周向槽与间隙改型组合控制间隙流场数值模拟  

Numerical simulation on combination of circumferential groove and tip clearance modification to control tip clearance flow field

作　　者：张国臣 李志鹏 曹志远[2] 徐志晖 孙丹 ZHANG Guochen;LI Zhipeng;CAO Zhiyuan;XU Zhihui;SUN Dan(School of Aero-engine,Shenyang Aerospace University,Shenyang 110136,China;School of Power and Energy,Northwest Polytechnical University,Xi’an 710072,China)

机构地区：[1]沈阳航空航天大学航空发动机学院,沈阳110136 [2]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2024年第12期314-326,共13页Journal of Aerospace Power

基　　金：翼型、叶栅空气动力学重点实验室基金(614220121050125)。

摘　　要：设计了一种平行扩张式叶尖间隙来抑制转子叶尖间隙处的流动损失。对其进行数值模拟发现改型间隙可以有效地抑制转子吸力面处的尾流损失,使转子吸力面尾缘处由径向潜流与泄漏流掺混形成的机匣角区分离涡尺度减小。转子吸力面上激波作用位置向下游移动,边界层长度缩短,边界层分离程度减弱,研究表明改型间隙比设计间隙的峰值等熵效率提高0.374%,稳定裕度提高3.457%。为了提高改型间隙对涡流损失抑制的效果,在叶尖前缘加入周向单槽,研究表明组合方案降低了双泄漏流的风险,使主流与叶尖泄漏流交界面向通道内移动且熵值减小,延迟在小质量流量工况下由前缘溢出而导致的尖峰型失速的发生,且组合方案比设计间隙的稳定裕度提高4.105%,峰值等熵效率提高0.164%。A parallel dilation tip clearance was designed to inhibit the flow loss at rotor tip clearance.Through numerical simulation,it was found that the modified tip clearance can effectively suppress the wake loss at the trailing edge of the rotor and reduce the size of the corner separation vortex in the region of the casing formed by mixing the spanwise underflow and the leakage flow at the trailing edge of the suction surface.The position of shock waves action on the rotor suction surface moved downstream,which shortened the length of the boundary layer and weakened the separation degree of the boundary layer.The research showed that the peak efficiency of the modified tip clearance increased to 0.374%and the stability margin increased to 3.457%compared with the design tip clearance.To improve the effect of vortex loss suppression by the modified tip clearance,a circumferential single casing groove was added at the leading edge of the rotor tip.The results showed that the combination scheme can reduce the risk of double leakage flow,make the interface between the main stream and the tip leakage flow move into the channel and reduce the entropy,delay the occurrence of spike stall caused by leading edge spillage at low flow rate.Moreover,the stability margin and peak efficiency of the combination scheme increased by 4.105%and 0.164%,respectively,compared with the design tip clearance.

关 键 词：涡流损失 尾流损失 间隙改型 周向槽 积极螺旋度 径向潜流 

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]