| Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance |
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| 作者姓名： | Wu Xianyu Li Xiaoshan Ding Meng Liu Weidong Wang Zhenguo |
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| 作者单位： | College of Aerospace and Material Engineering, National University of Defense Technology, ChangSha 410073, China |
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| 基金项目： | 国家高技术研究发展计划(863计划) |
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| 摘 要： | In order to investigate the effects of fuel injection distribution on the scramjet combustor performance, there are conducted three sets of test on a hydrocarbon fueled direct-connect scramjet test facility. The results of Test A, whose fuel injection is carried out with injectors located on the top-wall and the bottom-wall, show that the fuel injection with an appropriate close-front and centralized distribution would be of much help to optimize combustor performances. The results of Test B, whose fuel injection is performed at the optimal injection locations found in Test A, with a given equivalence ratio and different injection proportions for each injector, show that this injection mode is of little benefit to improve combustor performances. The results of Test C with a circumferential fuel injection distribution displaies the possibility of ameliorating combustor performance. By analyzing the effects of injection location parameters on combustor performances on the base of the data of Test C, it is clear that the injector location has strong coupled influences on combus- tor performances. In addition, an inner-force synthesis specific impulse is used to reduce the errors caused by the disturbance of fuel supply and working state of air heater while assessing combustor performances.
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| 关 键 词： | 燃烧器 超音速飞机 燃料 生产性能 |
| 收稿时间： | 2007-03-12 |
| 修稿时间： | 2007-11-16 |
Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance |
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| Wu Xianyu Li Xiaoshan Ding Meng Liu Weidong Wang Zhenguo.Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance[J].Chinese Journal of Aeronautics,2007,20(6):488-494. |
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| Authors: | Wu Li Xiaoshan Ding Meng Liu Weidong Wang Zhenguo |
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| Institution: | aCollege of Aerospace and Material Engineering, National University of Defense Technology, ChangSha 410073, China |
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| Abstract: | In order to investigate the effects of fuel injection distribution on the scramjet combustor performance, there are conducted three sets of test on a hydrocarbon fueled direct-connect scramjet test facility. The results of Test A; whose fuel injection is carried out with injectors located on the top-wall and the bottom-wall, show that the fuel injection with an appropriate close-front and centralized distribution would be of much help to optimize combustor performances. The results of Test B, whose fuel injection is performed at the optimal injection locations found in Test A, with a given equivalence ratio and different injection proportions for each injector, show that this injection mode is of little benefit to improve combustor performances. The results of Test C with a circumferential fuel injection distribution displaies the possibility of ameliorating combustor performance. By analyzing the effects of injection location parameters on combustor performances on the base of the data of Test C, it is clear that the injector location has strong coupled influences on combustor performances. In addition, an inner-force synthesis specific impulse is used to reduce the errors caused by the disturbance of fuel supply and working state of air heater while assessing combustor performances. |
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| Keywords: | scramjet combustor fuel injection direct-connect test Combustor Performance Scramjet Fuel Injection Effects Study synthesis specific impulse used reduce errors disturbance fuel supply working state heater assessing addition clear |
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