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Figure 1 – NSTX Upper Umbrella Assembly Upgrade Design: Version 3 PowerPoint Presentation
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Figure 1 – NSTX Upper Umbrella Assembly Upgrade Design: Version 3 - PowerPoint PPT Presentation

malik-harper
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Figure 1 – NSTX Upper Umbrella Assembly Upgrade Design: Version 3

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  1. Figure 1 – NSTX Upper Umbrella Assembly Upgrade Design: Version 3

  2. 304 SS Support G10 Support Figure 2 – Single Segment Strap Assembly Version 3 with G10/ 304 SS Supports

  3. Figure 3 – Single Segment Strap Assembly: Center Strap Only

  4. Rout = 5.688” 38 Laminations: - .060” thk; .005” gap Mat’l: Copper Wtfull = 37.4 lb (Wtarch = 20.4 lb) Rin = 3.160” 7.5” Bpol= .3 T 5” I = 130 kA Uvertthermal = .3 in Btor = 1 T Uradthermal = .018 in 2.523” 2” Figure 4 – Single Laminated Strap Assembly with Applied Fields and Current

  5. Calculated EMAG Loads Fop Out-of-Plane Load (z-direction) I+ R Fop = 2*I*Bpol*R Fop = 2 x 130,000 A/ 38 x .3 T x 5.688/39.37 m Fop = 296.4 N = 66.6 lbf [per lamination] Bpol In-Plane Load (y-direction) pressip Fip/ L = I*Btor Fip/ L = 130,000 A/ 38 x 1 T [per lamination] Fip/ L = 3,421 N/ m x .2248 lbf/ N x 1 m/ 39.37 in Fip/ L = 19.53 lbf/ in pressip = (Fip/ L)/ w pressip = 19.53 lbf/in / 2 in pressip = 9.77 lbf/ in2 (applied to inside cylindrical faces) x x x x x x x x x x x x x x x x x x I+ w Btor

  6. Force = 66.6 lbf Ux = .018 in Uy = .3 in Uz = 0 Press = 9.7 psi Fixed 3 Elements thru Thickness Figure 5A – Single Lamination FEA Model: Mesh and Boundary Conditions

  7. Figure 5B – Single Lamination Linear Results: von Mises Stress Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

  8. Figure 5C – Single Lamination Linear Results: von Mises Stress Loads: Thermal Displacements Only

  9. Figure 5D – Single Lamination Linear Results: von Mises Stress Loads: In-Plane (Pressure) Load Only

  10. Figure 5E – Single Lamination Linear Results: von Mises Stress Loads: Out-of-Plane (Force) Load Only

  11. Large deflection = On Figure 5F – Single Lamination Nonlinear Results: von Mises Stress Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

  12. Large deflection = On Figure 5G – Single Lamination Nonlinear Results: Z-Deformations Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

  13. Large deflection = On Figure 5H – Single Lamination Nonlinear Results: Z-Deformations_Front Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

  14. σhoop = P*R/ t = 9.77 psi x 5.688 in/ .060 in = 924 psi Large deflection = On Figure 5J – Single Lamination Nonlinear Results: von Mises Stress Loads: Emag Pressure (In Plane) Only

  15. 1st Mode Load Multiplier = 58.4 1st Mode Load Multiplier = 58.4 3rd Mode Load Multiplier = 117.6 (Nonlinear 1st Mode Load Multiplier = 50) Large deflection = Off 2nd Mode Load Multiplier = 73.0 Figure 5K – Single Lamination Pre-Stressed Linear Buckling Results Load multiplier LMF applies to all Emag loads and thermal displacements

  16. Y LMF = 14 0 80 Large deflection = On Figure 5L – Single Lamination Nonlinear Buckling: Y-Deformation at Onset (1) Load multiplier factor LMF applies only Out-of-Plane Emag load

  17. Y LMF = 26 0 80 Large deflection = On Figure 5M – Single Lamination Nonlinear Buckling: Y-Deformation at Onset (2) Load multiplier factor LMF applies only to Out-of-Plane Emag load

  18. Conclusions • Buckling due mostly to out-of-plane load. In-plane load (pressure outward) reduces buckling; thermal displacements slightly increase buckling. • Good agreement between linear and nonlinear buckling results with load multiplier factor applied to both Emag loads and to thermal displacements. • Load multiplier factor over 14 for nonlinear analysis with constant in-plane load and increasing out-of-plane load (conservative).

  19. 3 Elements / Lamination Figure 6A – 3 Lamination FEA Model: Mesh

  20. Large deflection = On Frictional contact (COF = .4) Figure 6B – 3 Lamination Nonlinear Results: von Mises Stress Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

  21. Large deflection = On Frictional contact (COF = .4) Figure 6C – 3 Lamination Nonlinear Results: Z-Deformations Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

  22. Large deflection = On Frictional contact (COF = .4) Figure 6D – 3 Lamination Nonlinear Results: Z-Deformations_Front Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

  23. Large deflection = On Frictional contact (COF = .4) Figure 6E – 3 Lamination Nonlinear Results: Contact Status Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

  24. 3rd Mode Load Multiplier = 61.8 1st Mode Load Multiplier = 58.2 Large deflection = Off Frictional contact (COF = .4) 2nd Mode Load Multiplier = 60.7 Figure 6F – 3 Lamination Results: Linear Buckling Mode Multiplier Load Multiplier factor LMF applies to all Emag loads and thermal displacements

  25. Figure 7A – Single Laminated Strap Assembly FEA Model: Bonded and Frictionless Contact Areas

  26. 3 elements/ lamination # Nodes = 850423 # Elements = 152895 Figure 7B – Single Laminated Strap Assembly FEA Model: Mesh

  27. Large deflection = Off Frictional contact (COF = 0) Fig. 7C –Laminated Strap Assembly FEA Results - Thermal Displacements Only: von Mises Stress

  28. Large deflection = Off Frictional contact (COF = 0) Fig. 7D –Laminated Strap Assembly FEA Results – Thermal Displacements Only: Total Deformation

  29. By = .3T Bz = 1 T ux = .018” uy = .30” I = 130 kA JS FLorentz Non-Linear Large Deflection Non-Linear Large Deflection Heat Gen Tnodes Fig. 8A – Upper Flex Strap ANSYS Multiphysics Analysis Work Flow Diagram

  30. Figure 8B – Single Segment_Center Strap Assembly: Mesh

  31. 0 V 130,000 A Fig. 9C – Single Segment_Center Strap Electric Model: Boundary Conditions

  32. Figure 8D – Single Segment_Center Strap Electric Model Results: Voltage

  33. Fig. 8E – Single Segment_Center Strap Electric Model Results: Current Density

  34. Fig. 8F – Single Segment_Center Strap Electric Model Results: Joule Heat