周向槽机匣处理对某跨音转子性能的影响  

Influence of Circumferential Casing Grooves on Transonic Compressor Rotor Performance

作　　者：段真真[1,2] 柳阳威[1,2] 陆利蓬[1,2] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191 [2]先进航空发动机协同创新中心,北京100191

出　　处：《航空学报》2014年第8期2163-2173,共11页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(51376001;51136003);国家"973"计划(2012CB720205);航空科学基金(2012ZB51014)~~

摘　　要：为了研究处理机匣对压气机稳定性的影响并探讨其中的流动机理,采用数值模拟方法研究了一系列深度不同的周向槽处理机匣结构对跨音压气机转子Rotor37性能的影响。结果表明:叶尖泄漏涡与激波干涉后形成的堵塞区是诱发失速的主要原因。采用周向槽机匣处理可以显著增加转子的稳定裕度,且裕度增量与槽深度呈"双峰"关系;尺寸最优的浅周向槽和深周向槽可分别获得6.7%和7.3%的稳定裕度增加,而前者的效率损失更小。该处理机匣的扩稳机理在于减弱甚至移除了泄漏涡破碎形成的堵塞区。最后从动量方程的角度对深浅槽的扩稳机理分别进行了分析。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.

关 键 词：压气机 跨音压气机 稳定裕度 机匣处理 周向槽 叶尖泄漏流 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程] TK12[动力工程及工程热物理—工程热物理]