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Comparison of cooling effectiveness of turbine vanes with and without film coolingThe cooling effectiveness of three film-cooled vanes were compared to the cooling effectiveness of two non-film-cooled vanes. The comparison indicated that, for the vane configurations and test conditions examined, film cooling had an adverse effect near the suction-surface trailing edge of the vanes. Film cooling was found to be beneficial on the pressure surface of the vanes.
Document ID
19740018277
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Yeh, F. C. (NASA Lewis Research Center Cleveland, OH, United States)
Gladden, H. J. (NASA Lewis Research Center Cleveland, OH, United States)
Gauntner, J. W. (NASA Lewis Research Center Cleveland, OH, United States)
Gauntner, D. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
June 1, 1974
Subject Category
Thermodynamics And Combustion
Report/Patent Number
E-7860
NASA-TM-X-3022
Accession Number
74N26390
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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