| 涡轮级间单涡燃烧室壁温研究 |
| |
| 引用本文： | 张荣春,樊未军,邢菲.涡轮级间单涡燃烧室壁温研究[J].航空动力学报,2010,25(7):1512-1517. |
| |
| 作者姓名： | 张荣春 樊未军 邢菲 |
| |
| 作者单位： | 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科技重点实验室,北京100191
2. 浙江大学,航空航天学院,杭州,310027 |
| |
| 摘 要： | 由于燃烧区和壁面的距离过近,驻涡燃烧室壁温过高的问题一直存在,影响其在实际发动机上的应用.对某涡轮级间驻涡燃烧室进行壁温分布试验研究,研究供油量、主流进气参数对壁温分布的影响,并考察燃烧室的冷却和进气结构是否合理.试验结果表明,试验件的最高壁温出现在凹腔后壁面;供油量和主流马赫数对试验件的壁温分布趋势影响较大,主流温度对壁温分布趋势的影响较小.
|
| 关 键 词： | 驻涡燃烧室 冷却 壁温 凹腔 进气参数 |
| 收稿时间： | 2009/5/31 0:00:00 |
| 修稿时间： | 2009/12/29 0:00:00 |
Study of wall temperature on the interstage turbine single vortex combustor |
| |
| ZHANG Rong-chun,FAN Wei-jun and XING Fei.Study of wall temperature on the interstage turbine single vortex combustor[J].Journal of Aerospace Power,2010,25(7):1512-1517. |
| |
| Authors: | ZHANG Rong-chun FAN Wei-jun and XING Fei |
| |
| Institution: | 1. National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China2. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China;1. National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China2. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China;1. National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China2. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China |
| |
| Abstract: | Because the distance between combustion zone and wall is very short,the overhigh wall temperature is a longstanding problem of trapped vortex combustor(TVC),which limits the actual application of TVC.The experimental study of wall temperature distribution on the TVC was reported in the paper,and the influences of fuel supply quantity and inlet parameters of main stream on the wall temperature distribution were investigated.Meanwhile,the rationality of cooling structure and air jet entrance structure was analyzed.The test results show that the hot spot temperature of combustor appears in the after-wall.The distribution of wall temperature is greatly influenced by the fuel supply quantity and the mach number of main stream,but little influenced by the temperature of main stream. |
| |
| Keywords: | trapped vortex combustor cooling wall temperature cavity inlet air parameter |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
|
