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Three-Dimensional Flow Field Measurements in a Transonic Turbine CascadeThree-dimensional flow field measurements are presented for a large scale transonic turbine blade cascade. Flow field total pressures and pitch and yaw flow angles were measured at an inlet Reynolds number of 1.0 x 10(exp 6) and at an isentropic exit Mach number of 1.3 in a low turbulence environment. Flow field data was obtained on five pitchwise/spanwise measurement planes, two upstream and three downstream of the cascade, each covering three blade pitches. Three-hole boundary layer probes and five-hole pitch/yaw probes were used to obtain data at over 1200 locations in each of the measurement planes. Blade and endwall static pressures were also measured at an inlet Reynolds number of 0.5 x 10(exp 6) and at an isentropic exit Mach number of 1.0. 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 deg of turning and an axial chord of 12.7 cm. The flow field in the cascade is highly three-dimensional as a result of thick boundary layers at the test section inlet and because of the high degree of flow turning. 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 CFD code and model verification.
Document ID
19970009632
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)
Lopez, I. (Army Research Lab. Cleveland, OH United States)
Boyle, R. J. (NASA Lewis Research Center Cleveland, OH United States)
VanFossen, G. J. (NASA Lewis Research Center Cleveland, OH United States)
Jett, T. A. (NASA Lewis Research Center Cleveland, OH United States)
Camperchioli, W. P. (NASA Lewis Research Center Cleveland, OH United States)
La, H. (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
E-10584
NASA-TM-107388
NAS 1.15:107388
ARL-TR-1252
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
97N15028
Funding Number(s)
CONTRACT_GRANT: NAS3-27186
PROJECT: RTOP 523-26-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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