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Infrared Low Temperature Turbine Vane Rough Surface Heat Transfer MeasurementsTurbine vane heat transfer distributions obtained using an infrared camera technique are described. Infrared thermography was used because noncontact surface temperature measurements were desired. Surface temperatures were 80 C or less. Tests were conducted in a three vane linear cascade, with inlet pressures between 0.14 and 1.02 atm., and exit Mach numbers of 0.3, 0.7, and 0.9, for turbulence intensities of approximately 1 and 10%. Measurements were taken on the vane suction side, and on the pressure side leading edge region. The designs for both the vane and test facility are discussed. The approach used to account for conduction within the vane is described. Midspan heat transfer distributions are given for the range of test conditions.
Document ID
20000082017
Acquisition Source
Glenn Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Boyle, R. J. (NASA Glenn Research Center Cleveland, OH United States)
Spuckler, C. M. (NASA Glenn Research Center Cleveland, OH United States)
Lucci, B. L. (NASA Glenn Research Center Cleveland, OH United States)
Camperchioli, W. P. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
August 1, 2000
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NASA/TM-2000-210220
E-12339
NAS 1.15:210220
ASME-2000-GT-0216
Meeting Information
Meeting: 45th International Gas Turbine and Aeroengine Technical Congress
Location: Munich
Country: Germany
Start Date: May 8, 2000
End Date: May 11, 2000
Sponsors: American Society of Mechanical Engineers
Funding Number(s)
PROJECT: RTOP 523-26-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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