包含处理机匣影响的压气机旋转失速稳定性模型  

Investigation on the Theoretical Model Combined with the Novel Casting Treatmentwith Rotating Stall

作　　者：于巍巍[1] 王晓宇[1] 孙晓峰[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《航空动力学报》2005年第5期873-881,共9页Journal of Aerospace Power

基　　金：国家自然科学基金资助(50136010)

摘　　要：通过引入等价分布源方法,建立了处理机匣非定常壁面边界条件的数学模型,从而可以计算处理机匣对压力扰动波的影响。同时,将这一计算模块引入稳定性模型中,发展了可以包含处理机匣影响的稳定性模型。与某低压压气机以及NA SA的37号压气机的实验结果对比表明,所发展的三维旋转失速稳定性模型完全满足预测压气机稳定性的需求。此外,对37号压气机的数值计算表明,处理机匣的结构参数,如长度、背腔高度和壁面开孔率等都对稳定性有影响。理论上表明可以通过设计这些结构参数达到扩大压气机稳定性裕度的目的。The effect of a new casing treatment on the axial flow compressors rotating stall precursor wave was comprised in a three-dimensional rotating stall stability model presented in this paper. It is verified to be accurate enough in prediction of the inception of rotating stall compared with several experimental results. With the application of the equivalent surface source method, the interaction between the precursor wave and the casing treatment could be calculated. This means that there is a theoretical way to design the casing treatment. Some numerical experiments were conducted to evaluate the roles played by the structural parameters of the casing treatment. The result shows that adequate combinations of these parameters could extend the stall margin of a high-speed compressor.

关 键 词：航空、航天推进系统 旋转失速 处理机匣 稳定性模型 失速先兆波 等价分布源 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]