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Measured effects of coolant injection on the performance of a film cooled turbineTests have been conducted on a 20-inch diameter single-stage air-cooled turbine designed to evaluate the effects of film cooling air on turbine aerodynamic performance. The present paper reports the results of five test configurations, including two different cooling designs and three combinations of cooled and solid airfoils. A comparison is made of the experimental results with a previously published analytical method of evaluating coolant injection effects on turbine performance.
Document ID
19770055755
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mcdonel, J. D. (General Electric Co. Evendale, OH, United States)
Eiswerth, J. E. (General Electric Co., Aircraft Engine Group, Evendale Ohio, United States)
Date Acquired
August 9, 2013
Publication Date
July 1, 1977
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 77-946
Meeting Information
Meeting: Propulsion Conference
Location: Orlando, FL
Country: US
Start Date: July 11, 1977
End Date: July 13, 1977
Sponsors: American Institute of Aeronautics and Astronautics, Society of Automotive Engineers
Accession Number
77A38607
Funding Number(s)
CONTRACT_GRANT: NAS3-16732
Distribution Limits
Public
Copyright
Other

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