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论文:2023,Vol:41,Issue(6):1125-1133 |
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引用本文： |
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李清安, 王可, 范玮, 杨海, 韩俊德, 黄颗, 康健, 高雅青, 江余敏. 单次脉冲爆震反压传播规律与抑制研究[J]. 西北工业大学学报 |
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LI Qing'an, WANG Ke, FAN Wei, YANG Hai, HAN Junde, HUANG Ke, KANG Jian, GAO Yaqing, JIANG Yumin. Study on back-pressure propagation and suppression of single pulse detonation[J]. Journal of Northwestern Polytechnical University |
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| 单次脉冲爆震反压传播规律与抑制研究 |
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| 李清安1, 王可2,3, 范玮2,3, 杨海1, 韩俊德1, 黄颗1, 康健1, 高雅青1, 江余敏1 |
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1. 四川航天系统工程研究所, 四川 成都 610100;
2. 西北工业大学 动力与能源学院, 陕西 西安 710129;
3. 陕西省航空动力系统热科学重点实验室, 陕西 西安 710129 |
| 摘要: |
| 脉冲爆震燃烧室(pulse detonation combustor,PDC)反压反流的前传是导致脉冲爆震发动机推力损失的主要因素。为抑制PDC反流的传播,采用气动抑制策略,设计出不同结构组合而成的10种隔离段,使用恰当比的乙烯/富氧空气混合物开展了单次脉冲爆震的实验研究。结果表明:当反压传播距离约为0.86倍PDC长度时,相比于基准隔离段,Venturi管(V)与1.5倍PDC直径的直管组合的隔离段由于能够提供更大的膨胀空间,其反压的传播速度与峰值可分别降低约10%与20%;相对于无Tesla阀(T)的隔离段,在安装了Tesla阀的隔离段中,反压传播速度可再降低27.3%以上;相对于无泄压小孔(S)的隔离段,安装了泄压小孔的隔离段可降低25%的反压峰值;中心锥(C)的引入可大幅提高反压传播过程中的平均衰减率。在10种隔离段中,CVST型组合隔离段结构具有最佳的反压抑制能力。相比于基准隔离段,反压在CVST隔离段中的传播速度降低了约50%,峰值降低了约40.5%,平均峰值衰减率提升了1倍左右。 |
| 关键词:
爆震
反流
压力传播
压力衰减
脉冲爆震发动机
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| Study on back-pressure propagation and suppression of single pulse detonation |
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| LI Qing'an1, WANG Ke2,3, FAN Wei2,3, YANG Hai1, HAN Junde1, HUANG Ke1, KANG Jian1, GAO Yaqing1, JIANG Yumin1 |
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1. Sichuan Aerospace System Engineering Research Institute, Chengdu 610100, China;
2. School of Power and Energy, Northwestern Polytechnical University, Xi'an 710129, China;
3. Shaanxi Key Laboratory of Thermal Sciences in Aero-Engine System, Xi'an 710129, China |
| Abstract: |
| The backflow and back-pressure propagation induced in a pulse detonation combustor (PDC) are the main factor in causing the thrust losses of a pulse detonation engine. In order to suppression the backflow propagation of a PDC, the aero-dynamic suppression strategy was implemented in this work. A total of ten isolators composed of different geometries were designed. A single-pulse detonation experiment was conducted by using the stoichiometric ethylene/enriched-oxygen mixture. It is shown that when the back-pressure has propagated about 0.86 the length of PDC, the propagation speeds and the pecks of the back-pressure in the isolator, which composed of the Venturi tube (V) and a long tube with 1.5 times diameter of the PDC, can be reduced by 10% and 20%, respectively, comparing with the base isolator. Comparing with the isolators that without the Tesla valve (T), the propagation speed of the back-pressure in the cases with the Tesla valve can be additionally reduced above 27.3%. Comparing with the isolators that without the slit (S), the peaks of the back-pressure in the cases with the slit can be decreased about 25%. The average decay rate of the back-pressure peaks can be highly increased if the cone (C) is introduced. It is found that the CVST-type isolator is the optimal. Comparing with the base isolator, the backpressure propagated in the CVST-type isolator can decrease about 50% and 40.5% of propagation speed and pressure peaks, respectively, and can increase the average decay rate of the back-pressure peaks by a factor of two. |
| Key words:
detonation
backflow
pressure propagation
pressure attenuation
pulse detonation engine
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| 收稿日期: 2022-10-13
修回日期:
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| DOI: 10.1051/jnwpu/20234161125 |
| 基金项目: 国家自然科学基金(52176133)与陕西省创新能力支撑计划(2021KJXX-93)资助 |
| 通讯作者: 王可(1986-),西北工业大学教授,主要从事爆震推进理论与工程研究。e-mail:wangk@nwpu.edu.cn
Email：wangk@nwpu.edu.cn |
| 作者简介: 李清安(1992-),四川航天系统工程研究所工程师,主要从事燃烧流动与控制研究。
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| 相关功能 |
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| 作者相关文章 |
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| 李清安 在本刊中的所有文章 |
| 王可 在本刊中的所有文章 |
| 范玮 在本刊中的所有文章 |
| 杨海 在本刊中的所有文章 |
| 韩俊德 在本刊中的所有文章 |
| 黄颗 在本刊中的所有文章 |
| 康健 在本刊中的所有文章 |
| 高雅青 在本刊中的所有文章 |
| 江余敏 在本刊中的所有文章 |
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参考文献: |
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[1] FICKETT W, DAVIS W C. Detonation: theory and experiment[M]. New York: Dover Publications Inc, 2000
[2] LU F K, BRAUN E M. Rotating detonation wave propulsion: experimental challenges, modeling, and engine concepts[J]. Journal of Propulsion and Power, 2014, 30(5): 1125-1142
[3] WOLAÑSKI P. Detonative propulsion[J]. Proceedings of the Combustion Institute, 2013, 34(1): 125-158
[4] MUNIPALLI R, SHANKAR V, WILSON D R, et al. Preliminary design of a pulsed detonation based combined cycle engine[C]//10th International Symposium of Air Breathing Engine, 2001
[5] KAEMMING T. Integrated vehicle comparison of turbo-ramjet engine and pulsed detonation engine[C]//Proceedings of ASME Turbo Expo, 2001
[6] BUSSING T R A, LIDSTONE G, CHRISTOFFERSON E, et al. Pulse detonation propulsion proof of concept test article development[C]//38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2002
[7] WANG K, FAN W. Efforts on high-frequency pulse detonation engines[J]. Journal of Propulsion and Power, 2016: 33(1): 17-28
[8] 于潇栋, 王可, 朱亦圆, 等. 无阀模式下液态燃料高频爆震燃烧组织方法实验研究[J]. 航空学报, 2022: 43: 126245 YU Xiaodong, WANG Ke, ZHU Yiyuan, et al. Experimental study on liquid fueled high-frequency detonations in the valveless scheme[J]. Acta Aeronautica et Astronautica Sinica, 2022: 43: 126245 (in Chinese)
[9] WANG K, WANG Z, ZHANG Q, et al. Study on a simplified double-frequency scheme for pulse detonation rocket engines[J]. Acta Astronautica, 2018, 148: 337-344
[10] LU W, FAN W, WANG K, et al. Operation of a liquid-fueled and valveless pulse detonation rocket engine at high frequency[J]. Proceedings of the Combustion Institute, 2017, 36(2): 2657-2664
[11] ANDERSON E, STEVENS C, HOKE J, et al. Ball valve pulsed detonation engine[C]//49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011
[12] MERCURIO N, PAL S, WOODWARD R, et al. Experimental studies of the unsteady ejector mode of a pulse detonation rocket-based combined cycle engine[C]//46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2010
[13] WU Y, HAN Q, SHEN Y, et al. Ignition study on a rotary-valved air-breathing pulse detonation engine[J]. International Journal of Turbo & Jet-Engines, 2015, 34(2): 1-12
[14] 彭畅新. 脉冲爆震外涵加力燃烧室关键技术研究[D]. 西安: 西北工业大学, 2013 PENG Changxin. Investigation on key technologies of pulse detonation combustor as bypass burner[D]. Xi'an: Northwestern Polytechnical University, 2013 (in Chinese)
[15] 马虎. 簧片阀式脉冲爆震发动机研究[D]. 南京: 南京理工大学, 2015 MA Hu. Investigation on pulse detonation engine with reed valve[D]. Nanjing: Nanjing University of Science and Technology, 2015 (in Chinese)
[16] DANIAU E, FALEMPIN F, ZHANG G, et al. Preliminary work for a pulsed detonation engine demonstrator[C]//14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference, 2006
[17] MATSUOKA K, YAGETA J, NAKAMICHI T, et al. Inflow-driven valve system for pulse detonation engines[J]. Journal of Propulsion and Power, 2011, 27(3): 597-607
[18] MATSUOKA K, ESUMI M, IKEGUCHI K B, et al. Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve[J]. Combustion and Flame, 2012, 159(3): 1321-1338
[19] 郑殿峰, 杨义勇, 王家骅. 吸气式脉冲爆震发动机钝体气动阀的设计与实验研究[J]. 北京大学学报(自然科学版), 2012: 48(3): 347-353 ZHEN Dianfeng, YANG Yiyong, WANG Jiahua. Design and experimental investigation of blunt aero-valve for air-breathing pulse detonation engine[J]. Acta Scientiarum Naturalium Universitatis Pekinensis, 2012: 48(3): 347-353 (in Chinese)
[20] 宫继双. 提高气动阀式脉冲爆震发动机性能的技术研究[D]. 南京:南京航空航天大学, 2012 GONG Jishuang. Investigation on improving performance of aero-valve pulse detonation engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2012 (in Chinese)
[21] 杨光远. 气动阀式PDE推力性能分析与实验研究[D]. 南京: 南京航空航天大学, 2017 YANG Guangyuan. Analysis and experimental investigation on the thrust performance of aero-valve pulse detonation engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2017 (in Chinese)
[22] QIU H, XIONG C, YAN C, et al. Effect of aerodynamic valve on backflow in pulsed detonation tube[J]. Aerospace Science and Technology, 2013, 25(1): 1-15
[23] FOA J V. Elements of flight propulsion[M]. New York and London: John Wiley & Sons, 1960
[24] 卢杰. 脉冲爆震涡轮发动机关键技术研究[D]. 西安: 西北工业大学, 2016 LU Jie. Investigation on key technologies of the pulse detonation turbine engine[D]. Xi'an: Northwestern Polytechnical University, 2012 (in Chinese)
[25] WANG Z, WANG Y, HUANG J, et al. Back-propagation suppression study based on intake configuration optimization for an air-breathing pulse detonation engine[J]. Aerospace Science and Technology, 2021, 118: 107042
[26] 李清安, 王可, 孙田雨, 等. 脉冲爆震发动机反压传播规律数值研究[J]. 实验流体力学, 2019, 33(1): 103-110 LI Qing'an, WANG Ke, SUN Tianyu, et al. Numerical study on propagation characteristics of back-pressure in a pulse detonation engine[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(1): 103-110 (in Chinese)
[27] TESLA N. Valvular Conduit: US, 1329559[P]. 1920-02-03
[28] 张文龙. 无阀式脉冲爆震火箭发动机测控方法与实现技术研究[D]. 西安: 西北工业大学, 2019 ZHANG Wenlong. Research on measurement and control method and implementation technology of valveless pulse detonation rocket engine[D]. Xi'an: Northwestern Polytechnical University, 2019 (in Chinese)
[29] 沙定国. 误差分析与测量不确定度评定[M]. 北京: 中国计量出版社, 2003 SHA Dingguo. Error analysis and evaluation of measurement uncertainty[M]. Beijing: China Metrology Publishing House, 2003 (in Chinese) |
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