The aviation gas-turbine engine axial-centrifugal compressor flow calculation research
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 numeri-cal investigation of the flow in the axial stages, end cen-trifugal stage and axial-centrifugal compressor as a whole was carried out. The overall characteristics and flow struc-ture in compressor were showed. the calculation results and the experimental data comparison was present.