位势场与涡轮端区二次流的相互作用机理研究  

A mechanism investigation of potential field-secondary flow interactions in turbine endwall regions

作　　者：綦蕾[1] 邹正平[1] 刘火星[1] 王雷[2] 

机构地区：[1]北京航空航天大学,航空发动机气动热力国防科技重点实验室,航空发动机数值仿真研究中心,北京100191 [2]中航工业沈阳发动机设计研究所涡轮室,辽宁沈阳110015

出　　处：《空气动力学学报》2012年第5期597-605,共9页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(51106004)

摘　　要：采用数值模拟方法,研究了某亚声速涡轮内部下游导叶位势场与动叶端区二次流和叶尖泄漏流的非定常相互作用,详细分析了不同时刻的流动特性。结果表明:受下游导叶的非定常位势作用影响,动叶出口瞬时时刻二次涡结构呈现明显的周期性变化,并导致动叶出口熵增和效率均随时间改变,文中利用旋涡运动学理论对产生这一现象的流动机理进行了深入探讨。The flow in turbomachiney is inherently unsteady, so investigating the unsteady interaction between the downstream pressure field and the end-wall flows is very important for improving the perform- ance of low-aspect-ratio, high-loaded turbine. This paper presents the results of a numerical study of the in- teraction between the end-wall secondary flow and tip leakage flow of the rotor and the downstream potential field of the stator in a low-aspect-ratio, subsonic turbine. The flow diagrams of tran-sient results were ana- lyzed in detail. The results indicate that the entropy rise and the efficiency at the exit of the rotor blade showed a significant periodic variation due to the unsteady interaction of the downstream pressure field. The periodic variation of the rotor performance is due to the unsteady interactions of the downstream pressure field with the secondary flow vortex and the tip leakage vortex, which has been interpreted using the theory of kinematic vortex transport.

关 键 词：位势场 二次流 非定常相互作用 涡轮端区 

分 类 号：V235.12[航空宇航科学与技术—航空宇航推进理论与工程]