微型涡流发生器控制压气机叶栅二次流的数值研究  

Numerical Investigation on Secondary Flow Control in Cascade with Micro-Vortex Generator

作　　者：马姗 楚武利[1,2] 张皓光 旷海洋[1] 李相君[1] 

机构地区：[1]西北工业大学能源与动力学院,陕西西安710072 [2]先进航空发动机协同创新中心,北京100191

出　　处：《推进技术》2017年第12期2641-2651,共11页Journal of Propulsion Technology

基　　金：国家自然科学基金重点项目(51536006);国家自然科学基金(51576162);航空科学基金(2014ZB53014);陕西省自然科学基金(2015JM5202)

摘　　要：二次流对压气机叶栅的性能有很大影响,为了探究微型涡流发生器(MVG)对于低马赫数来流叶栅的二次流控制情况,以一进口来流Ma<0.1的高负荷轴流压气机叶栅为研究对象,用数值方法分别对设计攻角(-1°)以及失速攻角(8°)下的流场进行损失分析,并借鉴失速因子对不同组合形式的MVG进行对比。得出在-1°攻角下,大部分MVG具有延缓分离的作用,但都会引起损失增加;在8°攻角下,所有MVG都具有延缓分离、减少损失的作用。损失减少最多的一组VGdvg3达到6.3%,失速系数减小了46%,因此认为MVG对于大分离区域的控制较为有效。MVG主要控制0%~30%叶高方向损失,并且MVG的叶片间距以及安装位置也存在一个最佳范围,不易过大或过小。The performance of compressor cascade is considerably influenced by secondary flow. The present study was carried out on a high-loaded axial compressor cascade with incoming flow of Ma0.1 to investigate the effects of Micro-vortex generator（MVG）used in low-Mach number cascade on secondary flow. The study analyzed the loss of design and stall incidence angle with numerical method and compared the different combinations of MVG referring to stall indicator. Results show that most cases can restrain the region of separation in -1° incidence angle,but all of them cause the increase of loss. In 8° incidence angle,all cases can delay separation region and decrease loss. The case VGdvg3 shows the highest loss reduction benefit of 6.3%,and the stall coefficient is decreased by 46%,which indicates that MVG can control the large separation area effectively. The loss of 0%~30% span is mainly controlled by MVG,and there is an optimal range of vane＇s distance and installation position,too far or close is unsuitable.

关 键 词：低马赫数 轴流压气机叶栅 微型涡流发生器 二次流 

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]