Program Design Of Through-flow Performance Prediction For Axial-radial Combined Compressor

Compressor is one of the most complicated components of aero-engines, and it’s always a major constrain in the design of aero-engines.The performance of a compressor will directly affect the quality of an aero-engine. In the current compressor design system althrough 3-D numerical simulation is more and more mature, through-flow calculation is the most important part up to now because of its fast calculation speed and explicit results. The paper focuses on the performance prediction method of compressors and the following parts are included.Based on previous studies a new streamline curvature equation that can be apllied to axial, centrifugal and combined compressor is deduced. For the centrifugal compressors, blade force term is considered because of the leaned calculation stations.Suitable empirical models for axial and centrifugal compressors are chosen according to the previous studies. In odered to use the centrifugal compressor models of meanline performance prediction to through-flow performance prediction, different spanwise and streamlinewise distributions of models are discussed.A program of performance prediction of compressors is written by Fortran90 and it fllows the modern code standard to ensure its maintainability.Two axial compressor cases, two centrifugal compressor cases and one combined compressor case are calculated by the program and its accuracy and applicability are validated due to comprasion with experimental data and NUMECA’s results.The program now can be used for axial, centrifugal and combined compressor, but its accuracy needs to be improved by modifying the empirical models. There is still a long distance before the program can be used in the design of compressors.