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Measurement of airfoil heat transfer coefficients on a turbine stageThe primary basis for heat transfer analysis of turbine airfoils is experimental data obtained in linear cascades. A detailed set of heat transfer coefficients was obtained along the midspan of a stator and a rotor in a rotating turbine stage. The data are to be compared to standard analyses of blade boundary layer heat transfer. A detailed set of heat transfer coefficients was obtained along the midspan of a stator located in the wake of a full upstream turbine stage. Two levels of inlet turbulence (1 and 10 percent) were used. The analytical capability will be examined to improve prediction of the experimental data.
Document ID
19870001788
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dring, R. P. (United Technologies Research Center East Hartford, CT, United States)
Blair, M. F. (United Technologies Research Center East Hartford, CT, United States)
Date Acquired
August 13, 2013
Publication Date
October 1, 1984
Publication Information
Publication: NASA. Lewis Research Center Turbine Engine Hot Section Technology, 1984
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
87N11221
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19870001747Collected WorksTurbine Engine Hot Section Technology, 1984
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