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涡轮排气液化循环发动机的能量分析 被引量:1

Energy Analysis of the Turbine Exhaust Liquefaction Cycle Engine
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摘要 对涡轮排气液化循环发动机液化水的处置进行了研究。通过热力学分析获得了发动机性能的理论解,并利用热力计算进行验证。分析表明液态水直接排出发动机将导致约2%的比冲损失。分析了发动机各环节的能量传递,获得了燃烧室中心燃烧区焓增的理论表达式,可作为燃烧室性能的详细分析的基础。 The treatment of the liquid water of the turbine exhaust liquefaction cycle engine (TELCE) was studied in this paper. The theory solution was acquired by thermal analysis and was identified by thermal calculation. The analysis showed that there was about 2% specific impulse loss if liquid water was drilled out of engine directly. Further more, the energy transfer in TELCE was analyzed, and the enthalpy theory expression of the gas in engine center combustion region was given out, which could be as the detail analysis base for the chamber performance.
出处 《上海航天》 2010年第2期46-48,55,共4页 Aerospace Shanghai
基金 自然科学基金资助(50406006)
关键词 液体火箭发动机 发动机循环 热力学分析 液化水 Liquid rocket engine Engine cycle Thermal analysis Liquid water
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参考文献3

  • 1DAVIS J,CAMPBELL R.Advantages of a full-flow combustion cycles engine system[R].AIAA,97-3318.
  • 2MANSKI D.Cycles for earth-to-orbit propulsion[J].Journal of Propulsion and Power,1998,14(5):588-604.
  • 3LOURDES Q.Airbreathing space boosters using in-flight oxidizer collection[J].Journal of Propulsion and Power,1996,12(2):315-321.

同被引文献3

  • 1休泽尔.液体火箭发动机现代工程设计[M].朱宁昌等译.北京:中国宇航出版社,2004.
  • 2LOURDES Q.Airbreathing space boosters using in-flight oxidizer collection[J].Journal of Propulsion and Power,1996,12(2):315-321.
  • 3MANSKI D.Cycles for earth-to-orbit propulsion[J].Journal of Propulsion and Power,1998,14(5):588-604.

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