Low-cost directionally-solidified turbine blades, volume 1.
- Author
- Sink, L. W.
- Published
- Jan 1, 1979.
- Physical Description
- 1 electronic document
- Additional Creators
- Hoppin, G. S., III and Fujii, M.
Online Version
- hdl.handle.net , Connect to this object online.
- Restrictions on Access
- Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access - Summary
- A 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.
- Other Subject(s)
- Collection
- NASA Technical Reports Server (NTRS) Collection.
- Note
- Document ID: 19790015950.
Accession ID: 79N24121.
NASA-CR-159464.
AIRESEARCH-21-2953-1. - Terms of Use and Reproduction
- No Copyright.
View MARC record | catkey: 15725540