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Cyclic Structural Analyses of SSME Turbine BladesThe problems of calculating the structural response of high-temperature space propulsion components such as turbine blades for the fuel turbopump are addressed. The first high-pressure-stage fuel turbine blade (HPFTB) in the liquid-hydrogen turbopump of the space shuttle main engine (SSME) was selected for this study. In the past these blades have cracked in the blade shank region and at the airfoil leading edge adjacent to the platform. To achieve the necessary durability, these blades are currently being cast by using directional solidification. Single-crystal alloys are also being investigated for future SSME applications. The study evaluated the utility of advanced structural analysis methods in assessing the low-cycle fatigue lives of these anisotropic components. The turbine blade airfoil of the high-pressure stage of the SSME fuel turbopump was analyzed because it has a history of rapid crack initiation.
Document ID
19850019651
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kaufman, A.
(NASA Lewis Research Center Cleveland, OH, United States)
Manderscheid, J. M.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
May 1, 1985
Publication Information
Publication: Struct. Integrity and Durability of Reusable Space Propulsion Systems
Subject Category
Structural Mechanics
Accession Number
85N27963
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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