Author: Dennis Fuk-Kuen LiPublisher:
ISBN:
Category :
Languages : en
Pages : 86
Book Description
Space shuttle main engine high pressure oxidizer turbopump critical speed and unbalance response analysis
Author: Dennis Fuk-Kuen LiThe dynamic analysis of the space shuttle main engine-high pressure fuel turbopump
Author: Edgar J. GunterExperimental data analysis of the space shuttle main engine - high pressure oxidizer and fuel turbopumps
Author: Edgar J. GunterStability analysis of the oxygen pump for the space shuttle main engine
Author: Lyle Arthur BranaganPublisher:
ISBN:
Category :
Languages : en
Pages : 108
Book Description
Interim report on the dynamic analysis of the space shuttle-main engine high pressure fuel turbopump
Author: Edgar J. GunterRotordynamic Instability Problems in High-performance Turbomachinery 1990
Author: Experimental Data analysis of the space shuttle main engine
Author: Ronald D. FlackDevelopmental Problems and Their Solution for the Space Shuttle Main Engine Alternate Liquid Oxygen High-pressure Turbopump: Anomaly Or Failure Investigation the Key
Author: R. S. RyanPublisher:
ISBN:
Category : Turbine pumps
Languages : en
Pages : 84
Book Description
Advanced High Pressure O2/H2 Technology
Author: S. F. MoreaPublisher:
ISBN:
Category : Liquid propellant rockets
Languages : en
Pages : 762
Book Description
Space Shuttle Main Engine Structural Analysis and Data Reduction/Evaluation. Volume 2
Author: National Aeronautics and Space Adm NasaPublisher:
ISBN: 9781730942747
Category :
Languages : en
Pages : 86
Book Description
The high-pressure oxidizer turbopump (HPOTP) consists of two centrifugal pumps, on a common shaft, that are directly driven by a hot-gas turbine. Pump shaft axial thrust is balanced in that the double-entry main inducer/impeller is inherently balanced and the thrusts of the preburner pump and turbine are nearly equal but opposite. Residual shaft thrust is controlled by a self-compensating, non-rubbing, balance piston. Shaft hang-up must be avoided if the balance piston is to perform properly. One potential cause of shaft hang-up is contact between the Phase 2 bearing support and axial spring cartridge of the HPOTP main pump housing. The status of the bearing support/axial spring cartridge interface is investigated under current loading conditions. An ANSYS version 4.3, three-dimensional, finite element model was generated on Lockheed's VAX 11/785 computer. A nonlinear thermal analysis was then executed on the Marshall Space Flight Center Engineering Analysis Data System (EADS). These thermal results were then applied along with the interference fit and bolt preloads to the model as load conditions for a static analysis to determine the gap status of the bearing support/axial spring cartridge interface. For possible further analysis of the local regions of HPOTP main pump housing assembly, detailed ANSYS submodels were generated using I-DEAS Geomod and Supertab (Appendix A). Sisk, Gregory A. Unspecified Center...