低速轴流压气机旋转失速演化机制研究  

Investigation on the Rotating Stall in a Low-Speed Axial Compressor

作　　者：贺象 银越千 黄生勤 马宏伟[2] 魏巍[2] 

机构地区：[1]中国航空机械动力研究所,湖南株洲412002 [2]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空发动机》2016年第5期81-86,共6页Aeroengine

摘　　要：为深入探讨轴流压气机旋转失速机理,利用全环非定常数值模拟在出口边界添加节流阀模型模拟压气机节流过程,通过试验测量与数值模拟结果对比分析,澄清了低速轴流压气机失速先兆及失速团的产生和演化过程。研究结果表明:压气机在转子叶片安装角存在几何偏差的情况下,spike型失速先兆是由2阶模态的整阶扰动演化而来,并最终直接形成2个大尺寸全叶高的失速团;与轴对称转子模型相比,考虑存在几何偏差的转子模型的数值模拟结果更为接近试验测量结果。In order to further investigate the axial flow compressor rotating stall mechanism, the compressor stall process was simulated via the methods of full-annulus unsteady numerical simulation in which a throttle model was imposed on the outlet boundary. With the comparative analysis of the experimental and numerical results, the generation and evolution of the stall inception and the stall cell in a low-speed axial-compressor was clarified. The results indicate that two spike inceptions are induced by the shaft order perturbations of the second order and evolve into two full-span stall cells in this compressor in the case of some deviation in the rotor blade stagger angle.Comparing with the symmetric rotor model, the numerical results of the rotor model with geometry deviation agreed well with the experimental results.

关 键 词：轴流压气机 全环非定常数值模拟 节流阀模型 失速先兆 失速团 航空发动机 

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]