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RESEARCH PAPERS

Aerodynamic Performance of a Transonic Turbine Guide Vane With Trailing Edge Coolant Ejection: Part I—Experimental Approach

[+] Author and Article Information
C. Kapteijn, J. Amecke

Institut für Strömungsmechanik, Deutsche Forschungsanstalt für Luft-und Raumfahrt e.V., Göttingen, Federal Republic of Germany

V. Michelassi

Department of Energetics, University of Florence, Florence, Italy

J. Turbomach 118(3), 519-528 (Jul 01, 1996) (10 pages) doi:10.1115/1.2836698 History: Received February 25, 1994; Online January 29, 2008

Abstract

Inlet guide vanes (IGV) of high-temperature gas turbines require an effective trailing edge cooling. But this cooling significantly influences the aerodynamic performance caused by the unavoidable thickening of the trailing edge and the interference of the cooling flow with the main flow. As part of a comprehensive research program, an inlet guide vane was designed and manufactured with two different trailing edge shapes. The results from the cascade tests show that the flow behavior upstream of the trailing edge remains unchanged. The homogeneous values downstream show higher turning and higher losses for the cut-back blade, especially in the supersonic range. Additional tests were conducted with carbon dioxide ejection, in order to analyze the mixing process downstream of the cascade.

Copyright © 1996 by The American Society of Mechanical Engineers
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