Test of Supersonic Compressor Cascade with Splitter Vanes and Vortex Generators on Blades.

摘要

The report describes experimental research conducted with a linear,stationary,supersonic compressor cascade with blades of constant spanwise geometry and contoured sidewalls. The cascade incorporated splitter vanes midway between blades in the latter half of each blade passage. The influence of splitter vane orientation was investigated. The investigation covered a range of Mach numbers from 1.40to 1.50and a range of static pressure ratios. This report describes work accomplished with vortex generators mounted on the suction surfaces of the blades. (Modified author abstract)