1.5级涡轮动叶的非轴对称端壁造型数值研究
Numerical Research on Non-axisymmetric End Wall Modeling of 1.5-stage Turbine Blades
何振鹏 1杨成全 2黎柏春 2姚连峥 2赵福星 2蔡猛3
作者信息
- 1. 中国民航大学航空工程学院,天津 300300;重庆航天职业技术学院,重庆 400021
- 2. 中国民航大学航空工程学院,天津 300300
- 3. 中国民航大学工程技术训练中心,天津 300300
- 折叠
摘要
为探究端壁造型对涡轮动叶气动性能及流场特性的影响,分析非轴对称端壁造型对涡轮转子叶片的压差作用,开展基于非轴对称端壁造型的理论研究,提出一种涡轮动叶轮毂上凸、下凹的造型方案,研究非轴对称端壁造型对涡轮流场二次流损失的影响.数值模拟分析表明:非轴对称端壁造型对减小横向压差具有重要作用,在动叶轮毂鞍点处进行非轴对称端壁造型,比在通道内造型效果更好;涡轮动叶下端壁不同区间造型可有效降低涡轮动叶通道内的二次流流动损失,使用非轴对称端壁造型方法可有效地减小动叶出口总压损失系数0.132 2％.
Abstract
In order to investigate the effect of end-wall modeling on the aerodynamic performance and flow field charac-teristics of turbine blades,the effect of non-axisymmetric end-wall modeling on the differential pressure of turbine rotor blades was analyzed,and the theoretical study was carried out based on non-axisymmetric end-wall modeling.A modeling scheme with upper convex and lower concave hub of turbine blades was proposed,and the effect of non-axisymmetric end-wall modeling on the secondary flow loss of turbine flow field was studied.The numerical simulation results show that non-axisymmetric end wall shaping method plays an important role in reducing lateral pressure difference,and the non-axisym-metric end wall shaping at the saddle point of the rotor hub is better than the shaping in the channel.Different interval sha-ping of the lower end wall of the turbine can effectively reduce the secondary flow loss in the turbine lobe channel,and the use of non-axisymmetric end wall shaping method can effectively reduce the total pressure loss coefficient of 0.132 2％at the outlet of the turbine lobe.
关键词
涡轮动叶/非轴对称端壁/造型方法/总压损失系数/流场特性Key words
turbine blades/non-axisymmetric endwall/modeling method/total pressure loss coefficient/flow field char-acteristics引用本文复制引用
基金项目
中央高校基本科研业务费专项自然科学重点项目(3122023045)
出版年
2024
NETL
NSTL
维普
万方数据