摘要
根据涡轮叶片的工作原理、流动换热机理,利用编程软件二次开发了包含ANSYS Fluent、ANSYS APDL和Flowmaster的流热固耦合计算系统,实现仿真软件自动调用、自动计算、不同计算域之间的数据交互和计算结果监控。利用该联合仿真软件对不同内冷通道高宽比的油冷涡轮导叶的燃气通道流动特性以及叶片换热特性进行了分析,结果表明:涡轮叶片内冷通道的结构设计和排布方案对油冷涡轮叶片冷却效果的影响较大,更改U型内冷通道高宽比会对油冷涡轮叶片的温度分布产生较大的影响;随着U型通道的高宽比增大,叶片的冷却效率随之降低,但降低幅度较小;高宽比更小的油冷结构设计,其叶片外壁面的温度分布更均匀,冷却覆盖区域更大,高宽比更大的油冷结构设计,其冷却效果更集中,冷却覆盖区域更小。
Based on the principle of turbine vanes and the mechanism of flow and heat transfer,a fluid-thermal-solid coupling calculation system incorporating ANSYS Fluent,ANSYS APDL,and Flowmaster was developed through secondary development.This system achieved the invocating of different programs,automatic calculation,data exchange between different computational domains,and monitoring of calculation results.Based on this integrated simulation software,the flow phenomena in the blade channels and heat transfer phenomena of oil-cooled turbine vanes with different cooling channels aspect ratios were analyzed.The results showed that the structural design and layout of cooling channels significantly influenced the cooling effectiveness of oil-cooled turbine vanes.Moreover,as the aspect ratio of U-shaped cooling channels increased,the oil-cooled turbine vanes had a great impact on the temperature distribution.With the increase of the aspect ratio of U-shaped channels,the cooling efficiency of the turbine vanes decreased,but the reduction was minor;oil cooling structures with smaller aspect ratios exhibited more uniform temperature distribution on the turbine vanes outer walls and a larger cooling coverage area,while oil cooling structures with larger aspect ratios had a more concentrated cooling effect and a smaller cooling coverage area.
作者
王瀚升
李育隆
徐诗杰
连华奇
李星剑
容诚钧
WANG Hansheng;LI Yulong;XU Shijie;LIAN Huaqi;LI Xingjian;RONG Chengjun(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;National Key Laboratory of Science and Technology on Aero-Engine Thermodynamics,Beihang University,Beijing 100191,China)
出处
《航空动力学报》
北大核心
2025年第11期197-209,共13页
Journal of Aerospace Power
基金
国家科技重大专项(J2022-Ⅳ-0005-0022)。
关键词
航空发动机
涡轮叶片
油冷涡轮导叶
流热固耦合仿真
二次开发
aeroengine
turbine vane
oil-cooled turbine guide vane
fluid-thermal-solid coupling simulation
secondary development
