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Predicted Turbine Heat Transfer for a Range of Test ConditionsComparisons are shown between predictions and experimental data for blade and endwall heat transfer. The comparisons of computational domain parisons are given for both vane and rotor geometries over an extensive range of Reynolds and Mach numbers. Comparisons are made with experimental data from a variety of sources. A number of turbulence models are available for predicting blade surface heat transfer, as well as aerodynamic performance. The results of an investigation to determine the turbulence model which gives the best agreement with experimental data over a wide range of test conditions are presented.
Document ID
19970007979
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Boyle, R. J. (NASA Lewis Research Center Cleveland, OH United States)
Lucci, B. L. (NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
November 1, 1996
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TM-107374
NAS 1.15:107374
E-10543
Meeting Information
Meeting: Gas Turbine and Aeroengine Congress
Location: Birmingham
Country: United Kingdom
Start Date: June 10, 1996
End Date: June 13, 1996
Sponsors: American Society of Mechanical Engineers
Accession Number
97N14506
Funding Number(s)
PROJECT: RTOP 505-62-52
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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