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基于连续旋转爆震的推进技术研究进展

谢峤峰,  王兵,  董琨

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文章导航 > 气体物理  > 2020 >  5(1): 1-23
谢峤峰, 王兵, 董琨. 基于连续旋转爆震的推进技术研究进展[J]. 气体物理, 2020, 5(1): 1-23. doi: 10.19527/j.cnki.2096-1642.0744
引用本文: 谢峤峰, 王兵, 董琨. 基于连续旋转爆震的推进技术研究进展[J]. 气体物理, 2020, 5(1): 1-23. doi: 10.19527/j.cnki.2096-1642.0744
shu
XIE Qiao-feng, WANG Bing, DONG Kun. Progress in Research of Rotating Detonation Propulsion[J]. PHYSICS OF GASES, 2020, 5(1): 1-23. doi: 10.19527/j.cnki.2096-1642.0744
Citation: XIE Qiao-feng, WANG Bing, DONG Kun. Progress in Research of Rotating Detonation Propulsion[J]. PHYSICS OF GASES, 2020, 5(1): 1-23. doi: 10.19527/j.cnki.2096-1642.0744
shu

基于连续旋转爆震的推进技术研究进展

doi: 10.19527/j.cnki.2096-1642.0744

  • 清华大学航天航空学院，北京 100084

基金项目: 

中国博士后科学基金第64批面上项目 2018M640140

中国博士后科学基金第12批特别资助 2019T120100

详细信息
    作者简介:

    谢峤峰(1986-)  男, 助理研究员, 主要研究方向为基础爆震及爆震推进技术.E-mail:qiaofengxie@mail.tsinghua.edu.cn

    通讯作者:

    王兵(1977-)  男, 特聘研究员, 主要研究方向为高速两相流、燃烧不稳定性、爆震、爆震发动机.E-mail:wbing@tsinghua.edu.cn

  • 中图分类号: O381

Progress in Research of Rotating Detonation Propulsion

  • School of Aerospace Engineering, Tsinghua University, Beijing, 100084, China

    摘要
  • 摘要:

    基于爆震燃烧的推进技术是未来空间技术的重要发展趋势，特别是可实现结构简单化设计和高热力学效率.针对火箭式连续旋转爆震发动机、吸气式爆震发动机的实验测试和数值仿真，文章综述了其国内外研究进展，分别总结了不同燃料、燃烧室结构、喷注方式以及工作方式等对连续旋转爆震波的传播规律和发动机的特性影响规律.虽然上述探索性研究得到了诸多有益的结论，但是由于连续旋转爆震燃烧技术涉及的流动、物理化学过程十分复杂，对旋转爆震燃烧的机理研究仍然有待进一步深入开展.

     

    Abstract:

    The propulsion technology based on detonation is a major trend for the future development of space technology, especially for its simple structural design and high thermodynamic efficiency. This paper conducted a series of latest researches for rotating detonation rocket engine and air breathing rotating detonation engine, including experimental tests and numerical simulation. It also discussed the propagation property of rotating detonation waves and the effects on engine's properties in terms of different fuels, combustion chamber structures, injection methods and operating modes. The aforementioned exploration has shown many beneficial results. However, since the flow, the physical and chemical progresses involved in rotating detonation technology are complicated, the mechanism of rotating detonation still needs to be studied in a further step.

     

    • HTML全文

  • 图  1  连续旋转爆震发动机结构示意图[1]

    Figure  1.  Schematic diagram of rotating detonation engine[1]

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    图  2  Voitsekhovskii团队的旋转爆震实验[2]

    Figure  2.  Experimental facility of the rotating detonation engine at Voitsekhovskii's lab[2]

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    图  3  不同几何构型的连续旋转爆震燃烧室结构示意图[3]

    Figure  3.  Schematic diagram of rotating detonation engine with different geometric configurations[3]

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    图  4  连续旋转爆震燃烧室不同喷注形式示意图[3]

    Figure  4.  Schematic diagram of different injection forms of rotaing detonation combustor[3]

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    图  5  连续旋转爆震发动机与火箭发动机的比冲和推力性能对比[10]

    Figure  5.  Comparison of specific impulse and thrust between rotating detonation engine and rocket engine[10]

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    图  6  406 mm直径的连续旋转爆震燃烧室实验台[12]

    Figure  6.  Rotating detonation combustor with a diameter of 406 mm[12]

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    图  7  连续旋转爆震燃烧室数值计算结果[12] (t=7.65 ms)

    Figure  7.  Numerical results of the rotating detonation combustor[12] (t=7.65 ms)

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    图  8  连续旋转爆震冲压发动机实验台及压力测试结果[14]

    Figure  8.  Rotating detonation ramjet and pressure test result[14]

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    图  9  爆震液体火箭发动机实验台[15]

    Figure  9.  Liquid rotating detonation rocket engine[15]

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    图  10  密西根大学连续旋转爆震发动机实验装置图[16]

    Figure  10.  Experimental setup of the rotating detonation engine at University of Michigan[16]

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    图  11  美国空军技术研究所的连续旋转爆震发动机实验装置图[22]

    Figure  11.  Experimental facility of the rotating detonation engine at the Air Force Institute of Technical [22]

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    图  12  美国空军技术研究所的连续旋转爆震涡轮发动机实验装置图[23]

    Figure  12.  Experimental facility of the rotating detonation turbine engine at the Air Force Institute of technical[23]

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    图  13  连续旋转爆震发动机实验装置及不同尾喷管示意图[24]

    Figure  13.  Experimental facility of the rotating detonation engine with different nozzles[24]

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    图  14  美国空军研究实验室6 in发动机和热传感器示意图[32]

    Figure  14.  Schematic diagrams of the rotating detonation engine with a 6 in diameter and the thermal sensor at Force Research Laboratory[32]

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    图  15  可视化连续旋转爆震燃烧室及OH基化学发光实验[34]

    Figure  15.  Visualized rotating detonation combustor and OH chemiluminescence experiment[34]

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    图  16  美国空军研究实验室直径10 in连续旋转爆震发动机[25]

    Figure  16.  Experimental facility of the rotating detonation engine with a 10 in diameter at Air Force Research Laboratory[25]

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    图  17  美国能源部技术实验室连续旋转爆震发动机实验台[43]

    Figure  17.  Experimental facility of the rotating detonation engine at the U.S. Department of Energy Technology Laboratory[43]

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    图  18  辛辛那提大学连续旋转爆震发动机实验台[44]

    Figure  18.  Experimental facility of the rotating detonation engine at the University of Cincinnati[44]

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    图  19  德克萨斯大学阿灵顿分校连续旋转爆震发动机实验台[49-50]

    Figure  19.  Experimental facility of the rotating detonation engine at the University of Texas at Arlington[49-50]

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    图  20  普渡大学连续旋转爆震燃烧室二维实验台[51]

    Figure  20.  Experimental facility of a 2D rotating detonation combustor at the Purdue University[51]

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    图  21  普渡大学连续旋转爆震发动机实验台[51]

    Figure  21.  Experimental facility of the rotating detonation engine at the Purdue University[51]

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    图  22  法国MBDA公司的连续旋转爆震发动机实验台[54]

    Figure  22.  Experimental facility of the rotating detonation engine at the MBDA[54]

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    图  23  华沙理工大学连续旋转爆震发动机实验台[61]

    Figure  23.  Experimental facility of the rotating detonation engine at the Warsaw University of Technology[61]

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    图  24  华沙理工大学连续旋转爆震发动机实验台[65]

    Figure  24.  Experimental facility of the rotating detonation engine at the Warsaw University of Technology[65]

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    图  25  波兰航空研究院新型连续旋转爆震发动机实验台[66]

    Figure  25.  Experimental facility of the rotating detonation engine at the Polish Aviation Institute[66]

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    图  26  波兰航空研究院煤油/空气连续旋转爆震发动机实验台[67]

    Figure  26.  Experimental facility of the kerosene/air rotating detonation engine at the Polish Aviation Institute[67]

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    图  27  连续旋转爆震波流场特征数值仿真结果[75]

    Figure  27.  Numerical simulation of the flow field in rotating detonation engine[75]

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    图  28  连续旋转爆震发动机收缩扩张喷管的Mach数分布[79]

    Figure  28.  Distribution of Mach number of expansion nozzle in a rotating detonation engine[79]

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    图  29  连续旋转爆震火箭轨道车实验系统[80]

    Figure  29.  Test system of the rotating detonation rocket railcar[80]

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    图  30  日本S520探空火箭[80]

    Figure  30.  S520 sounding rocket of Japan[80]

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    图  31  釜山国立大学的数值仿真结果及实验设计[84]

    Figure  31.  Numerical simulation and experimental design at Busan National University[84]

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    图  32  国防科技大学设计的连续旋转爆震发动机[89]

    Figure  32.  Experimental facility of the rotating detonation engines at the National University of Defense Technology[89]

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    图  33  国防科技大学的吸气式连续旋转爆震发动机及自由射流实验台[94]

    Figure  33.  Experimental facility of the air breathing rotating detonation engine and free jet test bench at the National University of Defense Technology[94]

    下载: 全尺寸图片 幻灯片

    图  34  南京理工大学的连续旋转爆震发动机实验台[101]

    Figure  34.  Experimental facility of the rotating detonation engine at Nanjing University of Science and Technology[101]

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    图  35  北京大学的连续旋转爆震发动机实验台[116]

    Figure  35.  Experimental facility of the rotating detonation combustor at Beijing University[116]

    下载: 全尺寸图片 幻灯片

    图  36  清华大学的连续旋转爆震发动机实验台[126]

    Figure  36.  Experimental facility of the rotating detonation combustor at Tsinghua University[126]

    下载: 全尺寸图片 幻灯片

    表  1  Aerojet Rocketdyne公司连续旋转爆震发动机研究[42]

    Table  1.   Research on rotating detonation engine at Aerojet Rocketdyne co., ltd[42]

    year project test time photo
    2010 proof of principle 28
    2010 experimental study on detonation engine 163
    2011 plasma ignition 21
    2012 determination of design parameters 198
    2013 experimental study on liquid fuel 79
    2013 exhaust emission measurement 35
    2014 experimental study on detonation turbojet engine 13
    2015 detonation turbojet engine modeling 0
    下载: 导出CSV
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