驻涡燃烧室发散冷却方案试验

张荣春; 樊未军; 宋双文; 邢菲; 孔祥雷

驻涡燃烧室发散冷却方案试验

1.
北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点试验室, 北京 100191
2.
中国航空工业集团公司中国航空动力机械研究所, 湖南株洲 412002
3.
浙江大学航空航天学院, 杭州 310027

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出版历程
- 收稿日期: 2010-12-21
- 修回日期: 2011-07-19
- 刊出日期: 2011-12-28

Experimental investigation on transpiration cooling of trapped vortex combustor

1.
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2.
China Aviation Powerplant Research Institute, Aviation Industry Corporation of China, Zhuzhou Hunan 412002, China
3.
School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China

摘要

摘要: 设计了两种适用于驻涡燃烧室的发散冷却结构,发散孔的倾角分别为30?和150?,并通过试验研究了两种冷却结构在不同位置处,不同温比及吹风比条件下的冷却效果.试验结果表明,两种冷却结构均具有较高的绝热效率;两种结构的绝热效率随主流温度或吹风比的变化规律相同;凹腔前壁面的绝热效率最高,后壁面的绝热效率最低;在相同试验条件下,倾角150?冷却结构的绝热效率高于倾角30?冷却结构的绝热效率;随着冷却气量的减小,两者之间的差距逐渐增大.最后,通过数值计算方法对试验结果进行了分析.
- 驻涡燃烧室 /
- 发散冷却 /
- 主流温度 /
- 吹风比 /
- 绝热效率
Abstract: Two kinds of transpiration cooling schemes of trapped vortex combustor were designed,and two angles of transpiration cooling holes were 30 ? and 150 ?.The cooling efficiency test was conducted to study the performance of cooling in different locations,different temperature ratios and blowing ratios.The experimental results show that two cooling structures have high cooling efficiency;and the cooling efficiency variation with mainstream temperature or blowing ratio is similar to each other.For the wall of cavity,the cooling efficiency of fore-wall is the highest and the cooling efficiency of after-wall is the lowest.Under the same experimental conditions,the cooling efficiency of the structure at angle 150 ? is higher than that of the structure at angle 30 ?.At the same time,with the decline of cooling gas rate,the difference between them will increase.Finally,the test results were analyzed by numerical methods.
- trapped vortex combustor /
- transpiration cooling /
- mainstream temperature /
- blowing ratio /
- cooling efficiency

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参考文献(14)

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