23rd Congress of International Council of the Aeronautical Sciences, 8-13 September, 2002, Toronto, Canada
Paper ICAS 2002-2.1.4

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

N. Chen, H. Zhang, Y. Xu, W. Huang
Chinese Academy of Sciences, PRC

Keywords: 3d aerodynamics, compressor blade, low speed, multi-stage

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. 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.

view full paper