| 冲压发动机驻涡燃烧室燃烧性能试验 |
| |
| 引用本文： | 何小民,秦伟林,朱志新,牛志刚,费立群,彭力,杨承宇.冲压发动机驻涡燃烧室燃烧性能试验[J].航空动力学报,2015,30(1):16-21. |
| |
| 作者姓名： | 何小民 秦伟林 朱志新 牛志刚 费立群 彭力 杨承宇 |
| |
| 作者单位： | 南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;中国航天科工集团公司 北京动力机械研究所 高超声速冲压发动机技术重点实验室, 北京 100074;南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;中国航天科工集团公司 北京动力机械研究所 高超声速冲压发动机技术重点实验室, 北京 100074;中国航天科工集团公司 北京动力机械研究所 高超声速冲压发动机技术重点实验室, 北京 100074;中国航天科工集团公司 北京动力机械研究所 高超声速冲压发动机技术重点实验室, 北京 100074;中国航天科工集团公司 北京动力机械研究所 高超声速冲压发动机技术重点实验室, 北京 100074 |
| |
| 基金项目： | 高超声速冲压发动机技术重点实验室开放基金;南京航空航天大学博士学位论文创新与创优基金(BCXJ14-01) |
| |
| 摘 要： | 针对某冲压发动机驻涡燃烧室模型,进行了不同进口温度、进口速度系数和余气系数下燃烧室燃烧性能的试验研究,研究结果证明:随着进口速度系数的增加(0.20~0.35),点火总油气比和贫油熄火油气比增加,燃烧效率变化不明显;随着进口温度的增加(573~773K),点火总油气比和贫油熄火油气比下降,燃烧效率提高;随着余气系数的增加(1.1~2.1),燃烧效率提高.试验中获得最小点火总油气比为0.003 5,最小贫油熄火油气比为0.002 8,最高燃烧效率93%.研究证明了驻涡应用于冲压发动机燃烧室的可行性.
|
| 关 键 词： | 冲压发动机 驻涡 燃烧室 燃烧性能 进口气动参数 |
| 收稿时间： | 9/9/2013 12:00:00 AM |
Experiment on combustion performance of ramjet engine withtrapped-vortex combustor |
| |
| HE Xiao-min,QIN Wei-lin,ZHU Zhi-xin,NIU Zhi-gang,FEI Li-qun,PENG Li and YANG Cheng-yu.Experiment on combustion performance of ramjet engine withtrapped-vortex combustor[J].Journal of Aerospace Power,2015,30(1):16-21. |
| |
| Authors: | HE Xiao-min QIN Wei-lin ZHU Zhi-xin NIU Zhi-gang FEI Li-qun PENG Li and YANG Cheng-yu |
| |
| Institution: | Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute, China Aerospace Science and Industry Corporation, Beijing 100074, China;Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute, China Aerospace Science and Industry Corporation, Beijing 100074, China;Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute, China Aerospace Science and Industry Corporation, Beijing 100074, China;Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute, China Aerospace Science and Industry Corporation, Beijing 100074, China;Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute, China Aerospace Science and Industry Corporation, Beijing 100074, China |
| |
| Abstract: | Experiments were conducted to study the combustion performance of ramjet engine model with trapped-vortex combustor under different inlet temperatures and velocity coefficients. The results show: with the increase of inlet velocity coefficient increases (0.20-0.35), the ignition and lean blowout fuel air ratios rise, and the combustion efficiency changes little. As the inlet temperature increases(573-773K), the ignition fuel air ratio and lean blowout fuel air ratio decreases, and the combustion efficiency increases varying with increase of the excess air coefficient(1.1-2.1). The minimum ignition fuel air ratio and the lean blowout fuel air ratio is 0.0035 and 0.0028 respectively, the maximum combustion efficiency obtained from experiment is 93%.The results prove the feasibility of applying the cavity to the ramjet combustor. |
| |
| Keywords: | ramjet engine trapped-vortex combustor combustion performance inlet aerodynamic 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 |
|
