LEE J H S . The detonation phenomenon [M ] . Cambridge,UK : Cambridge University Press , 2008 .

王健平 , 周蕊 , 武丹 . 连续旋转爆轰发动机的研究进展 [J ] . 实验流体力学 , 2015 , 29 ( 4 ): 12 - 25 .

WANG J P , ZHOU R , WU D . Progress of continuously rotating detonation engine research [J ] . Journal of Experiments in Fluid Mechanics , 2015 , 29 ( 4 ): 12 - 25 . (in Chinese)

XIE Q F , WEN H C , LI W H , et al . Analysis of operating diagram for H 2 /air rotating detonation combustors under lean fuel condition [J ] . Energy , 2018 , 151 : 408 - 419 .

MA Z , ZHANG S J , LUAN M Y , et al . Experimental research on ignition,quenching,reinitiation and the stabilization process in rotating detonation engine [J ] . International Journal of Hydrogen Energy , 2018 , 43 : 18521 - 18529 .

LIU S J , HUANG S Y , PENG H Y , et al . Characteristics of methane-air continuous rotating detonation wave in hollow chambers with different diameters [J ] . Acta Astronautica , 2021 , 183 : 1 - 10 .

LIN W , ZHOU J , LIU S J , et al . An experimental study on CH 4 /O 2 continuously rotating detonation wave in a hollow combustion chamber [J ] . Experimental Thermal and Fluid Science , 2015 , 62 : 122 - 130 .

ZHU Y Y , WANG K , ZHAO M H , et al . Experimental study on wave propagations in a rotating detonation chamber with different outlet configurations [J ] . Acta Astronautica , 2022 , 200 : 388 - 399 .

ZHU Y Y , WANG K , WANG Z C , et al . Study on the performance of a rotating detonation chamber with different aerospike nozzles [J ] . Aerospace Science and Technology , 2020 , 107 : 106338 .

KINDRACKI J . Experimental research on rotating detonation in liquid fuel-gaseous air mixtures [J ] . Aerospace Science and Technology , 2015 , 43 : 445 - 453 .

BYKOVSKII F A , ZHDAN S A , VEDERNIKOV E F . Continuous spin detonation of a heterogeneous kerosene-air mixture with addition of hydrogen [J ] . Combustion,Explosion,and Shock Waves , 2016 , 52 : 371 - 373 .

ZHENG Q , MENG H L , WENG C S , et al . Experimental research on the instability propagation characteristics of liquid kerosene rotating detonation wave [J ] . Defence Technology , 2020 , 16 : 1106 - 1115 . DOI: 10.1016/j.dt.2020.06.028 http://doi.org/10.1016/j.dt.2020.06.028 In order to study the instability propagation characteristics of the liquid kerosene rotating detonation wave (RDW), a series of experimental tests were carried out on the rotating detonation combustor (RDC) with air-heater. The fuel and oxidizer are room-temperature liquid kerosene and preheated oxygen-enriched air, respectively. The experimental tests keep the equivalence ratio of 0.81 and the oxygen mass fraction of 35% unchanged, and the total mass flow rate is maintained at about 1000 g/s, changing the total temperature of the oxygen-enriched air from 620 K to 860 K. Three different types of instability were observed in the experiments: temporal and spatial instability, mode transition and re-initiation. The interaction between RDW and supply plenum may be the main reason for the fluctuations of detonation wave velocity and pressure peaks with time. Moreover, the inconsistent mixing of fuel and oxidizer at different circumferential positions is related to RDW oscillate spatially. The phenomenon of single-double-single wave transition is analyzed. During the transition, the initial RDW weakens until disappears, and the compression wave strengthens until it becomes a new RDW and propagates steadily. The increased deflagration between the detonation products and the fresh gas layer caused by excessively high temperature is one of the reasons for the RDC quenching and re-initiation. © 2020 China Ordnance Society

MENG H L , ZHENG Q , WENG C S , et al . Propagation mode analysis of rotating detonation waves fueled by liquid kerosene [J ] . Acta Astronautica , 2021 , 187 : 248 - 258 .

FENG W K , ZHENG Q , XIAO Q , et al . Effects of cavity length on operating characteristics of a ramjet rotating detonation engine fueled by liquid kerosene [J ] . Fuel , 2023 , 332 : 126129 .

YANG X K , WU Y , SONG F L , et al . Experimental study on a premixed rotating detonation combustor using Tesla inlet configuration fueled by kerosene [J ] . Experimental Thermal and Fluid Science , 2023 , 146 : 110928 .

HAN X P , HUANG Y K , ZHENG Q , et al . Study of the characteristics and combustion efficiency of liquid kerosene/oxygen-enriched air rotating detonation wave with different modes [J ] . Fuel , 2024 , 355 : 1129424 .

李宝星 , 王中 , 许桂阳 , 等 . 煤油燃料旋转爆轰波起爆与传播特性实验研究 [J ] . 兵工学报 , 2020 , 41 ( 7 ): 1339 - 1346 . DOI: 10.3969/j.issn.1000-1093.2020.07.011 http://doi.org/10.3969/j.issn.1000-1093.2020.07.011 为研究煤油燃料旋转爆轰波的起爆与传播特性，开展气体-液体两相旋转爆轰发动机实验研究。旋转爆轰发动机环形燃烧室内径120 mm、外径153 mm、长240 mm，煤油为燃料、富氧空气为氧化剂，通过氢气/氧气微小型脉冲爆轰发动机进行点火；基于燃烧室内的高频压力，分析气体-液体两相旋转爆轰波的起爆过程、传播特性以及发动机的工作特性。实验结果表明：混合物的反应活性至关重要，当氧化剂中氧含量偏低时，混合物反应活性低，旋转爆轰波将无法起爆，直至氧含量增加到39.2%，才能形成自持传播的爆轰波；爆轰波成功起爆后均以双波对撞模态传播，波速为815~ 920 m/s；在 贫油条件下，爆轰波传播速度随着当量比提高呈增加趋势；当空气质量流量大于822 g/s时， 发动机基本以缓燃形式工作。

LI B X , WANG Z , XU G Y , et al . Experimental research on initiation and propagation characteristics of kerosene fuel rotating detonation wave [J ] . Acta Armamentarii , 2020 , 41 ( 7 ): 1339 - 1346 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2020.07.011 http://doi.org/10.3969/j.issn.1000-1093.2020.07.011 A rotating detonation engine（RDE） was test to study the initiation and propagation characteristics of kerosene fuel rotating detonation wave. The inner diameter, outer diameter and length of RDE annular combustor are 120 mm, 153 mm and 240 mm, respectively. It is ignited by a hydrogen/oxygen micro-pulse detonation engine with kerosene and oxygen-rich air used as fuel and oxidant, respectively. The initiation process and propagation of gas-liquid two-phase rotating detonation wave, and the operation characteristics of engine are analyzed from high-frequency pressure signals in combustor. The test results indicate that the reactivity of mixtures plays an important role on the initiation of detonation wave. When the content of oxygen in the oxidant is low, the reactivity of the mixture is low, and the rotating detonation wave fails to be initiated. It is until the oxygen content increases to 39.2% that the rotating detonation wave can be formed. The rotating detonation wave always propagates in two-wave collision mode with the wave velocity range of 815-920 m/s after successful initiation. The velocity of detonation wave tends to rise with the increase in equivalence ratio under lean fuel condition. The engine mainly works in a deflagration mode when the mass flow rate of air is more than 822 g/s. Key

HAN J X , BAI Q D , ZHANG S J , et al . Experimental study on propagation mode of rotating detonation wave with cracked kerosene gas and ambient temperature air [J ] . Physics of Fluids , 2022 , 34 : 075127 .

QIU H , BAI Q D , HAN J X , et al . Effects of blockage ratio on the propagation characteristics of hydrogen-rich gas rotating detonation [J ] . Physics of Fluids , 2023 , 35 : 085119 .

韩家祥 , 白桥栋 , 邱晗 , 等 . 燃烧室结构对煤油预燃裂解气旋转爆轰特性的影响 [J ] . 兵工学报 , 2024 , 45 ( 8 ): 2837 - 2850 . DOI: 10.12382/bgxb.2023.0491 http://doi.org/10.12382/bgxb.2023.0491 在固定来流条件下,改变旋转爆轰燃烧室宽度和出口阻塞比,实验研究上述结构对煤油预燃裂解气与空气旋转爆轰传播特性的影响。实验结果表明:适宜的燃烧室宽度和出口宽度能够促进旋转爆轰波 (Rotating Detonation Wave,RDW)的稳定自持传播,当燃烧室宽度为20mm和 26mm,燃烧室出口宽度为4~8mm时,煤油预燃裂解气和空气能够成功起爆并能稳定传播,增加燃烧室的宽度, RDW传播速度和稳定性均有提升;随着出口阻塞比增加,RDW传播模态经历了稳定单波模态、间断单波模态和双波同向模态,阻塞比的增加能提升燃烧室末端反射激波的强度,促进多波头的产生,RDW传播速度和压力随着阻塞比的增加,经历了升高后降低的变化。

HAN J X , BAI Q D , QIU H , et al . Influence of combustor configuration on rotating detonation characteristics of kerosene pre-combustion cracking gas [J ] . Acta Armamentarii , 2024 , 45 ( 8 ): 2837 - 2850 . (in Chinese) DOI: 10.12382/bgxb.2023.0491 http://doi.org/10.12382/bgxb.2023.0491 The width and outlet blockage ratio of rotating detonation combustion chamber are changed under the condition of fixed incoming flow. The effect of combustor configuration on the rotating detonation characteristics of kerosene pre-combustion cracking gas and air was experimentally investigated. The experimental results show that suitable combustor width and outlet width can promote stable self-sustaining propagation of rotating detonation wave (RDW). When the width of combustor is 20mm or 26mm and the width of combustor outlet is 4~8mm, the kerosene pre-combustion cracking gas and air can be successfully detonated and can propagate stably. The propagation velocity and stability of RDW are improved by increasing the width of combustor. With the increase in outlet blockage ratio, the RDW propagation mode experiences stable single rotating detonation wave (SRDW) mode, intermittent single rotating detonation wave (ISRDW) mode and two-co rotating detonation waves (TCORDW) mode. The blockage ratio can be increased to improve the intensity of reflected shock wave at the end of combustor and promote the generation of multiple wave heads. RDW propagation velocity and pressure increase first and then decrease with the increase in blockage ratio.

胡洪波 , 严宇 , 张锋 , 等 . 煤油富燃燃气旋转爆震燃烧实验研究 [J ] . 推进技术 , 2020 , 41 ( 4 ): 881 - 888 .

HU H B , YAN Y , ZHANG F , et al . Experimental investigation on rotational detonation combustion with fuel-rich gases of kerosene [J ] . Journal of Propulsion Technology , 2020 , 41 ( 4 ): 881 - 888 . (in Chinese)

唐新猛 , 王健平 , 邵业涛 . 连续旋转爆轰波在无内柱圆筒内的数值模拟 [J ] . 航空动力学报 , 2013 , 28 ( 4 ): 792 - 799 .

TANG X M , WANG J P , SHAO Y T . 3-D simulation of rotating detonation wave in combustion chambers without inner wall [J ] . Journal of Aerospace Power , 2013 , 28 ( 4 ): 792 - 799 . (in Chinese)

ZHANG H L , LIU W D , LIU S J . Effects of inner cylinder le ngth on H 2 /air rotating detonation [J ] . International Journal of Hydrogen Energy , 2016 , 41 : 13281 - 13293 .

PENG H Y , LIU W D , LIU S J , et al . Hydrogen-air,ethylene-air,and methane-air continuous rotating detonation in the hollow chamber [J ] . Energy , 2020 , 211 : 118598 .

WANG Y H , LE J L . A hollow combustor that intensifies rotating detonation [J ] . Aerospace Science and Technology , 2019 , 85 : 113 - 124 .

ZHAO M H , WANG K , ZHU Y Y , et al . Effects of the exit convergent ratio on the propagation behavior of rotating detonations utilizing liquid kerosene [J ] . Acta Astronautica , 2022 , 193 : 35 - 43 .

王致程 , 严宇 , 王可 , 等 . 燃烧室宽度对煤油旋转爆震波传播模态的影响 [J ] . 推进技术 , 2021 , 42 ( 4 ): 842 - 850 .

WANG Z C , YAN Y , WANG K , et al . Effects of combustor width on propagation modes of rotating detonation waves utilizing liquid kerosene [J ] . Journal of Propulsion Technology , 2021 , 42 ( 4 ): 842 - 850 . (in Chinese)

ZHOU S B , MA H , ZHOU C S , et al . Experimental research on the propagation process of rotating detonation wave with a gaseous hydrocarbon mixture fuel [J ] . Acta Astronautica , 2021 , 179 : 1 - 10 .

GORDON S , MCBRIDE B J . Computer program for calculation of complex chemical equilibrium compositions and applications I:analysis [Z ] . Cleveland,OH,US:NASA RP-1311 , 1994 .

HAN X P , WANG Y D , ZHENG Q , et al . Experimental study on propagation,quenching,and re-initiation characteristics of rotating detonation wave with liquid kerosene-oxygen-enriched air [J ] . Experimental Thermal and Fluid Science , 2023 , 148 : 110984 .