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Experimental determination of stator endwall heat transferLocal Stanton numbers were experimentally determined for the endwall surface of a turbine vane passage. A six vane linear cascade having vanes with an axial chord of 13.81 cm was used. Results were obtained for Reynolds numbers based on inlet velocity and axial chord between 73,000 and 495,000. The test section was connected to a low pressure exhaust system. Ambient air was drawn into the test section, inlet velocity was controlled up to a maximum of 59.4 m/sec. The effect of the inlet boundary layer thickness on the endwall heat transfer was determined for a range of test section flow rates. The liquid crystal measurement technique was used to measure heat transfer. Endwall heat transfer was determined by applying electrical power to a foil heater attached to the cascade endwall. The temperature at which the liquid crystal exhibited a specific color was known from a calibration test. Lines showing this specific color were isotherms, and because of uniform heat generation they were also lines of nearly constant heat transfer. Endwall static pressures were measured, along with surveys of total pressure and flow angles at the inlet and exit of the cascade.
Document ID
19890005995
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Boyle, Robert J. (NASA Lewis Research Center Cleveland, OH, United States)
Russell, Louis M. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1989
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TM-101419
NAS 1.15:101419
E-4517
Meeting Information
Meeting: International Gas Turbine and Aeroengine Congress and Exposition
Location: Toronto, Ontario
Country: Canada
Start Date: June 4, 1989
End Date: June 8, 1989
Sponsors: ASME
Accession Number
89N15366
Funding Number(s)
PROJECT: RTOP 505-62-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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