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Low-cost directionally-solidified turbine blades, volume 1A low cost process of manufacturing high stress rupture strength directionally-solidified high pressure turbine blades was successfully developed for the TFE731-3 Turbofan Engine. The basic processing parameters were established using MAR-M 247 and employing the exothermic directional-solidification process in trial castings of turbine blades. Nickel-based alloys were evaluated as directionally-solidified cast blades. A new turbine blade, disk, and associated components were then designed using previously determined material properties. Engine tests were run and the results were analyzed and compared to the originally established goals. The results showed that the stress rupture strength of exothermically heated, directionally-solidified MAR-M 247 turbine blades exceeded program objectives and that the performance and cost reduction goals were achieved.
Document ID
19790015950
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Sink, L. W. (AiResearch Mfg. Co. Phoenix, AZ, United States)
Hoppin, G. S., III (AiResearch Mfg. Co. Phoenix, AZ, United States)
Fujii, M. (AiResearch Mfg. Co. Phoenix, AZ, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1979
Subject Category
Metallic Materials
Report/Patent Number
NASA-CR-159464
AIRESEARCH-21-2953-1
Accession Number
79N24121
Funding Number(s)
PROJECT: RTOP 510-53-02
CONTRACT_GRANT: NAS3-20073
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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