基于Bezier曲线的非轴对称端壁流动控制模拟与实验研究  

Simulation and Experimental Study of Non-axisymmetric Endwall Flow Control based on Bezier Curve

作　　者：朱培模 周霖 付海晏 蔡乐[2] 王松涛[2] ZHU Pei-mo;ZHOU Lin;FU Hai-yan;CAI Le;WANG Song-tao(AEEC Guiyang Engine Research Institute,Guiyang 550081,China;School of Engrgy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]中国航发贵阳发动机设计研究所,贵州贵阳550081 [2]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《节能技术》2022年第5期456-462,共7页Energy Conservation Technology

基　　金：航空发动机及燃气轮机重大专项基础研究项目(J2019-Ⅱ-0021)。

摘　　要：本文基于Bezier曲线构建非轴对称端壁造型,分别选取10%、50%以及90%叶高处型面静压分布和原扇形叶栅进行对比分析以及对叶栅涡系结构和出口能量损失进行对比分析。结果表明,经过合理的调控端壁型面进行上端壁造型改造能够有效改变横向压力梯度,减少上端壁附面层厚度以及涡系强度。在0.7、0.8以及0.9马赫条件下进行数值计算得到了上端壁改造的非轴对称端壁造型,相对于原扇形叶栅可实现降低15%左右的能量损失,达到改善扇形叶栅中二次流的发展目标,从而实现降低二次流损失的目的。In this paper,the non-axisymmetric endwall model is constructed based on the Bezier curve,and the static pressure distribution at 10%,50%,and 90%of the blade height is compared with that of the original sector cascade.The vortex system structure and outlet energy loss are compared.The results show that modifying the shape of the shroud can effectively change the transverse pressure gradient and reduce the thickness of the shroud attachment layer and the strength of the vortex system after the reasonable control of the end wall surface.Numerical calculations at 0.7,0.8,and 0.9 Mach conditions were performed to obtain the non-axisymmetric endwall shape of the shroud modification,which can reduce the energy loss by about 15%compared with the original sector cascade,and achieve the goal of improving the development of secondary flow in the cascade,to achieve the purpose of reducing the secondary flow loss.

关 键 词：涡轮 二次流 非轴对称端壁 BEZIER曲线 

分 类 号：TK471[动力工程及工程热物理—动力机械及工程]