Investigation of a One Stage Axial Flow Supersonic Compressor, Part 1. Global Performance of the Blunt Trailing Edge Blade Rotor R 32

摘要

Overall performance tests of supersonic rotor with blunt trailing edge blades were carried out at air-equivalent tip speeds up to 430.m/sec. All tests were conducted in Freon-12-air mixture. The rotor has a 40 cm tip diameter and a constant hub-tip ratio of 0.85. No inlet guide vanes or stator were used. The overall performance, as obtained from detailed surveys taken downstream of the rotor, are presented under the form of mass weighted values. (Author)