摘要
为揭示叶顶凹槽对轴流压气机气动性能的影响和机理,本文对一试验台转子进行了全工况数值模拟,计算性能与试验结果取得很好的一致性。在此数值模型基础上对叶顶凹槽及其改进结构—叶顶篦齿进行了数值研究,研究分析表明:叶顶凹槽降低了泄漏流流量,但转子效率和失速裕度均有所下降,主要因为叶顶泄漏流在逆压梯度的作用下沿槽内向叶顶前缘方向流动,使前缘附近泄漏流反流程度增大,造成二次流损失及通道堵塞程度增大;凹槽深度是影响转子气动性能的主要因素。将叶顶凹槽分割开形成叶顶篦齿结构,在效率下降很小的情况下提高了转子的失速裕度;通过调整篦齿位置可进一步提高转子的气动性能;叶顶篦齿的应用存在特定的叶顶间隙范围。
In order to reveal the aerodynamic effects and mechanism of blade squealer tip on axial compressor,three-dimensional numerical simulation is conducted on a axial compressor,and the computational performance makes a good agreement with test results.Based on this numerical model the blade squealer tip and its improved structure – blade labyrinth tip is numerically studied,and we come to the following conclusions： Although blade squealer tip reduces the leakage flow mass,the efficiency and stall margin are declined,because the blade tip leakage flow moves forward to leading edge along the tank under the action of adverse pressure gradient effects,which makes the leakage reflux rate increased,and so the secondary flow loss and the degree of channel blockage have been aggravated;The groove depth is the main factor that have impact on the aerodynamic performance.By separating the squealer we get the blade labyrinth tip structure which improves rotor stall margin in the cost of slightly declined efficiency;aerodynamic performance can be further improved by adjusting the position of rotor labyrinth;and the application of blade labyrinth tip depends on the range of blade tip clearance.
出处
《流体机械》
CSCD
北大核心
2012年第6期33-39,共7页
Fluid Machinery
基金
西北工业大学研究生创业种子基金(z2011038)
关键词
轴流压气机
泄漏流
泄漏涡
叶顶凹槽
叶顶篦齿
axial compressor rotor
leakage flow
leakage vortex
blade squealer tip
blade labyrinth tip
