied loads and
assumptions.
• The loads on both Corner Bracket and Poloidal Bracket sub-models were provided.
• Hand Calculations with Complex Bending on the Poloidal Rail (48.6 Mpa) do not predict stress
issues on the foundation interface. This result supports the FE findings (53 Mpa).
• A Poloidal and Corner Bracket with Bolt Model was completed and stresses were shown to be
within limits at the foundation interface, however, the upper section on the rails have excessive
stresses.
• A design optimization was completed and several cases were identified that would minimize the
stresses on the Poloidal rail.
• The rail stresses with these optimized dimensions were completed to show that the Poloidal rail
will still need an additional bolt to minimize the bending.
• The magnitude of the bolt preload to assure fatigue loads are small was determined to be
49,048 Lbf.
50. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Conclusions - Continued
• The sensitivity charts on the Poloidal Rail show that the Inner rail is the most critical dimension
to influence stress intensity and working bolt load.
– The inner radius should not align with the bracket as was used in the PDR since stress intensity and bolt working loads
are increased .
• The Corner bracket rail width is also to small to support the current loads.
The initial preload (40,915 lbf) was not sufficient to maintain contact for Lorentz Load toward
the Plasma.
• The rail on the corner bracket should be optimized, however, it would be conservative to apply
the Poloidal Foundation results to this design as well.
• The isolated single bolt on the outside pad does not have adequate stiffness in comparison to
the other bolts on this bracket. This will likely be a fatigue problem is this is not extended to
provide a similar stiffness with two bolts.
51. PARAMETRIC FOUNDATION & BOLT STUDY February 24, 2011
Recommendations
• The foundation attachment design does not have sufficient (E/D) edge to diameter ratio. This should be
2.0 and at a minimum of 1.5 to have sufficient reliability.
• The Poloidal Foundation Rails should be increased to a width of 60 mm and positioned based on an Inner
Rail of 10 mm and the Outer Rail of 60 mm. This provide a Edge / Diameter (29.726/20=1.486).
• The bolting material should be Inconel 718 AMS-5662 with minimum strengths as specified in Military
Handbook could be used if shear strength is not critical.
• Add an addition bolt on the Poloidal Bracket to minimize bending and provide improved bolt fatigue life.
• Increase the Corner support stiffness and preload to control variation in Bolt Stress.
• These results are based on uniform temperatures and reference temperatures of 100 C. Any temperature
variations at the foundation would warrant additional study to include a thermal gradient through this sub-
model and possibly the reactor wall.
– The actual foundation temperature could be determined by applying the heat flux on the foundation
from the PDR model to a separate model of the reactor wall. Assume 100 C on one side of the
reactor wall model and apply a heat flux to the opposite end of the reactor wall to determine
accurate foundation temperatures for the sub-model analysis provided in this study.
51