Advanced Turbine Engine Seal Design.
Final rept. 30 Jun 72-31 Mar 73,
GENERAL ELECTRIC CO CINCINNATI OHIO AIRCRAFT ENGINE GROUP
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Program objective was to determine film-cooling effectiveness, eta sub f and transpiration cooling effectiveness, eta sub T, on advanced shroud concepts tested in a single stage, high pressure ratio air turbine. Three film-cooled shroud segments, with varying film hole patterns, and one transpiration-cooled shroud segment, featuring a coarse matrix Poroloy shroud surface, were designed, manufactured and tested. Effectiveness data were obtained and analyzed. Distribution of gas recovery temperature and of gas stream static pressure along the shroud surface were also measured for use in applying the effectiveness data to the design of future cooled shroud systems. The program results show that high levels of eta sub f and eta sub T are achievable on air cooled turbine shrouds. Author
- Adhesives, Seals and Binders
- Jet and Gas Turbine Engines