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Comprehensive Structural Dynamic Analysis of the SSME/AT Fuel Pump First-Stage Turbine BladeA detailed structural dynamic analysis of the Pratt & Whitney high-pressure fuel pump first-stage turbine blades has been performed to identify the cause of the tip cracking found in the turbomachinery in November 1997. The analysis was also used to help evaluate potential fixes for the problem. Many of the methods available in structural dynamics were applied, including modal displacement and stress analysis, frequency and transient response to tip loading from the first-stage Blade Outer Gas Seals (BOGS), fourier analysis, and shock spectra analysis of the transient response. The primary findings were that the BOGS tip loading is impulsive in nature, thereby exciting many modes of the blade that exhibit high stress at the tip cracking location. Therefore, a proposed BOGS count change would not help the situation because a clearly identifiable resonance situation does not exist. The recommendations for the resolution of the problem are to maintain the existing BOGS count, eliminate the stress concentration in the blade due to its geometric design, and reduce the applied load on the blade by adding shiplaps in the BOGS.
Document ID
19980217661
Acquisition Source
Marshall Space Flight Center
Document Type
Technical Memorandum (TM)
Authors
Brown, A. M.
(NASA Marshall Space Flight Center Huntsville, AL United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1998
Subject Category
Structural Mechanics
Report/Patent Number
M-891
NASA/TM-1998-208594
NAS 1.15:208594
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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