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Endwall Heat Transfer Measurements in a Transonic Turbine CascadeTurbine blade endwall heat transfer measurements are given for a range of Reynolds and Mach numbers. Data were obtained for Reynolds numbers based on inlet conditions of 0.5 and 1.0 x 106, for isentropic exit Mach numbers of 1.0 and 1.3, and for freestream turbulence intensities of 0.25% and 7.0%. Tests were conducted in a linear cascade at the NASA Lewis Transonic Turbine Blade Cascade Facility. The test article was a turbine rotor with 136' of turning and an axial chord of 12.7 cm. The large scale allowed for very detailed measurements of both flow field and surface phenomena. The intent of the work is to provide benchmark quality data for computational fluid dynamics (CFD) code and model verification. The flow field in the cascade is highly three-dimensional as a result of thick boundary layers at the test section inlet. Endwall heat transfer data were obtained using a steady-state liquid crystal technique.
Document ID
19970006983
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Giel, P. W. (NYMA, Inc. Brook Park, OH United States)
Thurman, D. R. (Army Research Lab. Cleveland, OH United States)
VanFossen, G. J. (NASA Lewis Research Center Cleveland, OH United States)
Hippensteele, S. A. (NASA Lewis Research Center Cleveland, OH United States)
Boyle, R. J. (NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1996
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
ARL-TR-1253
E-10583
NASA-TM-107387
NAS 1.15:107387
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
97N13847
Funding Number(s)
PROJECT: RTOP 523-26-13
CONTRACT_GRANT: NAS3-27186
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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