Stress analysis and life prediction of gas turbine blade

Hsiung, H. C.; Dunn, A. J.; Woodling, D. R.; Loh, D. L.

A 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

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

Report/Patent Number

Funding Number(s)

Distribution Limits

Public

Other

NTRS

NTRS - NASA Technical Reports Server