| 超临界航空煤油喷射的射流结构及相变过程 |
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| 引用本文： | 高伟,林宇震,梁获胜,许全宏.超临界航空煤油喷射的射流结构及相变过程[J].航空动力学报,2009,24(12):2661-2665. |
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| 作者姓名： | 高伟 林宇震 梁获胜 许全宏 |
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| 作者单位： | 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科技重点实验室,北京100191 |
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| 摘 要： | 研究了超临界RP-3航空煤油喷射到静止常温常压大气环境中的近场射流结构及喷口附近的射流相变过程.研究结果表明,超临界煤油喷射剑静止大气环境中后会经历类似于理想气体不完全膨胀的过程,会在喷嘴下游产生马赫盘等激波结构,马赫盘的位置随喷射压力的提高而增大,而喷射温度对马赫盘位置几乎没有影响,当喷射温度较高时,超临界煤油在喷嘴出口处直接进入气相区,没有凝结现象发生,而煤油的喷射温度接近临界温度时,超临界煤油会在喷嘴内部及出口处发生局部凝结,进入气液两相区.
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| 关 键 词： | 超临界航空煤油 射流结构 马赫盘 相变过程 |
| 收稿时间： | 2009/3/16 0:00:00 |
| 修稿时间： | 2009/6/25 0:00:00 |
Jet structures and phase transition process of supercritical aviation kerosene fuel injection |
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| GAO Wei,LIN Yu-zhen,LIANG Huo-sheng and XU Quan-hong.Jet structures and phase transition process of supercritical aviation kerosene fuel injection[J].Journal of Aerospace Power,2009,24(12):2661-2665. |
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| Authors: | GAO Wei LIN Yu-zhen LIANG Huo-sheng and XU Quan-hong |
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| Institution: | National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | The injection of supercritical RP-3 aviation kerosene fuel into a quiescent atmospheric environment was experimentally investigated to study the jet structures and phase transition process near the nozzle exit.It was found that supercritical kerosene jets injected above the critical point underwent ideal-gas-like expansion and exhibited visible Mach disk shock structures.The axial location of the Mach disk increased with the injection pressure,and the injection temperature had little effects on the axial location of Mach disk.The phase transition process analysis revealed that the supercritical kerosene fuel was penetrated into the gas region from the supercritical region directly at the nozzle exit,without going through two-phase region at higher injection temperature.Fuel condensation phenomenon occurred in the nozzle and fuel entered two-phase region when fuel was injected near the critical point. |
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| Keywords: | supercritical aviation kerosene fuel jet structures Mach disks phase transition process |
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