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Stress analysis and life prediction of gas turbine bladeA stress analysis procedure is presented for a redesign of the Space Shuttle Main Engine high pressure fuel turbopump turbine blades. The analysis consists of the one-dimensional scoping analysis to support the design layout and the follow-on three-dimensional finite element analysis to confirm the blade design at operating loading conditions. Blade life is evaluated based on high-cycle fatigue and low-cycle fatigue.
Document ID
19880057570
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hsiung, H. C. (Rockwell International Corp. Canoga Park, CA, United States)
Dunn, A. J. (Rockwell International Corp. Canoga Park, CA, United States)
Woodling, D. R. (Rockwell International Corp. Canoga Park, CA, United States)
Loh, D. L. (Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)
Date Acquired
August 13, 2013
Publication Date
July 1, 1988
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 88-3218
Accession Number
88A44797
Funding Number(s)
CONTRACT_GRANT: NAS8-40000
Distribution Limits
Public
Copyright
Other

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