| 超声速自引射装置的工作过程研究 |
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| 引用本文： | 张民庆,张忠利,周立新,张蒙正.超声速自引射装置的工作过程研究[J].航空动力学报,2012,27(1):218-224. |
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| 作者姓名： | 张民庆 张忠利 周立新 张蒙正 |
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| 作者单位： | 1. 西北工业大学航天学院,西安,710072
2. 中国航天科技集团公司西安航天动力研究所,西安,710100 |
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| 摘 要： | 应用湍流κ-ε双方程模型,分析了液体火箭发动机自引射工作过程所用的超声速自引射装置(简称引射器,包括圆柱型和二次喉道型引射器)在相同二次流入口面积时的流场分布,依据流场分析值确定了激波在引射器内的位置,结果表明喷管内的气流达到满流状态,并根据有关参数计算了引射系数.对比引射器真空舱内压力仿真值和试车测量值,两者基本一致.
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| 关 键 词： | 液体火箭发动机 引射器 流场 数值模拟 引射系数 |
| 收稿时间： | 2011/4/16 0:00:00 |
| 修稿时间： | 2011/11/19 0:00:00 |
Investigation on working course of supersonic self-ejector |
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| ZHANG Min-qin,ZHANG Zhong-li,ZHOU Li-xin and ZHANG Meng-zheng.Investigation on working course of supersonic self-ejector[J].Journal of Aerospace Power,2012,27(1):218-224. |
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| Authors: | ZHANG Min-qin ZHANG Zhong-li ZHOU Li-xin and ZHANG Meng-zheng |
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| Institution: | School of Astronautics, Northwestern Polytechnical university, Xi'an 71007;Xi'an Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Xi'an 710100, China;Xi'an Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Xi'an 710100, China;Xi'an Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Xi'an 710100, China |
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| Abstract: | The analysis model of self-ejector(ejector for short,including cylindrical ejector and second-throat ejector) was set up in liquid rocket engine.The two equation κ-ε model was employed to simulate the turbulence.The performances and the flow field features of cylindrical and second-throat ejector were gained in same gap.According as these flow fields,the site of the shock wave,the full flow in nozzle,the coefficients of ejecting were calculated.The numerical value was compared with hot fire test value in vacuum cabin,both are same. |
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| Keywords: | liquid rocket engine ejector flow fields numerical simulation coefficients of ejecting |
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