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.
Infrared Low-Temperature Turbine Vane Rough Surface Heat Transfer Measurements
Contributed by the International Gas Turbine Institute and presented at the 45th International Gas Turbine and Aeroengine Congress and Exhibition, Munich, Germany, May 8–11, 2000. Manuscript received by the International Gas Turbine Institute February 2000. Paper No. 2000-GT-216. Review Chair: D. Ballal.
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Boyle, R. J., Spuckler, C. M., Lucci, B. L., and Camperchioli, W. P. (February 1, 2000). "Infrared Low-Temperature Turbine Vane Rough Surface Heat Transfer Measurements ." ASME. J. Turbomach. January 2001; 123(1): 168–177. https://doi.org/10.1115/1.1333693
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