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A RAPID NUMERICAL METHOD FOR 3D AERO DYNAMICS DESIGN OF COMPRESSOR BLADE ROW (APPLICATION TO A LOW SPEED EXPERIMENTAL MULTI-IDENTICAL-STAGE COMPRESSOR DESIGN)

A numerical method for 3D aerodynamic design of a compressor blade row in the present paper is developed based on the iterative calculations by successively using a grid generation method and a N.S. solver. At beginning the flow rate, the pressure ratio and the geometry of meridian pattern were given. The span-height distributions of inlet and exit pitch-wise-averaged flow angles of the blade row were obtained by the preliminary calculations. They are served to be the target parameters of the present calculation. Successively using a grid generation method and a N.S. solver, a 3-D blade configuration can be obtained. The optimal design can be obtained by a set of calculations with different span-height distributions of inlet and exit pitch-wise-averaged flow angles of the blade row. As an example an experimental compressor with three identical stages is shown.