Joint prediction of aircraft gas turbine engine axial flow compressor off-design performance and surge line based on the expanded method of generalized functions

The paper discusses the development of simulation software COMPRESSOR for preliminary design of gas turbine engines axial flow and centrifugal compressor and multistage axial compressor off-design performance prediction. The off-design performance prediction for individual axial compressor stages is based on the modified Ol’shtein method. The surge line prediction for axial compressors is based on incidence angle limitation and Howell’s method.