空气涡轮火箭组合发动机共同工作研究

张留欢; 逯婉若; 王君; 李光熙

doi:10.13224/j.cnki.jasp.2018.03.030

空气涡轮火箭组合发动机共同工作研究

doi: 10.13224/j.cnki.jasp.2018.03.030

中国航天科技集团有限公司西安航天动力研究所，西安 710100

基金项目: 航天支撑技术项目（617010406）

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出版历程
- 收稿日期: 2016-09-09
- 刊出日期: 2018-03-28

Analysis of co-work for air turbo rocket

摘要

摘要: 根据空气涡轮火箭组合发动机工作原理，明确了发动机共同工作条件，建立了发动机共同工作方程，得到了发动机共同工作线，并给出了影响空气涡轮火箭组合发动机共同工作线位置的两个因素：尾喷管喉部面积和涡轮前燃气总温。基于共同工作方程，分析了两因素对发动机共同工作线的影响规律。结果表明：在同一转速线上，随着尾喷管喉部面积或涡轮前燃气总温增大，发动机空气质量流量增大，压气机增压比降低，共同工作线整体向右下方移动；尾喷管喉部面积和涡轮前燃气总温增大或减小使空气涡轮火箭组合发动机共同工作线移动的方向是相同的，但尾喷管喉部面积变化对共同工作线位置移动的影响程度大于涡轮前燃气总温。
- 空气涡轮火箭组合发动机 /
- 共同工作 /
- 尾喷管喉部面积 /
- 涡轮前燃气总温 /
- 影响规律
Abstract: Based on the principle of air turbo rocket, the condition, equation and line of co-work and its influence factors were presented. According to the co-working equation, the influence law of area of the throat for nozzle and total temperature of gas at the inlet of turbine on the co-working line was given. The result showed that the mass flow rate of air for the engine increased and the pressure ratio of compressor decreased as the numerical value of area of the throat for nozzle or total temperature of gas at the inlet of turbine increased on the same rotational velocity line, which made the co-working line move toward lower right direction. The influence law of area of the throat for nozzle and total temperature of gas at the inlet of turbine on the co-working line was similar, but the influence effect of area of the throat for nozzle was more obvious.
- air turbo rocket /
- co-work /
- area of the throat for nozzle /
- total temperature of gas at the inlet of turbine /
- influence law

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参考文献(18)

[1]	南向谊,王栓虎,李平.空气涡轮火箭发动机研究的进展与展望［J］.火箭推进,2008,34(6):31-35.NAN Xiangyi,WANG Shuanhu,LI Ping.Investigation on status and prospect of air turbine rocket［J］.Journal of Rocket Propulsion,2008,34(6):31-35.(in Chinese)
[2]	李文龙,李平,郭海波.空气涡轮火箭发动机掺混燃烧研究进展［J］.火箭推进,2011,37(6):14-19.LI Wenlong,LI Ping,GUO Haibo.Research progresses on turbulent mixing and combustion for air turbo rocket engine［J］.Journal of Rocket Propulsion,2011,37(6):14-19.(in Chinese)
[3]	THOMAS M E,BOSSARD J A,OSTRANDER M J.Addressing emerging tactical missile propulsion challenges with the solid propellant air-turbo-rocket［R］.AIAA-2000-3309,2000.
[4]	BOSSARD J A,THOMAS M E.The influence of turbomachinery characteristics on air turbo rocket engine operation［R］.AIAA-2000-3308,2000．
[5]	MARK J O,MATTHEW E T.Air turbo-rocket solid propellant development and testing［R］.AIAA 97-3258,1997.
[6]	TANATSUGU N,CARRICK P.Hypersonic and combined cycle propulsion for earth-to-orbit applications［R］.AIAA-2003-2586,2003.
[7]	MINATO R,HIGASHINO K,TANATSUGU N.Design and performance analysis of bio-ethanol fueled GG-cycle air turbo ramjet engine［R］.AIAA-2012-0842,2012.
[8]	MIZOBATA K，KIMURA H,SUGIYAMA H.Conceptual design of flight demonstrator vehicles for the ATREX engine［R］.AIAA-2003-7028,2003.
[9]	李文龙,郭海波,南向谊.空气涡轮火箭发动机热力循环特性分析［J］.火箭推进,2015,41(4):48-54.LI Wenlong,GUO Haibo,NAN Xiangyi.Analysis on thermodynamic cycle characteristics of air-turbo-rocket engine［J］.Journal of Rocket Propulsion,2015,41(4):48-54.(in Chinese)
[10]	TU Qiuye,DING Chaoxia,CHEN Yuchun.et al.Thermodynamic cycle analysis on solid propellant air-turbo-rocket［J］.Journal of Solid Rocket Technology,2009,32(1):53-57.
[11]	潘宏亮,周鹏.空气涡轮液体火箭发动机建模与仿真研究［J］.西北工业大学学报,2009,27(4):492-498.PAN Hongliang,ZHOU Peng.Modeling and simulation of liquid ATR (aero turbo rocket) performance［J］.Journal of Northwestern Polytechnical University,2009,27(4):492-498.(in Chinese)
[12]	李成,蔡元虎,屠秋野.吸气式空气涡轮冲压发动机的过渡态性能［J］.航空动力学报,2013,28(2):385-389.LI Cheng,CAI Yuanhu,TU Qiuye.Transition state performance simulation of air-turbo-ramjet engine［J］.Journal of Aerospace Power,2013,28(2):385-389.(in Chinese)
[13]	刘宁.基于化学平衡的富燃燃气工质涡轮性能分析与优化研究［D］.北京：中国科学院大学，2015.LIU Ning.Investigation on the performance analysis and optimization of a fuel-rich working fluid turbine based on chemical equilibrium［D］.Beijing：University of Chinese Academy of Sciences,2015.(in Chinese)
[14]	李文龙,李平,李光熙,等.局部进气条件下空气涡轮火箭发动机掺混燃烧研究［J］.推进技术，2013,34(9):1222-1230. LI Wenlong,LI Ping,LI Guangxi,et al. Investigation on turbulent mixing and combustion for air-turbo-rocket engine with turbine partial admission［J］.Journal of Propulsion Technology,2013,34(9):1222-1230.(in Chinese)
[15]	孙得川,张梦龙.波瓣型燃气/空气混合装置的设计与模拟［J］.推进技术,2015,36(6):893-898.SUN Dechuan,ZHANG Menglong.Numerical simulation and design of a lobe mixer for gas/air mixing［J］.Journal of Propulsion Technology,2015,36(6):893-898.(in Chinese)
[16]	张留欢,逯婉若.空气涡轮火箭发动机风车状态数值研究［J］.火箭推进,2015,41(6):16-20.ZHANG Liuhuan,LU Wanruo.Numerical simulation of air turbo rocket engine at wind-milling state［J］.Journal of Rocket Propulsion,2015,41(6):16-20.(in Chinese)
[17]	刘洋,蒲晓航,李江,等.固体燃料ATR涡轮/压气机匹配方法研究［J］.推进技术,2015,36(3):378-384.LIU Yang,PU Xiaohang,LI Jiang,et al.Research on matching method of turbine/compressor in solid propellant air turbo rocket［J］.Journal of Propulsion Technology,2015,36(3):378-384.(in Chinese)
[18]	廉筱纯,吴虎.航空发动机原理［M］.西安：西北工业大学出版社,2005.