2D flow calculation investigation method for GTE multistage axial compressors

Abstract

The main provisions of the two-dimensional calculation method span pre-and transonic flow in the axial multistage compressor, designed to study the flow structure and the overall characteristics of the object is presented. The results of numerical studies of flow in transonic stage axial compressor, axial multistage compressor modern aircraft engine are shown. The comparison of the results with experimental studies is demonstrated. The influence of the regulatory program guide vanes multistage axial compressor at its summary characteristics is shown.