MULTI-DISCIPLINARY DESIGN OF HIGH-SPEED COMPRESSORS FOR PROSPECTIVE TURBO-SHAFT ENGINE

摘要

In order to obtain higher efficiency thermodynamic cycles in prospective turbo-shaft engine, overall pressure ratio (PR) and efficiency of its compressor must be increased. Moreover there is a problem of growth potential of a compressor to develop a family of engines with increasing shaft power.This paper focuses on 3D Navier-Stokes aerodynamic design of a high pressure ratio compressors to identify compressor configuration, 3D blading and flow-path providing effective aerodynamics.This paper describes some observations appearing in the aerodynamic design of high-speed compact axial-centrifugal compressors achieving PR = 16  25 in 4  6 stages. Mechanical requirements are also taken into consideration.In-house and commercial validated 3D numerical tools are used to assess the quality of the aerodynamic and strength design.