周向槽机匣处理对某跨音转子性能的影响

doi:10.7527/S1000-6893.2013.0546

流体力学与飞行力学

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周向槽机匣处理对某跨音转子性能的影响

段真真^1,2, 柳阳威^1,2, 陆利蓬^1,2

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

收稿日期:2013-10-30 修回日期:2014-02-18 出版日期:2014-08-25 发布日期:2014-02-21
通讯作者: 柳阳威，Tel.：010-82316455，E-mail：liuyangwei@buaa.edu.cn E-mail:liuyangwei@buaa.edu.cn
作者简介:段真真女，博士研究生。主要研究方向：叶轮机械气动热力学。Tel：010-82338155，E-mail：duanzhenzhen@sjp.buaa.edu.cn；柳阳威男，博士，副教授。主要研究方向：叶轮机CFD，叶轮机复杂流动机理及流动控制。Tel：010-82316455，E-mail：liuyangwei@buaa.edu.cn；陆利蓬男，博士，教授，博士生导师。主要研究方向：湍流，叶轮机械复杂流动机理及其在工程计算中的应用。Tel：010-82317413，E-mail：lulp@buaa.edu.cn
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

DUAN Zhenzhen^1,2, LIU Yangwei^1,2, LU Lipeng^1,2

1. National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics, School of Energy and Power Engineering, Beihang University, Beijing 100191, China;
2. Collaborative Innovation Center of Advanced Aero-Engine, Beijing 100191, China

Received:2013-10-30 Revised:2014-02-18 Online:2014-08-25 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)

摘要/Abstract

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。

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

Abstract:

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.

Key words: compressor, transonic compressor, stall margin, casing treatment, circumferential groove, tip leakage flow

中图分类号:

V231.3
TK12

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.

DUAN Zhenzhen, LIU Yangwei, LU Lipeng. Influence of Circumferential Casing Grooves on Transonic Compressor Rotor Performance[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(8): 2163-2173.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

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

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