基于燃气涡轮动叶的非轴对称端壁数值研究  

Numerical Investigation of Non-axisymmetric Endwall for Gas Turbine Rotor

作　　者：张洪鑫[1] 李燕飞[1] 陈绍文[1] 王松涛[1] 王仲奇[1] ZHANG Hong-xin;LI Yan-fei;CHEN Shao-wen;WANG Song-tao;WANG Zhong-qi(Engine Aerodynamics Research Centre, Harbin Institute of Technology, Harbin 150001, China)

机构地区：[1]哈尔滨工业大学发动机气体动力研究中心

出　　处：《汽轮机技术》2019年第3期178-180,201,共4页Turbine Technology

基　　金：国家自然科学基金项目(51436002)

摘　　要：为揭示非轴对称端壁控制涡轮动叶二次流的物理机制,建立了一种新型的Bezier曲线造型方法,采用数值模拟的方式,对某一燃气涡轮的第一级动叶进行研究。结果表明,此造型法通过合理地调整横向压力梯度,从而有效地推迟通道涡的发展,使得通道涡的强度和尺度都小于轴对称端壁对应的情况,进而减小了损失,提升了效率,最优方案使得相对总压损失减小了4.7%,效率提升了0.48%。In order to explore the physical mechanism of non-axisymmetric endwall to control secondary flow, a new Bezier modeling method is developed to study the certain turbine rotor in the first stage by numerical simulation method. The results show that the development of passage vortex is suppressed effectively because the transverse pressure gradient is adjusted reasonably by this method, and thus the intensity and the size of the channel vortex are smaller than that of the axisymmetric endwall, and then the flow loss is reduced and the efficiency is increased, the relative total pressure loss is reduced by 4.7%, and also the efficiency is increased by 0.48% in the optimum case.

关 键 词：非轴对称端壁 Bezier曲线造型法 气动性能 通道涡 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]