| Citation: | XIE Junjie, ZHENG Longxi, LU Jie, et al. Thrust characteristics of pulse detonation duct burner[J]. Journal of Aerospace Power, 2025, 40（1）：20220448 doi: 10.13224/j.cnki.jasp.20220448
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In order to obtain the interaction mechanism between different nozzles and pulse detonation duct burner and improve the thrust enhancement performance of pulse detonation duct burner, the pulse detonation duct burners without nozzle, with seven convergent nozzles, seven convergent and divergent nozzles and five fluidic nozzles were numerically calculated. The results showed that the convergent nozzle could reflect the compression wave, slow down the discharge of high-pressure working substance, and then improve the axial force gain. The convergent divergent nozzle could further accelerate the flow on the basis of the convergent section, but it could make the shock wave enter the divergent section some time in a cycle, resulting in partial thrust loss; The fluidic nozzle could adjust the working substance parameters in the expansion section of the nozzle, but it could also bring some mixing loss. When the fluidic nozzle was used under these three working conditions, the axial force gain increase rate was the highest, which was 22.11%, 15.06% and 15.23%, respectively.
| [1] |
郑龙席. 脉冲爆震涡轮发动机技术[M]. 西安: 西北工业大学出版社,2019. ZHENG Longxi. Pulse detonation turbine engine technology[M]. Xi’an: Northwestern Polytechnical University Press,2019. (in Chinese
ZHENG Longxi. Pulse detonation turbine engine technology[M]. Xi’an: Northwestern Polytechnical University Press, 2019. (in Chinese)
|
| [2] |
郑龙席,卢杰,严传俊,等. 脉冲爆震涡轮发动机研究进展[J]. 航空动力学报,2014,29(5): 993-1000. ZHENG Longxi,LU Jie,YAN Chuanjun,et al. Research progress on pulse detonation turbine engine[J]. Journal of Aerospace Power,2014,29(5): 993-1000. (in Chinese
ZHENG Longxi, LU Jie, YAN Chuanjun, et al. Research progress on pulse detonation turbine engine[J]. Journal of Aerospace Power, 2014, 29(5): 993-1000. (in Chinese)
|
| [3] |
YUNGSTER S. Analysis of nozzle and ejector effects on pulse detonation engine performance: AIAA 2003-1316 [R]. Reston,Virigina: AIAA,2003.
|
| [4] |
BARBOUR E,HANSON R,MORRIS C,et al. A pulsed detonation tube with a converging-diverging nozzle operating at different pressure ratios: AIAA 2005-1307 [R]. Reston,Virigina: AIAA,2005.
|
| [5] |
BARBOUR E,HANSON R. Analytic model for single-cycle detonation tube with diverging nozzles[J]. Journal of Propulsion and Power,2009,25(1): 162-172. doi: 10.2514/1.35420
|
| [6] |
TANGIRALA V,DEAN A,TSUBOI N,et al. Performance on a pulse detonation engine under subsonic and supersonic flight conditions: AIAA 2007-1245 [R]. Reston,Virigina: AIAA,2007.
|
| [7] |
MORRIS C. Axisymmetric modeling of pulse detonation rocket engines: AIAA 2005-3508 [R]. Virigina: AIAA,2005.
|
| [8] |
李建玲,范玮,李强,等. 脉冲爆震火箭发动机喷管构型数值研究[J]. 航空发动机,2010,36(3): 5-9,49. LI Jianling,FAN Wei,LI Qiang,et al. Numerical investigation on nozzle configuration of pulsed detonation rocket engine[J]. Aeroengine,2010,36(3): 5-9,49. (in Chinese doi: 10.3969/j.issn.1672-3147.2010.03.002
LI Jianling, FAN Wei, LI Qiang, et al. Numerical investigation on nozzle configuration of pulsed detonation rocket engine[J]. Aeroengine, 2010, 36(3): 5-9, 49. (in Chinese) doi: 10.3969/j.issn.1672-3147.2010.03.002
|
| [9] |
王治武,张昆,郑龙席,等. 喷管角度对脉冲爆震发动机性能影响数值研究[J]. 西北工业大学学报,2015,33(3): 456-461. WANG Zhiwu,ZHANG Kun,ZHENG Longxi,et al. Numerical simulation of the nozzle angle effect on PDE performance[J]. Journal of Northwestern Polytechnical University,2015,33(3): 456-461. (in Chinese doi: 10.3969/j.issn.1000-2758.2015.03.016
WANG Zhiwu, ZHANG Kun, ZHENG Longxi, et al. Numerical simulation of the nozzle angle effect on PDE performance[J]. Journal of Northwestern Polytechnical University, 2015, 33(3): 456-461. (in Chinese) doi: 10.3969/j.issn.1000-2758.2015.03.016
|
| [10] |
邱华,龚婷婷,熊姹,等. 带二次流增推尾喷管的脉冲爆震发动机数值模拟研究[J]. 西北工业大学学报,2015,33(2): 271-277. QIU Hua,GONG Tingting,XIONG Cha,et al. Numerical simulation of pulse detonation engine (PDE) with fluidic nozzle[J]. Journal of Northwestern Polytechnical University,2015,33(2): 271-277. (in Chinese doi: 10.3969/j.issn.1000-2758.2015.02.017
QIU Hua, GONG Tingting, XIONG Cha, et al. Numerical simulation of pulse detonation engine (PDE) with fluidic nozzle[J]. Journal of Northwestern Polytechnical University, 2015, 33(2): 271-277. (in Chinese) doi: 10.3969/j.issn.1000-2758.2015.02.017
|
| [11] |
邱华,何有权,门凯. 流体喷管的脉冲爆震发动机出口过膨胀优化数值研究[J]. 火箭推进,2021,47(1): 29-35. QIU Hua,HE Youquan,MEN Kai. Numerical study on overexpansion optimization of pulse detonation engine with fluidic nozzle[J]. Journal of Rocket Propulsion,2021,47(1): 29-35. (in Chinese
QIU Hua, HE Youquan, MEN Kai. Numerical study on overexpansion optimization of pulse detonation engine with fluidic nozzle[J]. Journal of Rocket Propulsion, 2021, 47(1): 29-35. (in Chinese)
|
| [12] |
曾昊,何立明,章雄伟,等. 喷管收敛-扩张角对爆震发动机性能影响分析[J]. 推进技术,2011,32(1): 97-102. ZENG Hao,HE Liming,ZHANG Xiongwei,et al. Investigation on the effects of nozzles with different convergent-divergent angle on PDE performance[J]. Journal of Propulsion Technology,2011,32(1): 97-102. (in Chinese
ZENG Hao, HE Liming, ZHANG Xiongwei, et al. Investigation on the effects of nozzles with different convergent-divergent angle on PDE performance[J]. Journal of Propulsion Technology, 2011, 32(1): 97-102. (in Chinese)
|
| [13] |
李晓丰,肖俊峰,王玮,等. 脉冲爆震燃烧室出口燃气能量分布特性[J]. 航空动力学报,2020,35(11): 2356-2363. LI Xiaofeng,XIAO Junfeng,WANG Wei,et al. Energy distribution characteristics of gas at outlet of pulse detonation combustor[J]. Journal of Aerospace Power,2020,35(11): 2356-2363. (in Chinese
LI Xiaofeng, XIAO Junfeng, WANG Wei, et al. Energy distribution characteristics of gas at outlet of pulse detonation combustor[J]. Journal of Aerospace Power, 2020, 35(11): 2356-2363. (in Chinese)
|
| [14] |
韩信,张子健,马凯夫,等. 超燃冲压发动机喷管推力性能理论预测[J]. 气体物理,2022,7(1): 1-8. HAN Xin,ZHANG Zijian,MA Kaifu,et al. Theoretical prediction on the nozzle thrust of scramjets[J]. Physics of Gases,2022,7(1): 1-8. (in Chinese
HAN Xin, ZHANG Zijian, MA Kaifu, et al. Theoretical prediction on the nozzle thrust of scramjets[J]. Physics of Gases, 2022, 7(1): 1-8. (in Chinese)
|
| [15] |
ALLGOOD D,GUTMARK E,HOKE J,et al. Performance measurements of multicycle pulse-detonation-engine exhaust nozzles[J]. Journal of Propulsion and Power,2006,22(1): 70-79. doi: 10.2514/1.11499
|
| [16] |
OWENS Z,HANSON R. Unsteady nozzle design for pulse detonation engines: AIAA 2005-3649 [R]. Virigina: AIAA,2005.
|
| [17] |
OWENS Z,HANSON R. Single-cycle unsteady nozzle phenomena in pulse detonation engines[J]. Journal of Propulsion and Power,2007,23(2): 325-337. doi: 10.2514/1.22415
|
| [18] |
WILSON J,SGONDEA A,PAXSON D E,et al. Parametric investigation of thrust augmentation by ejectors on a pulsed detonation tube[J]. Journal of Propulsion and Power,2007,23(1): 108-115. doi: 10.2514/1.19670
|
| [19] |
COOPER M,SHEPHERD J E. Single-cycle impulse from detonation tubes with nozzles[J]. Journal of Propulsion and Power,2008,24(1): 81-87. doi: 10.2514/1.30192
|
| [20] |
STUESSY W,WILSON D,STUESSY W,et al. Experimental investigation of an annular multi-cycle pulsed detonation wave engine: AIAA 1997-808 [R]. Reston,Virigina: AIAA,1997.
|
| [21] |
ZMIJANOVIC V,LEGER L,SELLAM M,et al. Assessment of transition regimes in a dual-bell nozzle and possibility of active fluidic control[J]. Aerospace Science and Technology,2018,82/83: 1-8. doi: 10.1016/j.ast.2018.02.003
|
| [22] |
范玮,严传俊,李强,等. 脉冲爆震发动机尾喷管的实验[J]. 航空动力学报,2007,22(6): 869-872. FAN Wei,YAN Chuanjun,LI Qiang,et al. Experimental investigation on pulse detonation engine nozzles[J]. Journal of Aerospace Power,2007,22(6): 869-872. (in Chinese doi: 10.3969/j.issn.1000-8055.2007.06.004
FAN Wei, YAN Chuanjun, LI Qiang, et al. Experimental investigation on pulse detonation engine nozzles[J]. Journal of Aerospace Power, 2007, 22(6): 869-872. (in Chinese) doi: 10.3969/j.issn.1000-8055.2007.06.004
|
| [23] |
YAN Yu,FAN W,WANG K,et al. Experimental investigation of the effect of bell-shaped nozzles on the two-phase pulse detonation rocket engine performance[J]. Combustion,Explosion,and Shock Waves,2011,47(3): 335-342. doi: 10.1134/S0010508211030117
|
| [24] |
ZHANG Qibin,FAN Wei,WANG Ke,et al. Impact of nozzles on a valveless pulse detonation rocket engine without the purge process[J]. Applied Thermal Engineering,2016,100: 1161-1168. doi: 10.1016/j.applthermaleng.2016.02.135
|
| [25] |
ZHANG Qibin,QIAO Xinqi,FAN Wei,et al. Study on operation and propulsion features of a pulse detonation rocket engine with secondary oxidizer injection[J]. Applied Thermal Engineering,2020,180: 115661. doi: 10.1016/j.applthermaleng.2020.115661
|
| [26] |
秦亚欣,高歌. 环形爆震室引射增推试验研究[J]. 科学技术与工程,2016,16(6): 117-120,128. QIN Yaxin,GAO Ge. Experimental study on thrust augmentation of toroidal detonative chamber ejector systems[J]. Science Technology and Engineering,2016,16(6): 117-120,128. (in Chinese doi: 10.3969/j.issn.1671-1815.2016.06.020
QIN Yaxin, GAO Ge. Experimental study on thrust augmentation of toroidal detonative chamber ejector systems[J]. Science Technology and Engineering, 2016, 16(6): 117-120, 128. (in Chinese) doi: 10.3969/j.issn.1671-1815.2016.06.020
|
| [27] |
王凌羿,郑龙席,黄康,等. 回流型脉冲爆震燃烧室工作特性分析[J]. 推进技术,2021,42(4): 898-905. WANG Lingyi,ZHENG Longxi,HUANG Kang,et al. Operating characteristics of a reverse flow pulse detonation combustor[J]. Journal of Propulsion Technology,2021,42(4): 898-905. (in Chinese
WANG Lingyi, ZHENG Longxi, HUANG Kang, et al. Operating characteristics of a reverse flow pulse detonation combustor[J]. Journal of Propulsion Technology, 2021, 42(4): 898-905. (in Chinese)
|
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