| 气-气喷注器流量特性实验研究 |
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| 引用本文： | 杜正刚,金平,杨立军,蔡国飙,张蒙正.气-气喷注器流量特性实验研究[J].航空动力学报,2007,22(3):500-504. |
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| 作者姓名： | 杜正刚 金平 杨立军 蔡国飙 张蒙正 |
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| 作者单位： | 1. 北京航空航天大学,宇航学院,北京,100083
2. 中国航天科技集团公司第十一研究所,西安,710100 |
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| 摘 要： | 对气-气喷注器的两种类型七种结构的喷嘴进行了带反压的流量特性试验,选择其中一种结构的喷嘴展开在单路工作的流量特性试验,重点考察进口压力和反压变化对喷嘴流量特性的影响和氧化剂喷嘴和燃料喷嘴的相互作用;通过试验测量和对实验数据的拟合,得到喷嘴流量系数的经验公式.所得的结论对全流量补燃循环发动机气-气喷注器的优化设计有一定的指导意义.
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| 关 键 词： | 航空、航天推进系统 气-气喷注器 流量特性 反压 全流量补燃循环 |
| 文章编号： | 1000-8055(2007)03-0500-05 |
| 收稿时间： | 2006/3/16 0:00:00 |
| 修稿时间： | 2006年3月16日 |
Experimental investigation of flowrate characteristics of gas-gas injector |
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| DU Zheng-gang,JIN Ping,YANG Li-jun,CAI Guo-biao and ZHANG Meng-zheng.Experimental investigation of flowrate characteristics of gas-gas injector[J].Journal of Aerospace Power,2007,22(3):500-504. |
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| Authors: | DU Zheng-gang JIN Ping YANG Li-jun CAI Guo-biao and ZHANG Meng-zheng |
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| Institution: | School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;The 11th Research Institute of CASC, Xi'an 710100, China |
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| Abstract: | Seven types of gas-gas injectors involving two patterns were employed to conduct the flowrate characteristics tests at different back pressure conditions.An investigation on flowrate characteristics of one type of injectors was made at single propellant injection.The effects of inlet pressure of injector and back pressure as well as interaction between oxidizer injector and fuel injector on flowrate characteristics were investigated.Through the experimental measurements and fitting a mathematical expression,the formula of discharge coefficient was given.The results presented in this paper may provide valuable reference for the optimization design of the gas-gas injector for full flow staged combustion cycle engine. |
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| Keywords: | aerospace propulsion system gas-gas injector flowrate characteristics back pressure full flow staged combustion cycle |
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