The aviation gas-turbine engine axial-centrifugal compressor flow calculation research

Abstract

 The axial-centrifugal compressor two-dimensional sub- and transonic flow throughflow calculation method intended for the study of the flow structure and overall characteristics main positions were provided. The numerical investigation of the flow in the axial stages, end centrifugal stage and axial-centrifugal compressor as a whole was carried out. The overall characteristics and flow structure in compressor were showed. the calculation results and the experimental data comparison was present.