Distorted Flow Field in Compressor Inlet Channels

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.