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RESEARCH PAPERS

Distorted Flow Field in Compressor Inlet Channels

[+] Author and Article Information
P. Bry, P. Laval, G. Billet

Office National D’Etudes et de Recherches Aerospatiales, 92320 Chatillon, France

J. Eng. Gas Turbines Power 107(3), 782-791 (Jul 01, 1985) (10 pages) doi:10.1115/1.3239801 History: Received December 10, 1981; Online October 15, 2009

Abstract

Solving the complex inlet-distortion related problems in turbojets or turbofans has become crucial to the successful development of new-generation engines. In order to curtail costs, reliable prediction methods, both analytical and numerical, must be developed and implemented. ONERA has been studying this problem for several years now. This paper reports on the preliminary numerical investigations of the three-dimensional flow field in the annular duct extending in front of a compressor with distorted inflow. The computational approach is a fully unsteady time-splitting, finite difference method solving the inviscid flow equations with nonuniform steady boundary conditions. Some analytical examples are presented and discussed. Matching of this three-dimensional computer code with models representing rotating or fixed blade rows is under way and will be reported on in a future contribution.

Copyright © 1985 by ASME
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