Aerodynamic Profiling of Transonic Axial Compressors

Aerodynamic profiling of transonic axial compressors is carried out indetails, utilizing a theoretical method. the main governing equations consist ofcontinuity and momentum equations in cylindrical coordinate system. steadyaxisymmetric flow is assumed and the governing equations are solved in themeridional plane, based on the well-known streamline curvature method. actuatordisk theory is used for a rapid convergence of initial values of axial velocitydistribution. profile and shock wave losses are modeled using semi-empiricalcorrelations. main available data include; annulus air passage geometry, mass flowrate, total inlet pressure and temperature, rotational speed and total pressure ratio. anumber of other data, like axial distribution of stage load factor along each streamsurface, specify and control the geometry and aerodynamic performance of eachblade row and the whole compressor. these latter data are altered through designprocess to achieve an optimum configuration. validation of theoretical results isapproved through redesigning an available compressor of a mini-turbojet engine.very good agreement is observed between the predicted blades geometries withthose of real case for most blades rows.