Experimental investigation and analysis of an axial compressor stage with 45° circumferential inlet flow pressure distortion

摘要

The effects of screen-induced circumferential inlet total pressure distortion on an axial flowcompressor stage are investigated with the help of a high speed subsonic compressor test rig. The overallperformance for rotor with and without circumferential inlet flow total pressure distortion are obtained atmiddle equivalent-speed (8130 rpm).Detailed flow measurements around the circumference at 5 radialpositions are made at 3 axial locations. The results show that, at middle equivalent-speed, the compressorstage is weakly affected under a low magnitude distortion. With inlet flow total pressure distortion, Stallpressure ratio of rotor is improved 1.8 percent and the equivalent mass flow is decreased from 3.23kg/second to 3.16 kg/second if compared with clean inlet flow. The influenced sector of absolute flowangle is about a 90° circumferential extent at rotor inlet and a 75 o circumferential extent at rotor outlet. Inaddition, there are some differences between the distorted circumferential extent of absolute flow angleand the distorted circumferential extent of pressure. Enlargement and traverse of the distortedcircumferential extent of pressure are not obvious at rotor outlet. Indeed, circumferential pressuredistortion extent enlarged about 100 percent at stator outlet. The magnitude of circumferential totalpressure distortion is enhanced at rotor outlet and attenuated at stator outlet.