| 基于超声速汽液两相流液化装置的排气液化循环方案 |
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| 引用本文： | 黄奕勇,许军校.基于超声速汽液两相流液化装置的排气液化循环方案[J].上海航天,2009,26(6):35-39. |
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| 作者姓名： | 黄奕勇 许军校 |
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| 作者单位： | 国防科学技术大学航天与材料工程学院,湖南,长沙,410073 |
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| 基金项目： | 自然科学基金资助项目 |
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| 摘 要： | 构造了基于超声速汽液两相流液化装置的涡轮排气液化循环发动机系统方案,对性能进行了分析、计算。结果表明：该方案可将燃烧室压力提高至35 MPa,氢主涡轮泵出口压力降低40.4%,燃气发生器室压降低38%,发动机比冲提高50.9 m/s,同时水液膜可发挥较好的热防护作用,系统冷却安全、可靠。
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| 关 键 词： | 液体火箭发动机 液化 两相流 |
Scheme of Turbine Exhaust Liquefaction Cycle Engine Based on Supersonic Two-Phase Flow |
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| HUANG Yi-yong,XU Jun-xiao.Scheme of Turbine Exhaust Liquefaction Cycle Engine Based on Supersonic Two-Phase Flow[J].Aerospace Shanghai,2009,26(6):35-39. |
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| Authors: | HUANG Yi-yong XU Jun-xiao |
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| Institution: | (School of Astronautics and Material Engineering,NUDT,Changsha Hunan,410073,China) |
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| Abstract: | The scheme of turbine exhaust liquefaction cycle engine（TELCE） based on supersonic two-phase flow was put forward in this paper.The performances of the device were analyzed and calculated.The results showed that the MCC pressure of the device would reach 35 MPa,the gas generator pressure would be 38% lower,and the exit pressures of liquid H_2 pump would be 40.4% lower than that of the staged engine.The specific impulse would increase 45.5 m/s.And the water film formed by water injected in MCC participates in TELCE chamber would provide heat protection.The cooling of the system was safe and reliable. |
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| Keywords: | Liquid propellant rocket engine Liquefaction Two-phase flow |
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