全流量补燃循环液氧甲烷发动机系统方案研究
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摘要
为了在现有火箭发动机的技术条件下,研制高性能、高可靠性、重复使用的液氧甲烷发动机,采用与液氧煤油和液氧甲烷发动机对比的方法,从推力室冷却难易程度、影响涡轮寿命的燃气温度、发动机运载能力等角度考虑,对全流量补燃循环液氧甲烷发动机的混合比和室压进行了优化选择,发动机在高室压和高混合比下工作性能更优;参考目前液氧煤油和液氧液氢发动机方案,对发动机的部分子系统配置进行了对比,采用泵后高压液体驱动预压涡轮、分段冷却推力室的方案技术风险小,且涡轮燃气温度较低。
In order to develop a high performance, high reliability and reusable LOX(liquid oxygen)/LCH4(liquid methane) engine based on the existing rocket engine technology conditions, the mixing ratio and chamber pressure of full flow staged combustion cycle LOX/LCH4 engine were optimally selected by comparing with the LOX/LH2(liquid hydrogen) and LOX/kerosene engine and taking into account the cooling capacity of thrust chamber, the gas temperature that influencing the life of turbine and the engine's carriage capacity. Full flow staged combustion cycle LOX/LCH4 engine had better performance in higher chamber pressure and mixing ratio. According to the current projects of LOX/LH2 and LOX/kerosene engines, comparison of some subsystem configurations were carried out. The engine with boost turbo driven by pumped propellant and thrust chamber cooled separately had smaller risk, and the turbine gas temperature did not exceed the present technical level.
In order to develop a high performance, high reliability and reusable LOX(liquid oxygen)/LCH4(liquid methane) engine based on the existing rocket engine technology conditions, the mixing ratio and chamber pressure of full flow staged combustion cycle LOX/LCH4 engine were optimally selected by comparing with the LOX/LH2(liquid hydrogen) and LOX/kerosene engine and taking into account the cooling capacity of thrust chamber, the gas temperature that influencing the life of turbine and the engine's carriage capacity. Full flow staged combustion cycle LOX/LCH4 engine had better performance in higher chamber pressure and mixing ratio. According to the current projects of LOX/LH2 and LOX/kerosene engines, comparison of some subsystem configurations were carried out. The engine with boost turbo driven by pumped propellant and thrust chamber cooled separately had smaller risk, and the turbine gas temperature did not exceed the present technical level.
引文
[1] Klepikov I A, Katorgin B I, Chvanov V K. The new generation of rocket engines, operating by ecologically safe propellant “liquid oxygen and liquefied natural gas(methane)”[C]//48th International Astronautical Congress, Turin, Italy, 1997:1-9.
[2] Kalmykov G P, Mossolov S V. Liquid rocket engines working on oxygen + methane for space transportation systems of the XXI century (on the results of scientific and experimental studies) [C]//51th International Astronautical Congress, Rio de Janerio, Brazil, 2000:1-7.
[3] Pempie P, Frohlich T, Vermin H. LOX/Methane and LOX/Kerosene high thrust engine trade-off [C]//37th AIAA/ASME/SAE/ASEE Joint Propulsion, Salt Lake City, Utah, 2001:1-11.
[4] 尹亮,刘伟强. 液氧/甲烷发动机研制进展与技术展望[J].航空兵器,2018(4):21-27.Yin L, Liu W Q. Review and prospect of LOX/methane rocket engine systems[J]. Aero Weaponry, 2018 (4): 21-27.(in Chinese)
[5] 王珺,张卫红,石文靓,等. 60 t 级液氧/甲烷发动机起动过程建模与仿真[J]. 火箭推进, 2013, 39(5):16-22.Wang J, Zhang W H, Shi W L, et al. Modeling and simulation of start-up process of 60 t class LOX/methane liquid rocket engine [J]. Journal of Rocket Propulsion, 2013, 39(5):16-22. (in Chinese)
[6] 马冬英,卢钢,张小平,等. 液氧/甲烷燃气发生器试验研究[J]. 火箭推进, 2013, 39(3):21-26.Ma D Y, Lu G, Zhang X P, et al. Research on hot tests of LOX/methane gas generator [J]. Journal of Rocket Propulsion, 2013, 39(3):21-26. (in Chinese)
[7] 金平,蔡国飚. 全流量补燃循环发动机及其特点[J]. 火箭推进, 2003, 29(4):43-47.Jin P, Cai G B. Full flow staged combustion cycle engine and its characteristics[J]. Journal of Rocket Propulsion, 2003, 29(4):43-47. (in Chinese)
[8] 马翰英.航天煤油[M]. 北京:中国宇航出版社, 2003: 377-422.Ma H Y. Aerospace Kerosene[M]. Beijing: China Astronautic Publishing House, 2003: 377-422. (in Chinese)
[9] 黄永华,陈国邦.低温流体热物理性质[M]. 第二版.北京:国防工业出版社,2014: 100-145,428-460.Huang Y H, Chen G B. Thermophysical Properties of Cryogenic Fluids[M].Second Edition. Beijing: National Defense Industry Press, 2014: 100-145,428-460. (in Chinese)
[10] Q/Tm 19-94, 液体双组元推进剂燃气热力气动力和热物理参数计算方法[S].Q/Tm 19-94, Calculation of Thermal Dynamic and Thermal Physical Parameters of Liquid Dual Propellant Gas [S]. (in Chinese)
[11] Vachnadze V D, Ovechko-Filippov E V, Smolentsev A A, et al. Development, upgrade phases and results of fifty years of operation of our country’s first closed-loop liquid rocket engine[J]. Space Engineering and Technology,2015,2(9):82-90.
[12] 《世界导弹与航天发动机大全》编委会.世界导弹与航天发动机大全[M].北京:军事科学出版社,1999:47-126.Editorial Committee of An Encyclopedia of world missile and space engines. An Encyclopedia of World Missile and Space Engines[M].Beijing:Military Science Press, 1999:47-126. (in Chinese)
[13] Chelkis F Y, Chwiedor T D, Connolly P J, et al. Incorporation of RD-180 failure response features in the atlas V booster emergency detection system[C]//AIAA Space 2011 Conference &Exposition, Long Beach, California, 2011:1-14.
[14] 张贵田.高压补燃液氧煤油发动机[M].北京:国防工业出版社,2005:29-58,248-254.Zhang G T. High Pressure Staged Combustion LOX/kerosene Rocket Engine[M]. Beijing: National Defense Industry Press, 2005:29-58,248-254. (in Chinese)
[15] 李斌,谭永华.液氧煤油富氧补燃发动机[J].火箭推进,2003,29(2):1-6.Li B, Tan Y H. Oxidizer-rich gas staged combustion liquid oxygen/kerosene engine[J]. Journal of Rocket Propulsion, 2003,29(2):1-6. (in Chinese)
[16] Van Hooser K P, Bradley D P. Space shuttle main engine -the relentless pursuit of improvement[C]// AIAA Space 2011 Conference & Exposition, Long Beach, California,2011:1-16.
[2] Kalmykov G P, Mossolov S V. Liquid rocket engines working on oxygen + methane for space transportation systems of the XXI century (on the results of scientific and experimental studies) [C]//51th International Astronautical Congress, Rio de Janerio, Brazil, 2000:1-7.
[3] Pempie P, Frohlich T, Vermin H. LOX/Methane and LOX/Kerosene high thrust engine trade-off [C]//37th AIAA/ASME/SAE/ASEE Joint Propulsion, Salt Lake City, Utah, 2001:1-11.
[4] 尹亮,刘伟强. 液氧/甲烷发动机研制进展与技术展望[J].航空兵器,2018(4):21-27.Yin L, Liu W Q. Review and prospect of LOX/methane rocket engine systems[J]. Aero Weaponry, 2018 (4): 21-27.(in Chinese)
[5] 王珺,张卫红,石文靓,等. 60 t 级液氧/甲烷发动机起动过程建模与仿真[J]. 火箭推进, 2013, 39(5):16-22.Wang J, Zhang W H, Shi W L, et al. Modeling and simulation of start-up process of 60 t class LOX/methane liquid rocket engine [J]. Journal of Rocket Propulsion, 2013, 39(5):16-22. (in Chinese)
[6] 马冬英,卢钢,张小平,等. 液氧/甲烷燃气发生器试验研究[J]. 火箭推进, 2013, 39(3):21-26.Ma D Y, Lu G, Zhang X P, et al. Research on hot tests of LOX/methane gas generator [J]. Journal of Rocket Propulsion, 2013, 39(3):21-26. (in Chinese)
[7] 金平,蔡国飚. 全流量补燃循环发动机及其特点[J]. 火箭推进, 2003, 29(4):43-47.Jin P, Cai G B. Full flow staged combustion cycle engine and its characteristics[J]. Journal of Rocket Propulsion, 2003, 29(4):43-47. (in Chinese)
[8] 马翰英.航天煤油[M]. 北京:中国宇航出版社, 2003: 377-422.Ma H Y. Aerospace Kerosene[M]. Beijing: China Astronautic Publishing House, 2003: 377-422. (in Chinese)
[9] 黄永华,陈国邦.低温流体热物理性质[M]. 第二版.北京:国防工业出版社,2014: 100-145,428-460.Huang Y H, Chen G B. Thermophysical Properties of Cryogenic Fluids[M].Second Edition. Beijing: National Defense Industry Press, 2014: 100-145,428-460. (in Chinese)
[10] Q/Tm 19-94, 液体双组元推进剂燃气热力气动力和热物理参数计算方法[S].Q/Tm 19-94, Calculation of Thermal Dynamic and Thermal Physical Parameters of Liquid Dual Propellant Gas [S]. (in Chinese)
[11] Vachnadze V D, Ovechko-Filippov E V, Smolentsev A A, et al. Development, upgrade phases and results of fifty years of operation of our country’s first closed-loop liquid rocket engine[J]. Space Engineering and Technology,2015,2(9):82-90.
[12] 《世界导弹与航天发动机大全》编委会.世界导弹与航天发动机大全[M].北京:军事科学出版社,1999:47-126.Editorial Committee of An Encyclopedia of world missile and space engines. An Encyclopedia of World Missile and Space Engines[M].Beijing:Military Science Press, 1999:47-126. (in Chinese)
[13] Chelkis F Y, Chwiedor T D, Connolly P J, et al. Incorporation of RD-180 failure response features in the atlas V booster emergency detection system[C]//AIAA Space 2011 Conference &Exposition, Long Beach, California, 2011:1-14.
[14] 张贵田.高压补燃液氧煤油发动机[M].北京:国防工业出版社,2005:29-58,248-254.Zhang G T. High Pressure Staged Combustion LOX/kerosene Rocket Engine[M]. Beijing: National Defense Industry Press, 2005:29-58,248-254. (in Chinese)
[15] 李斌,谭永华.液氧煤油富氧补燃发动机[J].火箭推进,2003,29(2):1-6.Li B, Tan Y H. Oxidizer-rich gas staged combustion liquid oxygen/kerosene engine[J]. Journal of Rocket Propulsion, 2003,29(2):1-6. (in Chinese)
[16] Van Hooser K P, Bradley D P. Space shuttle main engine -the relentless pursuit of improvement[C]// AIAA Space 2011 Conference & Exposition, Long Beach, California,2011:1-16.