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An adverse effect of film cooling on the suction surface of a turbine vaneFilm-cooling-air ejection from the suction surface of a turbine vane was investigated. This investigation was conducted in a four-vane cascade on a J75 size turbine vane which had a row of holes near the leading edge. The experimental data are presented. It was found that a small amount of film-cooling air has a detrimental effect on the downstream vane wall cooling effectiveness. It was also shown that the presence of the film-cooling holes, without blowing, also cause an increase in vane wall temperatures. These results came from an increase in the gas-side heat transfer coefficient that was apparently caused by a laminar or transitional boundary layer becoming transitional or turbulent.
Document ID
19740012480
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Gladden, H. J. (NASA Lewis Research Center Cleveland, OH, United States)
Gauntner, J. W. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1974
Subject Category
Thermodynamics And Combustion
Report/Patent Number
E-7744
NASA-TN-D-7618
Accession Number
74N20593
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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