弯曲叶片造型对涡轮叶栅作用力影响的非定常数值研究  

Unsteady Numerical Study of Effects on Turbine Blade Forces for the Bowed Blade

作　　者：杨彤[1] 王松涛[1] 姜斌[2] 

机构地区：[1]哈尔滨工业大学发动机气体动力研究中心,黑龙江哈尔滨150001 [2]哈尔滨工程大学动力与能源工程学院,黑龙江哈尔滨150001

出　　处：《推进技术》2013年第6期760-767,共8页Journal of Propulsion Technology

摘　　要：为了研究弯曲叶片对涡轮叶片非定常气动力的控制作用,采用非定常数值模拟方法对高压涡轮两级的内部流场进行了计算,研究了第一级静叶采用正弯叶片时,汽轮机涡轮叶片非定常气动力和非定常压力场的变化。结果表明,采用弯曲静叶的设计方法,通过改变静叶出口处径向压力梯度和涡量分布,能够有效抑制动静叶片表面气动力的非定常脉动作用。但弯叶片给非定常压力场带来的改善是局部的,其对叶片中间截面改善最为显著。从整体上来看,正弯曲的静叶设计对于减小非定常流场中的压力脉动是有益的。In order to study the control capability of curved blade for turbine blade unsteady forces, nu merical simulations on the unsteady flow in two stages of a HP turbine were performed. The change of the unsteady blade forces and pressure were investigated when the stator of the first stage used the positive bowed blade. The results show when the bowed blade is used, it can suppress the unsteady pulsing of the forces acting on the turbine cascades by changing radial pressure gradient and vorticity distribution in the outlet of stator. But it is a locally beneficial effect for the unsteady pressure, and a clear beneficial effect for the midsection of the blade. Regarding it as a whole,the positive bowed blade decreases the pulsing of the pressure in the unsteady flow field remarkably.

关 键 词：高压涡轮 正弯叶片 非定常性 型面压力 叶片力 

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]