A Transonic Compressor Design Methodology Including the Influence of 3D Passage Shock Waves

Abstract

Throughflow theory, as a design problem, is extensively used in the design of transonic axial flow compressors and fans. The losses caused by a simplified passage shock named shock loss model were taken into account in the design of transonic stages. However, the influences of shock waves on flow fields are still under development for transonic design. This problem is studied in the present paper. The basic equations of the throughflow method are re-derived under the concept of discontinuous passage averaging, and then, the distribution shock forces acied on the averaged throughflow fields are obtained. To evaluate these effects on averaged throughflow fields, a passage shock structure model is developed based on the previous models. Finally, the shock influences are assessed and compared in the present paper. It is demonstrated that the distribution shock forces have dramatically effects on the results of design.

Investigation of modification design of the fan stage in axial compressor

“…This target was originally implemented by Wennerstrom, the HTFC [2,3] single stage fan which was designed by him arrived at very high level that the pressure ratio was 2 and the adiabatic efficiency was 88%. After that, a series of design and experimental study about highly loaded transonic single or two-stage axial compressor and fan were carried out [4][5][6] in US and several developed countries. The two-stage highly loaded fan parts with a total pressure ratio of 4.3 were tested at compressor test equipment of Wright-Patterson AFB since 1989.…”