周向槽机匣处理的数值研究及扩稳机理分析  

Numerical Investigation of the Circumferential Grooved Casing Treatment and Analysis of the Mechanism of Improving Stall Margin

作　　者：张皓光[1] 楚武利[1] 吴艳辉[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《机械科学与技术》2010年第3期346-350,357,共6页Mechanical Science and Technology for Aerospace Engineering

基　　金：中国博士后科学基金项目(20090451395);航空基金项目(2007ZB53021);航空科技创新基金项目(08B53004)资助

摘　　要：结合周向槽机匣处理试验结果,采用全三维的数值方法对带周向槽机匣处理的亚音速轴流压气机内部流动进行研究。试验与数值结果均表明周向槽机匣处理能扩大压气机的稳定工作范围,同时略微地降低压气机效率。在两个转速下,数值模拟结果与试验结果符合良好。通过详细地分析压气机叶顶流场表明实体壁机匣时,触发该压气机失速的主要原因是间隙泄漏涡涡核破碎,使得叶顶通道堵塞程度严重。采取周向槽机匣处理能降低产生叶尖泄漏运动的驱动力,有效地削弱了间隙泄漏流造成的负面影响。与此同时,周向槽具有抽吸或吹除机匣端壁区低相对总压流体的能力,使低能气团在叶顶通道堆积的范围大为缩小,提高了叶顶通道内的流通能力。Combining the experimental results of grooved casing treatment, the numerical investigation of effect of circumferential grooved casing treatment on performance of subsonic axial flow compressor is performed. The results of experiment and calculation show that the circumferential grooved casing treatment which are effective in extending the operating range of compressor, generally tend to induce a little loss at the compressor efficiency. The calculated overall performance lines show good agreement with the experiments at the two rotation speeds. The fundamental flow mechanism obtained by detailed analysis of the flow-filed at the blade tip indicates that the primary reason for the subsonic compressor rotor is the breakdown of the clearance leakage vortex with smooth easing. The easing treatment weakens blade tip load and consequently reduces the driving power of tip leakage flow, thus restraining the development and decreasing of the adverse influence of tip leakage vortex. Circumferential grooves have the a- bility to pump or blow the low energy flux near end wall, and the action of blowing or bleeding can improve the current ability of blade tip passage.

关 键 词：轴流压气机 机匣处理 数值模拟 流场 泄漏涡 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]