THE EFFECTS OF DIFFERENT ROTATING INLET DISTORTION ON A LOW SPEED COMPRESSOR
In multi-spool engines, the downstream compressor experiences a rotating inlet distortion if rotating stall occurs in upstream compressor. For a multi-stage compressor, rotating stall in upstream stages also impose a rotating distortion on the downstream stages, which may induce the whole compressor instability. In this paper, we take for the rotating inlet distortion as an external motivation and the compressor dynamic 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 produce different 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 of distortion sector/combination are used in the research work,which are single 30degree sector, four 30degree sectors and single 120degree sector. It is found that the total pressure loss caused by rotating sector(s) increases when the distortion speed rises. For co-rotating distortions, all the three types inlet distortion exhibited a peak in stall margin degradation when the distortion speed corresponded to roughly 50％ of rotor speed,while, for counter-rotational distortions, no peak appeared. The two-dimensional numerical simulations of the compressor flow field clearly show the propagation of the disturbances trigged by the distortion sector(s).
JingXuan Zhang ZhiTing Tong HongWu Zhang ChaoQun Nie
Institute of Engineering Thermo physics, Chinese Academy of Sciences,Graduate School Chinese Academy Institute of Engineering Thermo physics, Chinese Academy of Sciences
国际会议
昆明
英文
455-459
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）