چكيده لاتين :
Aerodynamic profiling of transonic axial compressors is carried out in
details, utilizing a theoretical method. The main governing equations consist of
continuity and momentum equations in cylindrical coordinate system. Steady
axisymmetric flow is assumed and the governing equations are solved in the
meridional plane, based on the well-known streamline curvature method. Actuator
disk theory is used for a rapid convergence of initial values of axial velocity
distribution. Profile and shock wave losses are modeled using semi-empirical
correlations. Main available data include; annulus air passage geometry, mass flow
rate, total inlet pressure and temperature, rotational speed and total pressure ratio. A
number of other data, like axial distribution of stage load factor along each stream
surface, specify and control the geometry and aerodynamic performance of each
blade row and the whole compressor. These latter data are altered through design
process to achieve an optimum configuration. Validation of theoretical results is
approved through redesigning an available compressor of a mini-turbojet engine.
Very good agreement is observed between the predicted blades geometries with
those of real case for most blades rows.
