航空发动机高压旋转涡轮盘腔流动与换热

推进技术 ›› 2003, Vol. 24 ›› Issue (2): 118-121.

航空发动机高压旋转涡轮盘腔流动与换热

丁水汀,张东,陶智,徐国强

北京航空航天大学动力系北京 100083;北京航空航天大学动力系北京 100083;北京航空航天大学动力系北京 100083;北京航空航天大学动力系北京 100083

发布日期:2021-08-15

Numerical simulation for flow and heat transfer of a rotating turbine cavity with realistic engine parameters

Dept. of Jet Propulsion, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;Dept. of Jet Propulsion, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;Dept. of Jet Propulsion, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;Dept. of Jet Propulsion, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China

Published:2021-08-15

摘要/Abstract

摘要： 在同模型实验参数范围内,且数值解和实验解基本吻合的前提下,对发动机原型参数进行数值模拟,求解了旋转系下流体流动与换热微分方程组,通过对气体域和固体域进行共轭计算,并将动量方程与能量方程耦合求解。结果表明利用低参数下实验数据支持的数值计算程序对真实参数的模拟是合理的,对于复杂的非线性现象,数值外推法比传统实验外推更加准确。

关键词: 航空发动机;涡轮盘;传热;混合长度流动理论;数值仿真

Abstract: Numerical simulation was extended with the proposed mixing length equation for the cavity model with realistic engine parameters and the prediction was quite reasonable. It was believed that, for highly non-linear phenomena such as coolant through rotating cavity, this extension was more accurate than direct application of correlations from model tests.

Key words: Aircraft engine;Turbine wheel;Mixing length flow theory;Heat transfer;Numerical simulation

丁水汀,张东,陶智,徐国强. 航空发动机高压旋转涡轮盘腔流动与换热[J]. 推进技术, 2003, 24(2): 118-121.