径向进气轴向出流旋转盘腔流动传热耦合分析及验证  

Coupled flow-heat transfer analysis and verification for a rotating cavity with radial intake and axial outflow

作　　者：李天禄 王鹏飞 郭文 LI Tian-lu;WANG Peng-fei;GUO Wen(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2022年第4期40-44,34,共6页Gas Turbine Experiment and Research

摘　　要：针对径向进气轴向出流压气机旋转盘腔流动、换热特性复杂,气流压力、温度及转子盘壁温测量困难,现有计算模型缺乏验证的特点,对压气机旋转盘腔流动换热及转子盘温度分布,进行了三维气热耦合数值模拟,并与基于整机环境下压气机转子盘温度场示温漆测量结果进行了对比验证。研究结果表明,压气机旋转盘腔中,气流从高半径流到低半径时,压力损失较大,有明显的温升;随着转速增加,盘腔内涡流沿径向拉伸,且涡核逐渐向高半径位置移动,盘心气流有被卷吸进入盘腔的趋势;压气机三级盘温度分布计算结果与试验结果基本一致,不同径向位置温度相对误差在2.12%~4.47%之间。三维流动传热耦合数值模拟方法可行、结果可信、精度较高,具有良好的工程适用性。For rotating cavity with radial inlet and axial outflow, it has complex flow and heat transfer characteristics, so it is difficult to measure its flow pressure, temperature and rotating disk wall temperature. It is also difficult to verify using current calculation model. In this paper, flow and heat transfer characteristic of compressor rotating cavity, distribution of compressor disk have been simulated by 3D coupled heat transfer methodology, and verified by thermal paint measurement results in whole engine environment. The results indicate that the pressure in compressor rotating cavity decreased and temperature increased while air flows from higher radius to lower radius. With the increase of rotation speed, vortex in cavity was stretched in the radial direction, and its core moved to higher radius. The trend showed that the center of the disk entrained into cavity. The calculation results of the compressor 3rd disk temperature distribution were consistent with the experimental results, and the relative error was between 2.12% and 4.47% in different radius position. The results show that the method is feasible for engineering application, and its results are reliable and have high accuracy.

关 键 词：航空发动机 旋转盘腔 流动传热耦合 示温漆 整机环境 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]