跨音速压气机转子叶尖间隙流场特性研究  

Effect of Tip Clearance Flow on Aerodynamic Performance of Transonic Compressor Rotor

作　　者：刘海旭 冯永志 任利 LIU Haixu;FENG Yongzhi;REN Li(Hadian Power Equipment Engineering Research Center Co.,Ltd.,Harbin 150046,China;China United Gas Turbine Technology Co.,Ltd.,Beijing 100000,China)

机构地区：[1]哈电发电设备工程研究中心有限公司,哈尔滨150046 [2]中国联合重型燃气轮机技术有限公司,北京100000

出　　处：《机械工程师》2021年第1期31-33,共3页Mechanical Engineer

摘　　要：为了分析跨音速转子叶尖间隙高度对转子叶尖流场的影响,以某轴流压气机跨音级为研究对象,采用全三维数值模拟方法,探讨了设计点和近失速工况下叶尖泄漏涡与激波的相互作用现象及不同的间隙条件下叶尖泄漏涡的演化、发展规律。计算结果表明,与设计点相比,近失速工况下间隙泄漏涡在流场中的位置及其与叶片弦长的夹角基本不变,但其对激波的影响更大。此外,随着叶尖间隙的增大,叶尖泄漏涡的强度、尺寸和影响范围也会逐渐增加,降低叶片的扩压能力。In order to analyze the influence of tip clearance on the performance of transonic compressor rotor tip flow field,the transonic compressor is calculated using 3D numerical simulation method,the interaction of shock with tip clearance vortex and the evolution of leakage vortex are discussed at design point and near stall condition.The result shows that compared with the design point,the position of the gap leakage vortex in the flow field and its angle with the chord length of the blade are basically unchanged,but the effect on the shock wave is stronger.Furthermore,the size,swirl intensity and the impact of leakage vortex will be strengthened gradually along with the increase of tip clearance,which reduces the diffuser capacity of blade.

关 键 词：跨音速压气机 转子 叶尖间隙 泄漏涡 激波 

分 类 号：TK47[动力工程及工程热物理—动力机械及工程]