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Comparison of heat-transfer characteristics of two air-cooled turbine blades tested in a turbojet engineTwo air-cooled blades were tested to gas temperatures of 2568 F with coolant temperatures to 764 F. Both average and local blade temperatures were correlated over the range of operating conditions. Calculated and measured blade wall temperatures are compared. Potential operating turbine-inlet temperatures of each blade are discussed.
Document ID
19720019316
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Fallon, G. E. (NASA Lewis Research Center Cleveland, OH, United States)
Livingood, J. N. B. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
June 1, 1972
Subject Category
Thermodynamics And Combustion
Report/Patent Number
NASA-TM-X-2564
E-6822
Report Number: NASA-TM-X-2564
Report Number: E-6822
Accession Number
72N26966
Funding Number(s)
PROJECT: RTOP 764-74
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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