摘要
为设计一套适用于燃气轮机第1级涡轮导叶的高效冷却结构,将一套涡轮传热设计方案应用于涡轮导叶冷却结构设计中,数值模拟结果表明:中后部冲击射流能够有效冲刷叶片内表面,降低了叶片吸力侧中部壁面温度,同时形成较大漩涡结构降低压力侧中部的壁面温度;通过设计,得出冷却结构最大外壁面无量纲温度为0.849,冷却效率为0.651,设计目标冷却气体的流量为127 g/s,实际流量93 g/s;采用该设计流程能够有效降低冷却结构设计的盲目性,使冷却结构设计更加灵活方便。
To design a highly efficient cooling structure for gas turbine engine first stage turbine guide vanes, a turbine heat transfer design was introduced to the cooling structure design. The numerical simulation results show that impinging jet in the middle and tail scours the inside of the blade effectively, the temperature of the middle section of the suction side is decreased. Simultaneously, the eddy is formed, and then the temperature of the middle section of the pressure side is reduced. The highest outside blade wall dimensionless temperature is 0.849 with a cooling efficiency of 0.651. The cooling gas mass flow designed was 127 g/s while the actual mass flow was 93 g/s. This design progress helps avoid the uncertainty in designing cooling structure and make it more flexible.
出处
《中国电机工程学报》
EI
CSCD
北大核心
2014年第5期800-807,共8页
Proceedings of the CSEE
基金
国家自然科学基金委创新研究群体科学基金项目(51121004)~~
关键词
涡轮导叶
管网计算
气热耦合
冷却结构
温度分布
turbine vane
pipe network calculations
aero- thermal conjugated
cooling structure
temperature distribution
