IMPROVED BLADE PROFILE LOSS AND DEVIATION ANGLE MODELS FOR ADVANCED TRANSONIC COMPRESSOR BLADINGS .2. A MODEL FOR SUPERSONIC-FLOW

New binding concepts as used in,modern transonic axial-flow compressor s require, improved loss and deviation angle correlations. The new mod el presented in this paper incorporates several elements and treats bl ade-row flows having subsonic and supersonic inlet conditions separate ly. The second part of the present report focuses on the Extension of a well-known correlation for cascade losses at supersonic inlet flows. It was originally established for DCA bladings and is now modified to reflect the flow situation in blade rows having low-cambered, arbitra rily designed blades including precompression blades. Finally, the ste ady loss increase from subsonic to supersonic inlet-flow velocities de monstrates the matched performance of the different correlations of th e new model.