连续旋转爆轰发动机外流场三维数值模拟
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摘要
为研究连续旋转爆轰发动机(CRDE)内外流场的变化特性,采用氢气-空气单步有限速率化学反应模型,对内径为40 mm、外径为60 mm、长度为50 mm的连续旋转爆轰发动机进行三维数值模拟,获得了CRDE内外流场结构特征和旋转爆轰波相关参数的变化特性,分析了不同进气总压条件对流场结构和发动机性能的影响。结果表明:爆轰产物在燃烧室出口附近膨胀加速,压力和温度大幅降低,在流场下游产生激波使压力回升,且随进气总压的升高,激波距燃烧室出口距离增加;出口附近羽流中心形成低压高温区域,中心平面上的平均压力低于环境压力,给发动机推力带来了副作用;羽流外围的空气受出口处斜激波的扰动,压力呈现出周期性变化;发动机推力随进气总压的升高而呈线性增加,进气总压为0.55MPa时,发动机推力达到了1160 N。计算仿真结果对掌握连续旋转爆轰发动机外流场特性具有一定的参考价值。
To investigate the characteristics of the internal and external flow field in a continuous rotating detonation engine(CRDE),a one-step hydrogen-air finite rate chemical reaction model has been used to simulate the three-dimensional continuous rotating detonation engine with an inner diameter of 40 mm,an outer diameter of 60 mm and a length of 50 mm.The structural characteristics of the internal and external flow field of CRDE and the variation characteristics of the parameters related to the rotating detonation wave have been obtained.The effects of different inlet stagnation pressure conditions on the flow field structure and engine performances have been analyzed.It has been shown that the detonation product accelerates near the exit of the combustion chamber,with the pressure and temperature greatly reduced,and a shock wave is formed from the downstream flow field.As the inlet stagnation pressure rises,the distance between the shock wave and the outlet of the combustion chamber increases.The low-pressure and hightemperature zone is formed in the center of the plume near the outlet,so that the average pressure on the center plane is lower than the ambient pressure,which brings the side effects to the engine thrust.The air around the plume is disturbed by oblique shock waves at the outlet,and the pressure changes periodically.The thrust of the engine increases linearly with the inlet stagnation pressure rising.The thrust of the engine reaches 1160 N when the inlet stagnation pressure is 0.55 MPa.
To investigate the characteristics of the internal and external flow field in a continuous rotating detonation engine(CRDE),a one-step hydrogen-air finite rate chemical reaction model has been used to simulate the three-dimensional continuous rotating detonation engine with an inner diameter of 40 mm,an outer diameter of 60 mm and a length of 50 mm.The structural characteristics of the internal and external flow field of CRDE and the variation characteristics of the parameters related to the rotating detonation wave have been obtained.The effects of different inlet stagnation pressure conditions on the flow field structure and engine performances have been analyzed.It has been shown that the detonation product accelerates near the exit of the combustion chamber,with the pressure and temperature greatly reduced,and a shock wave is formed from the downstream flow field.As the inlet stagnation pressure rises,the distance between the shock wave and the outlet of the combustion chamber increases.The low-pressure and hightemperature zone is formed in the center of the plume near the outlet,so that the average pressure on the center plane is lower than the ambient pressure,which brings the side effects to the engine thrust.The air around the plume is disturbed by oblique shock waves at the outlet,and the pressure changes periodically.The thrust of the engine increases linearly with the inlet stagnation pressure rising.The thrust of the engine reaches 1160 N when the inlet stagnation pressure is 0.55 MPa.
引文
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[13]邵业涛,王健平,唐新猛,等.连续旋转爆轰发动机流场三维数值模拟[J].航空动力学报,2010,25(8):1717-1722.SHAO Yetao,WANG Jianping,TANG Xingmeng,et al.Three-dimentional numerical simulation of continuous rotating detonation engine flowfields[J].Journal of Aerospace Power,2010,25(8):1717-1722.
[14]张旭东,范宝春,归明月,等.旋转爆轰的三维结构和侧向稀疏波的影响[J].爆炸与冲击,2010,30(4):337-341.ZHANG Xudong,FAN Baochun,GUI Mingyue,et al.Threedimentional structure of detonation and effect of lateral rarefaction waves[J].Explosion and Shock Waves,2010,30(4):337-341.
[15]李宝星,翁春生.连续旋转爆轰发动机气液两相爆轰波传播特性二维数值研究[J].固体火箭技术,2015,38(5):646-652.LI Baoxing,WENG Chunsheng.Numerical investigation on two-dimension gas-liquid two-phase detonation wave propulsion characteristic of continuous rotating detonation engine[J].Journal of Solid Rocket Technology,2015,38(5):646-652.
[16]马虎,武晓松,杨成龙,等.分开喷注方式下旋转爆震发动机三维数值模拟[J].燃烧科学与技术,2016,22(1):9-14.MA Hu,WU Xiaosong,YANG Chenglong,et al.Three-dimensional numerical simulation of rotating detonation engine with separate injection[J].Journal of Combustion Science and Technology,2016,22(1):9-14.
[2]Voitsekhovskii B V.Stationary spin detonation[J].Soviet Journal of Applied Mechanics and Technical Physics,1960,3:157164.
[3]Bykovskii F A,Zhdan S A,Vedernikov E F.Initiation of detonation of fuel-air mixtures in a flow-type annular combustor[J].Combustion,Explosion,and Shock Waves,2014,50(2):214-222.
[4]Bykovskii F A,Vedernikov E F.Continuous detonation of a subsonic flow of a propellant[J].Combustion,Explosion and Shock Waves,2003,39(3):323-334.
[5]Fotia M L,Hoke J,Schauer F.Experimental ignition characteristics of a rotating detonation engine under backpressured conditions[R].AIAA 2015-0632.
[6]Wolański P.Application of the continuous rotating detonation to gas turbine[C]//Applied Mechanics and Materials.Trans.Tech.Publications,2015,782:3-12.
[7]Zheng Quan,Weng Chunsheng,Bai Qiaodong.Experimental research on the propagation process of continuous rotating detonation wave[J].Defence Technology,2013,9(4):201-207.
[8]林伟,周进,林志勇,等.H2/Air连续旋转爆震发动机推力测试(II)---双波模态下的推力[J].推进技术,2015,36(5):641-649.LIN Wei,ZHOU Jin,LIN Zhiyong,et al.Thrust measurement of H2/Air continuously rotating detonation engine(II)-thrust under dual wave mode[J].Journal of Propulsion Technology,2015,36(5):641-649.
[9]Zhdan S A,Bykovskii F A,Vedernikov E F.Mathemati-cal modeling of a rotating detonation wave in a hydrogen-oxygen mixture[J].Combustion,explosion,and shock waves,2007,43(4):449-459.
[10]Yi T H,Lou J,Turangan C,et al.Effect of nozzle shapes on the performance of continuously rotating detonation engine[R].AIAA 2010-152.
[11]Eude Y,Davidenko D M,Gokalp I.Use of the adaptive mesh refinement for 3D simulations of a CDWRE(continuous detonation wave rocket engine)[R].AIAA 2011-2236.
[12]Schwer D A.Kailasanath K.Modeling exhaust effects in rotating detonation engines[R].AIAA 2012-3943.
[13]邵业涛,王健平,唐新猛,等.连续旋转爆轰发动机流场三维数值模拟[J].航空动力学报,2010,25(8):1717-1722.SHAO Yetao,WANG Jianping,TANG Xingmeng,et al.Three-dimentional numerical simulation of continuous rotating detonation engine flowfields[J].Journal of Aerospace Power,2010,25(8):1717-1722.
[14]张旭东,范宝春,归明月,等.旋转爆轰的三维结构和侧向稀疏波的影响[J].爆炸与冲击,2010,30(4):337-341.ZHANG Xudong,FAN Baochun,GUI Mingyue,et al.Threedimentional structure of detonation and effect of lateral rarefaction waves[J].Explosion and Shock Waves,2010,30(4):337-341.
[15]李宝星,翁春生.连续旋转爆轰发动机气液两相爆轰波传播特性二维数值研究[J].固体火箭技术,2015,38(5):646-652.LI Baoxing,WENG Chunsheng.Numerical investigation on two-dimension gas-liquid two-phase detonation wave propulsion characteristic of continuous rotating detonation engine[J].Journal of Solid Rocket Technology,2015,38(5):646-652.
[16]马虎,武晓松,杨成龙,等.分开喷注方式下旋转爆震发动机三维数值模拟[J].燃烧科学与技术,2016,22(1):9-14.MA Hu,WU Xiaosong,YANG Chenglong,et al.Three-dimensional numerical simulation of rotating detonation engine with separate injection[J].Journal of Combustion Science and Technology,2016,22(1):9-14.
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