无导叶对转涡轮高压动叶叶尖开槽的研究  

AN INVESTIGATION ON AERODYNAMIC PERFORMANCE OF A VANELESS COUNTER-ROTATING TURBINE WITH RECESSED HIGH-PRESSURE ROTOR TIPS

作　　者：张永军[1] 王会社[1] 王文三[1] 徐建中[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100190

出　　处：《工程热物理学报》2009年第3期402-406,共5页Journal of Engineering Thermophysics

基　　金：叶轮机械气动热力学国家自然科学基金重大项目(No.90718025)

摘　　要：对一无导叶对转涡轮高压动叶叶尖经开槽后的叶顶间隙流场进行了研究,CFD预测结果表明叶尖开槽后对转涡轮间隙泄漏损失的降低幅度超过了10%。对数值结果的分析表明,叶尖开槽后叶顶间隙通道内的粘性阻力增加,致使间隙流场结构发生变化,并引起了泄漏涡强减弱和泄漏流量下降;另外间隙泄漏流通过凹槽侧壁对叶片具有额外的做功能力。在本文的研究条件下,高压动叶叶尖开槽使得对转涡轮整级性能得到明显改善。A numeric study on the tip leakage flow field was achieved in a vaneless counter-rotating turbine with recessed high-pressure rotor tips. CFD results showed a decrease of over 10% for tip leakage loss. The viscous resistance＇s increase resulted from recessed tips led to the variation of tip leakage flow field, the weakening of leakage vortex and the reduction of leakage mass flow; moreover, the leakage flow could do extra work to blades through the sidewall surfaces of the recesses. Under the research conditions of this work, the recessed tips of high-pressure rotor improved the overall stage performance of the vaneless counter-rotating turbine evidently.

关 键 词：对转涡轮 泄漏流动 叶尖凹槽 涡系结构 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]