液体火箭发动机推力室可重复使用技术

康玉东; 孙冰

液体火箭发动机推力室可重复使用技术

康玉东,
孙冰

北京航空航天大学宇航学院,北京 100191

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出版历程
- 收稿日期: 2011-07-29
- 刊出日期: 2012-07-28

Reusable technology for liquid rocket engine thrust chamber

School of Astronautics,Beihang University,Beijing 100191,China

摘要

摘要: 为了验证液体火箭发动机推力室可重复使用技术,采用流-固耦合方法对推力室内壁材料、外壁厚度、冷却通道高宽比等影响推力室内壁寿命的因素进行了数值模拟.通过计算,得到了推力室内壁在不同内壁材料、不同外套厚度、不同冷却通道高宽比下单循环各阶段的应力、应变分布,对计算结果进行后处理,得到了内壁损伤.结果表明,采用高强度及延展性内壁材料、低刚性外套、大冷却通道高宽比可以减小推力室内壁损伤,延长推力室内壁使用寿命.
- 液体火箭发动机 /
- 推力室 /
- 可重复使用技术 /
- 流-固耦合 /
- 数值模拟
Abstract: To validate the reusable technology for liquid rocket engine thrust chamber,the fluid-structural coupling method was adopted to simulate the effect of thrust chamber inner wall material,closeout thickness and regenerative cooling channel aspect ratio on the usable life of thrust chamber inner wall.Through computation,the stress and strain distribution of thrust chamber wall at different stage of each cycle under different inner wall materials,closeout thicknesses and cooling channel aspect ratios were obtained,and a post processing method was applied to predict the damage of the thrust chamber inner wall.The results show that the use of high yield strength inner wall material with reasonable ductility,low-stiffness closeout and high aspect ratio cooling channel can decrease the damage of thrust chamber inner wall and extend the usable life the thrust chamber.
- liquid rocket engine /
- thrust chamber /
- reusable technology /
- fluid-structural coupling /
- numerical simulation

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参考文献(15)

[1]	Dumbacher D.NASA’s second generation reusable launch vehicle program introduction,status and future plans .AIAA 2002-3613,2002.
[2]	Accettura A G,Mascanzoni F,Ierardo N.Inve-stigations and considerations about reusable LOX/HC engines as key technologies for future launch vehicles .AIAA 2002-3846,2002.
[3]	张登成,唐硕.美国重复使用运载器的发展历史、现状及启示[J].导弹与航天运载技术,2003,265(5):20-27. ZHANG Dengcheng,TANG Shuo.Development history, current status and revelation of RLV in USA[J].Missiles and Space Vehicles,2003,265(5):20-27.(in Chinese)
[4]	才满瑞.可重复使用空间往返运输系统的最新发展[J].航天控制,2004,22(4):21-25. CAI Manrui.New development of reusable space transportation system[J].Aerospace Control,2004,22(4):21-25.(in Chinese)
[5]	丁丰年,张恩昭,张小平,等.论我国重复使用运载器推进系统方案[J].火箭推进,2004,30(3):13-18.
[6]	Wagner W R,Shoji J M.Advanced regenerative cooling techniques for future space transportation systems .AIAA 75-1247,1975.
[7]	Hannum N P,Quentmeyer R J,Kasper H J.Some effects of cyclic induced deformation in rocket thrust chambers .AIAA 79-0911,1979.
[8]	Quentmeyer R J.Rocket combustion chamber life-enhancing design concepts .AIAA 90-2116,1990.
[9]	Popp M,Schmidt G.Rocket engine combustion chamber design concepts for enhanced life .AIAA 96-3303,1996.
[10]	Carlile J,Quentmeyer R J.An experimental investigation of high aspect ratio cooling passages .AIAA 92-3154,1992.
[11]	Wadel M F,Meyer M L.Validation of high aspect ratio cooling in a 89 kN thrust combustion chamber .AIAA 96-2584,1996.
[12]	康玉东,孙冰.燃气非平衡流再生冷却流动传热数值模拟[J].推进技术,2011,32(1):119-124. KANG Yudong,SUN Bing.Numerical simulation of regenerative cooling flow and heat transfer with nonequilibrium flow[J].Journal of Propulsion Technology,2011,32(1):119-124.(in Chinese)
[13]	KANG Yudong,SUN Bing.Numerical simulation of liquid rocket engine thrust chambet regenerative cooling[J].Journal of Thermophysics and Heat Transfer,2011,25(1):155-164.
[14]	Riccius J R,Zametaev E B.Stationary and dynamic thermal analyses of cryogenic liquid rocket combustion chamber walls .AIAA 2002-3694,2002.
[15]	Esposito J J,Zabora R F.Thrust chamber life prediction Volume I:mechanical and physical properties of high performance rocket nozzle materials .NASA CR-134806,1975.