超高膨胀比涡轮气动噪声控制技术研究  

Research on aerodynamic noise control technology of an ultra-high expansion ratio turbine

作　　者：赵辛午[1] 黄洪雁[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院

出　　处：《哈尔滨工程大学学报》2016年第8期1076-1080,1117,共6页Journal of Harbin Engineering University

基　　金：国家重点基础研究发展计划(613188020201)

摘　　要：针对超高膨胀比涡轮气动噪声控制问题,从超高膨胀比涡轮的流动特征入手,探讨了喷嘴出口不均匀性和叶尖泄漏流动对涡轮气动噪声特性的影响,并有针对性地提出3种超高膨胀比涡轮气动噪声的控制方案:增加转静子之间轴向间距,喷管下俯、双侧修型、尾缘吹气和叶尖间隙流动控制。综合采用3种气动噪声控制方法对某单级超高膨胀比涡轮进行优化,结果表明本文提出的改进方法可在对涡轮气动性能影响不大的情况下,显著降低涡轮的气动噪声。To address the need for aerodynamic noise control of an ultra-high expansion ratio turbine, we discuss the effect of the non-uniform outflow of the nozzle and a tip leakage vortex on the aerodynamic noise characteristics of the turbine. We put forward three kinds of aerodynamic noise control methods, including adding an axial gap be-tween the rotor and stator;nozzle-down, bilateral repair and trailing edge blowing, and tip-leakage flow control. We then optimized a one-stage ultra-high expansion ratio turbine with respect to the suggested aerodynamic noise control methods. The results show that the aerodynamic noise of the single-stage ultra-high expansion ratio turbine is signifi-cantly reduced after the proposed noise-control optimization, and this optimization has little impact on the turbine＇s aerodynamic performance.

关 键 词：超高膨胀比涡轮 气动噪声 流动特征 叶形优化 数值模拟 激波控制 

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]