Publication Date:
2019-07-13
Description:
Turbine 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 percent. 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.
Keywords:
Aircraft Propulsion and Power
Type:
Paper-2000-GT-216
,
Journal of Turbomachinery; 123; 168-177|45th International Gas Turbine and Aeroengine Congress and Exhibition; Mar 08, 2000 - Mar 11, 2000; Munich; Germany
Format:
text
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