周向槽机匣处理对某跨音转子性能的影响
收稿日期: 2013-10-30
修回日期: 2014-02-18
网络出版日期: 2014-02-21
基金资助
国家自然科学基金（51376001，51136003）；国家“973”计划（2012CB720205）；航空科学基金（2012ZB51014）
Influence of Circumferential Casing Grooves on Transonic Compressor Rotor Performance
Received date: 2013-10-30
Revised date: 2014-02-18
Online published: 2014-02-21
Supported by
National Natural Science Foundation of China (51376001,51136003); National Basic Research Program of China (2012CB720205); Aeronautical Science Foundation of China(2012ZB51014)
段真真 , 柳阳威 , 陆利蓬 . 周向槽机匣处理对某跨音转子性能的影响[J]. 航空学报, 2014 , 35(8) : 2163 -2173 . DOI: 10.7527/S1000-6893.2013.0546
In order to investigate the influence of casing treatment on compressor stability and to study its flow mechanism, numerical investigations are conducted to study the influence of circumferential casing grooves on the transonic compressor performance in Rotor37. A series of circumferential grooves with different depths are studied. The simulations reveal that the tip leakage vortex breaks down due to the interaction with passage shock and forms a recirculation zone which is mainly responsible for the onset of rotating stall. Circumferential casing grooves are able to delay stalls significantly. As a function of groove depth, the stall margin increment has two peaks. The stall margin increases by 6.7% and 7.3% with optimum shallow grooves and deep grooves, respectively, while the former result in even less loss in efficiency.The flow mechanism of stall margin improvement is that the casing treatment is able to reduce or even eliminate the recirculation zone caused by the tip leakage vortex breakdown. An analysis from the angle of momentum theorem is then carried out to explain the mechanism for shallow and deep grooves,respectively.
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