叶顶喷气对跨声转子近失速点流动的影响  

Effect of tip injection on the flow of near-stall condition in a transonic rotor

作　　者：贾惟[1] 刘火星[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191

出　　处：《航空动力学报》2011年第12期2731-2740,共10页Journal of Aerospace Power

基　　金：重点实验室基金(9140C4103091003)

摘　　要：利用数值模拟的方法研究了叶顶喷气对跨声转子性能及近失速点流动的影响.研究表明:在+65°的喷气角度下,喷气能保持效率不降低的同时使转子喘振裕度的绝对值提高4.48%.此外喷气还能改善转子叶片吸力面的流动,减弱叶尖泄漏涡的强度,同时使泄漏涡的轨迹更贴近叶片吸力面,这也是喘振裕度大幅提高的物理原因.Effect of tip injection on the performance and the flow of near-stall condition of transonic axial compressor rotor was investigated numerically.The result shows that the stall margin of this transonic rotor gains an absolute improvement of 4.48% by tip injection while the efficiency remains unchanged at the injection angle of ＋65°.Furthermore,the separation on the suction side of the rotor and intensity of the tip leakage vortex are both weakened.Besides,the trajectory of the tip leakage is more inclined to the suction side of the blade which mainly leads to the increase of stall margin.

关 键 词：跨声转子 叶顶喷气 近失速 泄漏涡 喘振裕度 

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]