气热参数对涡轮外环冲击-气膜冷却特性影响的实验研究
Experimental Study on Effects of Aerothermal Parameters on Impingement-Film Cooling Characteristics of the Turbine Shroud
李自强 1王龙飞 1毛军逵 1毕帅 1吕城亮1
作者信息
- 1. 南京航空航天大学能源与动力学院,南京 210016
- 折叠
摘要
针对涡轮外环实际工况的复杂、多变特性,本文搭建了垂直进气、气热参数可调的涡轮外环冲击-气膜冷却实验台,借助红外测温技术,以正交实验法开展主流马赫数、吹风比和温比变化对涡轮外环冷却特性的关联性研究.结果发现:涡轮外环的面平均综合冷却效率随主流马赫数增大呈降低-升高-降低的变化趋势,Ma=0.5～0.8的研究范围内,Ma为0.6时涡轮外环具有最佳的综合冷却效果;提高吹风比以增大冷气流量和动压的方式增益涡轮外环内外侧的冲击、气膜冷却效果,吹风比每提高0.5,涡轮外环的面平均综合冷却效率提升1.46％～9.08％;温比由1.5变为1.6,涡轮外环的面平均综合冷却效率下降0.85％～7.95％.
Abstract
In view of the complex and variable characteristics of the turbine shroud in actual operat-ing conditions,an impingement-film cooling test platform for turbine shroud with vertical gas-intake and adjustable aerothermal parameters was built in this paper.Infrared temperature measurement technology was used to conduct orthogonal experiment to study the correlation between mainstream Mach number,blower ratio and temperature ratio on turbine shroud cooling characteristics.The results show that the surface average overall cooling efficiency of the turbine shroud presents a trend of decreasing-increasing-decreasing with the increase of mainstream Mach number.In the research range of Mach number is 0.5～0.8,the turbine shroud has the best overall cooling effect when Mach number is 0.6.By increasing the blowing ratio,the impingement and film cooling effects inside and outside turbine shroud can be gained by increasing the cool-gas flow rate and dynamic pressure.When the blowing ratio increases by 0.5,the surface average overall cooling efficiency of the turbine shroud increases by 1.46％～9.08％.When the temperature ratio changes from 1.5 to 1.6,the surface average overall cooling efficiency of the turbine shroud decreases by 0.85％～7.95％.
关键词
涡轮外环/冲击-气膜冷却/综合冷却效率/多变工况Key words
turbine shroud/impingement-film cooling/overall cooling efficiency/variable operating conditions引用本文复制引用
基金项目
江苏省自然科学基金青年基金(BK20200454)
中国博士后科学基金(2020TQ0147)
出版年
2024
NETL
NSTL
万方数据