压气机周向槽处理机匣的轴向位置研究  

Deal location of a compressor's circumferential casing treatment

作　　者：祝剑虹[1] 朴英[1] 岂兴明[1] 周建兴[1] 

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《哈尔滨工程大学学报》2008年第4期342-347,共6页Journal of Harbin Engineering University

摘　　要：为研究处理机匣位置对压气机性能的影响,对跨音压气机rotor37进行了不同轴向位置周向处理槽的全三维定常数值模拟,在分析处理机匣扩稳机理的基础上研究了光壁机匣和各种处理机匣下的压气机流场结构.结果表明,周向槽处理机匣能在效率损失不大的情况下使压气机失稳边界向特性图的左上方移动,额定转速下的周向处理槽覆盖叶尖弦长中部时能获得3.35%的扩稳裕度,而效率损失仅为0.23%.在对比多种处理机匣下的压气机性能和内部流场分布后认为:设计点下的处理机匣应以覆盖叶尖中部为宜.In order to identify the effect of the location of casing treatment on a compressor, a full 3-D numerical simulation was made of casing treatments with circumferential grooves at different axial locations on transonic compressor-rotor 37. Following an analysis of the effects of casing treatment on stall margin, the flow fields of compressors with smooth casing or other different casing treatments were researched. This showed that circumferential casing treatment can increase stall margin at the cost of a small reduction in efficiency. More research on compressor performance and flow fields of different casing treatments showed that, if the circumferential grooves are in the middle part of a chord at the tip of the blade, they can increase the stall margin by 3.35% with only 0.23% efficiency loss. Therefore, it is suggested the optimal location for casing treatment lies in the middle part of the blade tip.

关 键 词：压气机 数值模拟 机匣处理 失稳 

分 类 号：TK12[动力工程及工程热物理—工程热物理]