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In multi-spool engines,the downstream compressor experiences a rotating inlet distortion if rotating stall occursin upstream compressor,which may induce the instability of the whole compressor.In this paper,the compressordynamic behavior is the major focus.The experiment was carried out on a single-stage low-speed axial-flowcompressor.A rotating distortion generator equipped with different distortion sector(s)was designed to producedifferent rotating inlet distortion clockwise or counterclockwise with up to 100% of the compressor design speed.The distortion sector can be installed single or in some combination such as four sectors together.Three types ofdistortion sector/combination are used in the research work,which are single 30 degree sector,four 30 degree sec-tors and single 120 degree sector.It is found that the total pressure loss caused by rotating sector(s)increaseswhen the distortion speed rises.For co-rotating distortions,all the three types of inlet distortion exhibited a peakin stall margin degradation when the distortion speed corresponded to roughly 50% of rotor speed.Thetwo-dimensional numerical simulations of the compressor flow field clearly show the propagation of the distur-bances trigged by the distortion sector(s).
The multi-spool engines, the downstream compressor experiences a rotating inlet distortion if rotating stall occursin upstream compressor, which may induce the instability of the whole compressor.In this paper, the compressordynamic behavior is the major focus.The experiment was carried out on a single-stage low-speed axial-flow compressor. A rotating distortion generator equipped with different distortion sector (s) was designed to produceififferent rotating inlet torque or clockwise or counterclockwise with up to 100% of the compressor design speed. or in some combination such as four sectors together.Three types of distortion sector / combination are used in the research work, which are single 30 degree sector, four 30 degree sec-tors and single 120 degree sector. It is found that the total pressure loss caused by rotating sector (s) increaseswhen the distortion speed rate. For co-rotating distortions, all the three types of inlet distortionached ap eakin stall margin degradation when the distortion velocity corresponded to roughly 50% of rotor speed. Thetwo-dimensional numerical simulations of the compressor flow field clearly show the propagation of the distur-bances trigged by the distortion sector (s).