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Effect of thermal shock on fiber-reinforced superalloy compositesAn evaluation is presented of the thermal shock behavior of tungsten fiber-reinforced superalloy (FRS) composites with respect to the turbine blade requirements of rocket engine turbopumps. Each composite was reinforced unidirectionally with 40-volume-pct continuous tungsten fibers. The start-up conditions of the first-stage turbine blades of the high-pressure fuel turbopump in the Space Shuttle Main Engine (SSME) were used to investigate the thermal shock behavior of these materials. The FRS composites showed excellent thermal shock resistance, two to nine times better than the turbine blade material used in the SSME. Thermal shock cycling produced microcracks on the surfaces of the irradiated area that were less than 0.13 mm long and 0.005 mm deep. Neither fiber/matrix debonding nor microvoiding was observed.
Document ID
19910071295
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Yuen, J. L.
(Rockwell International Corp. Canoga Park, CA, United States)
Schnittgrund, G. D.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)
Petrasek, D. W.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Composite Materials
Meeting Information
Meeting: TMS Fall Meeting
Location: Indianapolis, IN
Country: United States
Start Date: October 1, 1989
End Date: October 5, 1989
Sponsors: Minerals, Metals and Materials Society, ASM International
Accession Number
91A55918
Funding Number(s)
CONTRACT_GRANT: NAS3-24380
Distribution Limits
Public
Copyright
Other

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