Experimental investigation and analysis of an axial compressor stage with 45° circumferential inlet flow pressure distortion
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° 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.
experimental investigation axial compressor pressure distortion all performance pressure distribution
J.Huang H.Wu W.H.Du
School of power and Energy, Northwestern Polytechnical University, Xi’ an, 710072 China
国际会议
The Fifth International Conference on Fluid Mechanics(第五届国际流体力学会议)
上海
英文
2007-08-15（万方平台首次上网日期，不代表论文的发表时间）