|
|||||
|
|
| 声能喷嘴供油级间驻涡燃烧室的性能试验 | |
| 引用本文： | 谭米,樊未军,张荣春,宋双文,邢菲.声能喷嘴供油级间驻涡燃烧室的性能试验[J].航空动力学报,2013,28(5):1142-1149. |
| 作者姓名： | 谭米 樊未军 张荣春 宋双文 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国家级重点实验室,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. 厦门大学物理与机电工程学院,福建厦门,361005 |
| 摘 要： | 对一种采用声能喷嘴供油方式的级间燃烧室进行了性能试验研究.试验结果表明:当进口马赫数为0.20～0.40,燃烧室的熄火余气系数为25～35,燃烧室的稳定工作范围较宽；随余气系数增大,出口温度分布均匀性提高；燃烧效率为96％～98％,随余气系数减小,燃烧效率降低；进口马赫数对点火性能、熄火性能、出口温度分布和燃烧效率的影响较小；壁面热点温度出现在凹腔的后壁面；总压损失系数为0.03～0.11,热态时比冷态时高0.015左右；CO和NOx的排放指数分别为20～46和0.9～2.1,进口马赫数、余气系数均对污染物排放有较大影响. |
| 关 键 词： | 级间燃烧室 驻涡燃烧室 声能喷嘴 燃烧性能 性能试验 |
| 收稿时间： | 6/5/2012 12:00:00 AM |
Experiment on performance of interstage turbine trapped vortex combustor with acoustic energy nozzle |
|
| TAN Mi,FAN Wei-jun,ZHANG Rong-chun,SONG Shuang-wen and XING Fei.Experiment on performance of interstage turbine trapped vortex combustor with acoustic energy nozzle[J].Journal of Aerospace Power,2013,28(5):1142-1149. | |
| Authors: | TAN Mi FAN Wei-jun ZHANG Rong-chun SONG Shuang-wen and XING Fei |
| Institution: | National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;China Aviation Powerplant Research Institute, Aviation Industry Corporation of China, Zhuzhou Hunan 412002, China;School of Physics and Mechanical and Electrical Engineering, Xiamen University, Xiamen Fujian 361005, China |
| Abstract: | Performance of an interstage turbine burner with an acoustic energy nozzle was investigated experimentally.The experimental result shows that the air excess coefficient of lean blowout is in the range of 25~35 under the condition of Mach number being 0.20~0.40,and the range of stable combustion is relatively wide.The uniformity of outlet temperature distribution is improved with the increase of air excess coefficient.The combustion efficiency is in the range of 96%~98%,and it decreases as the air excess coefficient decreases.Inlet Mach number has little effect on ignition performance,lean blowout performance,outlet temperature distribution and combustion efficiency.The maximum wall temperature locates on the after-wall of the cavity.The total pressure loss coefficient is in the range of 0.03~0.11,and it is about 0.015 higher in hot state than in cold state.The emission index of CO is in the range of 20~46 and that of NOx is in the range of 0.9~2.1.The inlet Mach number and air excess coefficient both have significant effect on the pollutant emission. |
| Keywords: | interstage turbine burner trapped vortex combustor acoustic energy nozzle combustion performance performance experiment |
| 本文献已被 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 | |