环缝宽度对旋转爆震发动机工作特性的影响
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摘要
为研究环缝宽度对旋转爆震发动机(rotating detonation engine, RDE)工作特性的影响,在非预混RDE中进行实验,同时采用高频压力传感器、离子探针和高速摄影等测量设备,在同一入口质量流率的条件下,改变空气进气环缝宽度和燃烧室环缝宽度。获得了单波、双波、四波对撞及混合传播模态;当燃烧室环缝宽6 mm时,增加空气进气环缝宽度,爆震波由四波对撞转变为同向双波,最终以单波形式传播;而燃烧室环缝宽10或15 mm时,空气进气环缝宽度对爆震波传播模态的影响较小;此外,四波对撞模态下,爆震波压力峰值和离子信号峰值低于单波和双波模态时的值。
In order to investigate the propagation mode of rotating detonation wave in rotating detonation engine(RDE) with different annular gap width, the experiment was conducted on non-premixed RDE.During the experiment, high-frequency pressure transducers, ion probes and high-speed photography were used simultaneously. Under the condition of the same inlet mass flow rate, the annular gap width of air inlet and detonation chamber were changed. As a result, the propagation mode including the single wave, double wave, four wave collision and mixed mode were obtained. By analyzing the experimental results, it was found that when the detonation chamber width was 6 mm, the detonation wave was changed from four wave collision to double wave, and finally to the single wave as the air inlet width was increased. When the detonation chamber width were 10 and 15 mm, the air inlet width had little influence on detonation wave propagation mode. In addition, under the four wave collision mode, both of the pressure peak and ion signal peak were lower than that of the single wave and double wave modes.
In order to investigate the propagation mode of rotating detonation wave in rotating detonation engine(RDE) with different annular gap width, the experiment was conducted on non-premixed RDE.During the experiment, high-frequency pressure transducers, ion probes and high-speed photography were used simultaneously. Under the condition of the same inlet mass flow rate, the annular gap width of air inlet and detonation chamber were changed. As a result, the propagation mode including the single wave, double wave, four wave collision and mixed mode were obtained. By analyzing the experimental results, it was found that when the detonation chamber width was 6 mm, the detonation wave was changed from four wave collision to double wave, and finally to the single wave as the air inlet width was increased. When the detonation chamber width were 10 and 15 mm, the air inlet width had little influence on detonation wave propagation mode. In addition, under the four wave collision mode, both of the pressure peak and ion signal peak were lower than that of the single wave and double wave modes.
引文
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[14]刘世杰,林志勇,刘卫东,等.连续旋转爆震波传播过程研究(II):双波对撞传播模式[J].推进技术,2014,35(2):270-275.LIU Shijie,LIN Zhiyong,LIU Weidong,et al.Research on continuous rotating detonation wave propagation process(II):twowave collision propagation mode[J].Journal of Propulsion Technology,2014,35(2):270-275.
[15]KOWALKOWSKI M,MATSUTOMI Y,HEISTER S,et al.Flame sensing in pulsed combustion using ion probes diodes and visual indictions:AIAA 2009-4945[R].USA:AIAA,2009.
[2]BYKOVSKII F A,VEDEMIKOV E F,POLOZOV S V,et al.Initiation of detonation in flows of fuel-air mixtures[J].Combustion,Explosion,and Shock Waves,2007,43(3):345-354.
[3]周蕊,李晓鹏.连续旋转爆轰发动机冷流场的混合特性研究[J].航空学报,2016,37(12):3668-3674.ZHOU Rui,LI Xiaopeng.Numerical investigation of mixing characteristic of cold continuously rotating detonation engine[J].Acta Aeronautica et Astronautica Sinica,2016,37(12):3668-3674.
[4]NAPLES A,HOKE J,KARNESKY J,et al.Flowfield characterization of a rotating detonation engine:AIAA,2013-0278[R].USA:AIAA,2013.
[5]BYKOVSKII F A,ZHDAN S A,VEDEMIKOV E F.Continuous spin detonation of fuel-air mixtures[J].Combustion,Explosion,and Shock Waves,2006,42(4):463-471.
[6]BYKOVSKII F A,MITROFANOV V V,VEDEMIKOV E F.Continuous detonation combustion of fuel-air mixtures[J].Combustion,Explosion,and Shock Waves,1997,33(3):344-353.
[7]陈洁,王栋,马虎,等.轴向长度对旋转爆震发动机的影响[J].航空动力学报,2013,28(4):844-849.CHEN Jie,WANG Dong,MA Hu,et al.Influence of axial length on rotating detonation engine[J].Journal of Aerospace Power,2013,28(4):844-849.
[8]RANKIN B A,FOTIA M L,NAPLES A G,et al.Overview of performance,application,and analysis of rotating detonation engine technologies[J].Journal of Propulsion and Power,2017,33(1):131-143.
[9]ANDRUS I Q,POLANKA M D,KING P I,et al.Experimental of premixed rotating detonation engine using variable slot feed plenum[J].Journal of Propulsion and Power,2017:1-11.
[10]SCHWER D,KAILASANATH K.Numerical investigation of the physics of rotating-detonation-engines[J].Proceedings of the Combustion Institute,2011,33:2195-2202.
[11]FROLOV S M,AKSENOV V S,IVANOV V S,et al.Large-scale hydrogen-air continuous detonation combustor[J].International Journal of Hydrogen Energy,2015,40:1616-1623.
[12]FOTIA M L,HOKE J,SCHAUER F.Experimental performance scaling of rotating detonation engines operated on gaseous fuels[J].Journal of Propulsion and Power,2017:1-10.
[13]刘世杰,刘卫东,林志勇,等.连续旋转爆震波传播过程研究(I):同向传播模式[J].推进技术,2014,35(1):138-144.LIU Shijie,LIU Weidong,LIN Zhiyong,et al.Research on continuous rotating detonation wave propagation process(I):one direction mode[J].Journal of Propulsion Technology,2014,35(1):138-144.
[14]刘世杰,林志勇,刘卫东,等.连续旋转爆震波传播过程研究(II):双波对撞传播模式[J].推进技术,2014,35(2):270-275.LIU Shijie,LIN Zhiyong,LIU Weidong,et al.Research on continuous rotating detonation wave propagation process(II):twowave collision propagation mode[J].Journal of Propulsion Technology,2014,35(2):270-275.
[15]KOWALKOWSKI M,MATSUTOMI Y,HEISTER S,et al.Flame sensing in pulsed combustion using ion probes diodes and visual indictions:AIAA 2009-4945[R].USA:AIAA,2009.