1 / 22

N. Dhanaraj , Y. Orlov , R. Wands

Thermal-Stress Analysis of CC1 Space Frame. N. Dhanaraj , Y. Orlov , R. Wands. Outline. Background and Motivation Design Changes Assembly and Loading Sequence Finite Element Analysis Strategy Analysis and Results Summary. Background and Motivation.

nevina
Download Presentation

N. Dhanaraj , Y. Orlov , R. Wands

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Thermal-Stress Analysis of CC1 Space Frame N. Dhanaraj, Y. Orlov, R. Wands

  2. Outline • Background and Motivation • Design Changes • Assembly and Loading Sequence • Finite Element Analysis Strategy • Analysis and Results • Summary

  3. Background and Motivation • The Superconducting cavity in the Capture Cavity 1 (CC1) cryomodule is mounted on a space frame structure. • There has been a recent plan to upgrade this cryomodule by replacing the cavity and lever tuner set up with a newer 1.3 GHz 9-cell cavity and blade tuner. • This upgrade has invoked a thermal-stress verification of the space frame support structure. • The following slides will provide the details of the thermal-stress analysis and the basis to deem the safety of the upgrade and also address recommendations from previous review.

  4. 3D Model of Space Frame with Cavity Dressed Cavity G10 Support Rods

  5. 3D Model of Space Frame SS Bearing Blocks to seat the Dressed Cavity Aluminum Support Frame G10 Support System to Control Longitudinal Motion of the Support Frame G10 Support Rods

  6. Design Changes 1506.11N

  7. Assembly and Loading Sequence • The assembly sequence dictates the various loads acting on the space frame and the G10 support rods, thus defining this assembly procedure is critical. • Assembly Procedure of Main Components: • The dressed cavity is mounted on the aluminum frame and the assembly is loaded on to a cart. • The cart is rolled into the cryomodule. • The top G10 rods are used to lift the cavity assembly and then locked in position. • The cart is rolled out and the bottom G10 rods and snug fit before cool down. • After cool down all G10 rods should see tensile forces that should produce stresses that fall within the allowable limits for the material to ensure proper design.

  8. Finite Element Analysis Strategy Albeit First Thermal in ANSYS

  9. FEA Models Meshed Model – 207737 nodes, 77810 elements Half Symmetry Model

  10. Static Structural – Loading of Upper G10 Rods Fixed Ends 4X Rz = Free 1/4th (1506.11 N) Free to move along length Free along Z

  11. Results – Forces and Displacements Fz = 371.44 N Fz = 501.24 N Uz = -0.491 mm Uz = -0.404 mm Uz global= -0.191 mm

  12. Results – Stresses in Frame From the Aluminum Association, Specifications for Aluminum Structures (FOS > 1.5): Maximum fiber stress for 6061-T6 unwelded = 131 MPa Maximum fiber stress for 6061-T6 welded = 75.8 MPa

  13. Results – Rod Forces and Stresses

  14. Thermal Analysis A A B B B C B A A

  15. Results – Temperature Profile

  16. Heat Loads 0.014 W

  17. Combined Thermal-Structural Rod 2 Rod 1 Rod 4 Rod 3 Displacements Uz set from previous analysis

  18. Results – Rod Forces and Stresses

  19. Results – Stresses in Frame From the Aluminum Association, Specifications for Aluminum Structures (FOS > 1.5): Maximum fiber stress for 6061-T6 unwelded = 131 MPa Maximum fiber stress for 6061-T6 welded = 75.8 MPa Verification of High stress: Stress classification line through weld gives membrane stress 88.5 MPa and membrane + bending 175.6 MPa which are well below the allowables for secondary stresses of 1.5 Sm for membrane and 3 Sm for membrane + bending from ASME VIII Div. 2.

  20. Results - Displacements Lateral Range 2.3 to -2.1 mm Range 0.75 to -2.8 mm Cavity axis Range 1.4 to -0.9 mm Z

  21. Beam Tube Radiation Heat Load Assumptions: • Steady state conditions, surroundings approximated as blackbody. • Emissivity of inner beam tube surface = 0.16 (unpolished or slightly polished copper surface) Heat load from 300 K to 2 K is 0.3 Watts 450 mm 78 mm 2 K 300 K surroundings

  22. Summary • Thermal-stress analysis was performed on the CC1 space frame to match the assembly and loading sequence. • The stresses in the parts of concern were looked at (G10 rods) and the stresses were found to be significantly below the allowable limits. • There is no need for spring washers on the G10 rods as the forces experienced are very low. • The stresses in the aluminum frame was also analyzed and found to be below the allowables of Aluminum Association standards. No credit was taken for cold properties. • The displacements of the space frame due to thermal contraction are within the bellows capabilities. • The heat loads to 2 K /5 K junctions are very small. • The support structure is safe for the operation of the upgrade.

More Related