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RESEARCH PAPERS

Computation of a Wall Boundary Layer With Discrete Jet Injections

[+] Author and Article Information
P. Kulisa, F. Leboeuf, G. Perrin

Ecole Centrale de Lyon, Laboratoire de Mecanique des Fluides et d’Acoustique, 69131 Ecully Cedex—France

J. Turbomach 114(4), 756-764 (Oct 01, 1992) (9 pages) doi:10.1115/1.2928029 History: Received February 20, 1991; Online June 09, 2008

Abstract

Cooling of turbine blades is often achieved with cold discrete jets introduced at the wall. In this paper, a new method for computation of a wall boundary layer with discrete jet interactions is presented. The jets are assumed to be arranged in rows and the flow is assumed locally periodic in the row direction. The conservation equations are spatially averaged between two jet orifices. The resulting equations look like two-dimensional boundary layer equations, but with three-dimensional jet source terms. The numerical method solves the boundary layer equations with a Keller box method. A strong interaction with inviscid flow is also introduced in order to avoid numerical difficulty in the jet region. Three-dimensional jet conservation equations are solved with an integral method, under the boundary layer influence. A coupling of the two methods is performed. Comparisons with low-speed experimental data are presented, particularly near the jet orifices. It is shown that the agreement between the results of computation and the experiments depends on the jet behavior very near the jet exit.

Copyright © 1992 by The American Society of Mechanical Engineers
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