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Space Shuttle main engine powerhead structural modeling, stress and fatigue life analysis. Volume 3: Stress summay of blades and nozzles at FPL and 115 percent RPL loads. SSME HPFTP and HPOTP blades and nozzlesGasdynamic environments applied to the turbine blades and nozzles of the HPFTP and HPOTP were analyzed. Centrifugal loads were applied to blades to account for the pump rotation of FPL and 115 percent RPL. The computer models used in the blade analysis with results presented in the form of temperature and stress contour plots are described. Similar information is given for the nozzles.
Document ID
19840012569
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Hammett, J. C. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Hayes, C. H. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Price, J. M. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Robinson, J. K. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Teal, G. A. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Thomson, J. M. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Tilley, D. M. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Welch, C. T. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1983
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
LMSC-HREC-TR-D867333-III
NAS 1.26:171001
NASA-CR-171001
Report Number: LMSC-HREC-TR-D867333-III
Report Number: NAS 1.26:171001
Report Number: NASA-CR-171001
Accession Number
84N20637
Funding Number(s)
CONTRACT_GRANT: NAS8-34978
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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