The evolution of increasing turbine inlet temperature has led to the necessity of full-coverage film cooling for the first turbine vane and blade. A new approach using high speed wall jets for blade cooling has been proposed by the authors. In this paper a 2-D upwind-biased Navier-Stokes code is used to calculate the aerodynamic behaviour of these surface coolant jets in a linear cascade. Special emphasis is put on the investigation of the coolant flow around the leading edge. Various numerical results concerning the leading edge flow are presented in detail, showing a strong tendency of these jets to bend towards convex surfaces. Finally, Schlieren pictures taken at the Institute’s transonic cascade on a 140mm chord length blade are presented for comparison.
- International Gas Turbine Institute
Blade Film Cooling by Underexpanded Transonic Jet Layers
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Gehrer, A, Woisetschläger, J, & Jericha, H. "Blade Film Cooling by Underexpanded Transonic Jet Layers." Proceedings of the ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. Orlando, Florida, USA. June 2–5, 1997. V001T03A042. ASME. https://doi.org/10.1115/97-GT-246
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