Thermal And Structural Analysis Of A Hollow Core Space Shuttle Main Engine Ssme Turbine Blade
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Thermal And Structural Analysis Of A Hollow Core Space Shuttle Main Engine Ssme Turbine Blade
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Author :
language : en
Publisher:
Release Date : 1995
Thermal And Structural Analysis Of A Hollow Core Space Shuttle Main Engine Ssme Turbine Blade written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1995 with categories.
Thermal Finite Element Analysis Of Space Shuttle Main Engine Turbine Blade
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Author :
language : en
Publisher:
Release Date : 1987
Thermal Finite Element Analysis Of Space Shuttle Main Engine Turbine Blade written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1987 with categories.
Structures Division 1994 Annual Report
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Author :
language : en
Publisher:
Release Date : 1996
Structures Division 1994 Annual Report written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with categories.
Research And Technology 1995
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Author :
language : en
Publisher:
Release Date : 1996
Research And Technology 1995 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with categories.
Space Shuttle Main Engine Structural Analysis And Data Reduction Evaluation Volume 2
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-10
Space Shuttle Main Engine Structural Analysis And Data Reduction Evaluation Volume 2 written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-10 with categories.
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...
Assessment Of Crack Growth In A Space Shuttle Main Engine First Stage High Pressure Fuel Turbopump Blade
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Author : National Aeronautics and Space Adm Nasa
language : en
Publisher: Independently Published
Release Date : 2018-10-24
Assessment Of Crack Growth In A Space Shuttle Main Engine First Stage High Pressure Fuel Turbopump Blade written by National Aeronautics and Space Adm Nasa and has been published by Independently Published this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-10-24 with Science categories.
A two-dimensional finite element fracture mechanics analysis of a space shuttle main engine (SSME) turbine blade firtree was performed using the MARC finite element code. The analysis was conducted under combined effects of thermal and mechanical loads at steady-state conditions. Data from a typical engine stand cycle of the SSME were used to run a heat transfer analysis and, subsequently, a thermal structural fracture mechanics analysis. Temperature and stress contours for the firtree under these operating conditions were generated. High stresses were found at the firtree lobes where crack initiation was triggered. A life assessment of the firtree was done by assuming an initial and a final crack size. Abdul-Aziz, Ali Unspecified Center NAS3-25266; RTOP 553-13-00...
Space Shuttle Main Engine High Pressure Fuel Turbopump Turbine Blade Cracking
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Author : National Aeronautics and Space Adm Nasa
language : en
Publisher:
Release Date : 2018-11-02
Space Shuttle Main Engine High Pressure Fuel Turbopump Turbine Blade Cracking written by National Aeronautics and Space Adm Nasa and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-11-02 with categories.
The analytical results from two-dimensional (2D) and three-dimensional (3D) finite element model investigations into the cracking of Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump (HPFTP) first- and second-stage turbine blades are presented. Specifically, the initiation causes for transverse cracks on the pressure side of the firststage blade fir tree lobes and face/corner cracks on the downstream fir tree face of the second-state blade are evaluated. Because the blade material, MAR-M-246 Hf (DS), is highly susceptible to hydrogen embrittlement in the -100 F to 400 F thermal environment, a steady-state condition (full power level = 109 percent) rather than a start-up or shut-down transient was considered to be the most likely candidate for generating a high-strain state in the fir tree areas. Results of the analyses yielded strain levels on both first- and second-stage blade fir tree regions that are of a magnitude to cause hydrogen assisted low cycle fatigue cracking. Also evident from the analysis is that a positive margin against fir tree cracking exists for the planned design modifications, which include shot peening for both first- and second-stage blade fir tree areas. Lee, Henry Marshall Space Flight Center...
Space Shuttle Main Engine Structural Analysis And Data Reduction Evaluation Volume 2
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Author : National Aeronautics and Space Adm Nasa
language : en
Publisher:
Release Date : 2018-11-09
Space Shuttle Main Engine Structural Analysis And Data Reduction Evaluation Volume 2 written by National Aeronautics and Space Adm Nasa and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-11-09 with categories.
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...
Space Shuttle Main Engine Structural Analysis And Data Reduction Evaluation Volume 4
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-10
Space Shuttle Main Engine Structural Analysis And Data Reduction Evaluation Volume 4 written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-10 with categories.
The analysis performed on the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump (HPFTP) inlet housings is summarized. Three DIAL finite element models were build to aid in assessing the structural life of the welds and fillets at the vanes. Complete results are given. Pool, Kirby V. Unspecified Center...
Developmental Problems And Their Solution For The Space Shuttle Main Engine Alternate Liquid Oxygen High Pressure Turbopump Anomaly Or Failure Investigation The Key
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Author : R. S. Ryan
language : en
Publisher:
Release Date : 1995
Developmental Problems And Their Solution For The Space Shuttle Main Engine Alternate Liquid Oxygen High Pressure Turbopump Anomaly Or Failure Investigation The Key written by R. S. Ryan and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1995 with Turbine pumps categories.