DESIGN AND PERFORMANCE OF A HIGH- PRESSURE -RATIO, HIGHLY LOADED AXIAL-FLOW TRANSONIC COMPRESSOR STAGE

摘要

A 50-cm-diam axial-flow transonic compressor stage with multiple-circular-arc blades was designed and tested. At design speed, a rotor peak efficiency of 0.85 occurred at an equivalent weight flow of 29.3 kg/sec. Stage peak efficiency was 0.79 at 28.6 kg/sec. Stage total pressure ratio at peak efficiency was 1. 84. The stall margin at design speed was 5 percent. Rotor and stator losses were higher than predicted. The stator choked at design flow.