Local Heat-Transfer Measurements on a Large Scale-Model Turbine Blade Airfoil Using a Composite of a Heater Element and Liquid Crystals

[+] Author and Article Information
S. A. Hippensteele, L. M. Russell, F. J. Torres

National Aeronautics and Space Administration, Lewis Research Center, Cleveland, OH 44135

J. Eng. Gas Turbines Power 107(4), 953-960 (Oct 01, 1985) (8 pages) doi:10.1115/1.3239841 History: Received December 21, 1984; Online October 15, 2009


Local heat-transfer coefficients were experimentally mapped along the midchord of a five-times-size turbine blade airfoil in a static cascade operated at room temperature over a range of Reynolds numbers. The test surface consisted of a composite of commercially available materials: a mylar sheet with a layer of cholesteric liquid crystals, which change color with temperature, and a heater sheet made of a carbon-impregnated paper, which produces uniform heat flux. After the initial selection and calibration of the composite sheet, accurate, quantitative, and continuous heat-transfer coefficients were mapped over the airfoil surface. The local heat-transfer coefficients are presented for Reynolds numbers from 2.8×105 to 7.6×105 . Comparisons are made with analytical values of heat-transfer coefficients obtained from the STAN5 boundary layer code. Also, a leading-edge separation bubble was revealed by thermal and flow visualization.

Copyright © 1985 by ASME
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