Use of the Characteristic Method for the Prediction of the Three-Dimensional Flow Field in High Transonic Compressors

[+] Author and Article Information
J. Martinon

Office National d’Etudes et de Recherches Aérospatiales (ONERA), 92320 Châtillon, France

J. Eng. Power 102(1), 96-103 (Jan 01, 1980) (8 pages) doi:10.1115/1.3230240 History: Received December 08, 1978; Online September 28, 2009


The strong pressure gradients that take place in high performance transonic axial flow compressors induce important viscous interaction effects. In order to estimate these effects and to calculate the flow field in the inviscid core, the perfect gas approach is necessary. A three-dimensional stationary characteristic method is used for such an approach, and numerical results are given for the flow field in: • the blade channel of a supersonic cascade with converging side walls, • the blade channel of an annular supersonic cascade, • the inlet region of a linear supersonic blade cascade with converging side walls.

Copyright © 1980 by ASME
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