2级脉冲爆震发动机中超声速射流对撞诱导激波聚焦试验研究
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摘要
为研究2-St age PDE中连续超声速射流及结构参数对撞诱导激波聚焦的影响规律,在冷态条件下开展了2-St age PDE中连续超声速射流对撞诱导激波聚焦的试验。分析了喷口宽度、导流环深度、凹面腔开口端与喷管间距、尾喷管角度、射流入射压力等参数对凹面腔底部峰值压力的影响。结果表明:喷口宽度、导流环深度、凹面腔开口端与喷口间距、射流入射压力越大,凹面腔底部峰值压力越大,激波聚焦效果越好;尾喷管角度越大,凹面腔底部峰值压力越小,激波聚焦效果越差;喷口宽度、导流环深度、射流入射压力对激波聚焦的影响较大。
In order to study the influence of continuous supersonic jet and structure parameters on shock focusing induced by collision in 2-Stage PDE,the experiment of continuous supersonic jet on shock focusing induced by collision in 2-Stage PDE was carried out under cold condition. The influence of the width of the nozzle,depth of guide ring,distance between the open end of concave cavity and nozzle,angle of nozzle and pressure of jet incidence on the peak pressure at the bottom of concave cavity were analyzed. The results show that the larger the width of the nozzle,the depth of the guide ring,the distance between the open end of the concave cavity and the nozzle,the jet incidence pressure are,the greater the peak pressure at the bottom of the concave cavity is,and the better the shock focusing effect is. The bigger the angle of nozzle is,the smaller the peak pressure at the bottom of concave cavity is and the worse the shock focusing effect is.
In order to study the influence of continuous supersonic jet and structure parameters on shock focusing induced by collision in 2-Stage PDE,the experiment of continuous supersonic jet on shock focusing induced by collision in 2-Stage PDE was carried out under cold condition. The influence of the width of the nozzle,depth of guide ring,distance between the open end of concave cavity and nozzle,angle of nozzle and pressure of jet incidence on the peak pressure at the bottom of concave cavity were analyzed. The results show that the larger the width of the nozzle,the depth of the guide ring,the distance between the open end of the concave cavity and the nozzle,the jet incidence pressure are,the greater the peak pressure at the bottom of the concave cavity is,and the better the shock focusing effect is. The bigger the angle of nozzle is,the smaller the peak pressure at the bottom of concave cavity is and the worse the shock focusing effect is.
引文
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[15]蔡晓东,梁剑寒,林志勇,等.基于自适应网格加密的超声速可燃气热射流起爆详细反应数值模拟[J].航空动力学报,2014,29(10):2385-2392.CAI Xiaodong,LIANG Jianhan,LIN Zhiyong,et al. Adaptive mesh refinement-based numerical simulation of initiation in supersonic combustible mixtures using hot jet with detailed reaction model[J].Journal of Aerospace Power,2014,29(10):2385-2392.(in Chinese)
[16]何立明,刁志成,蒋永健,等.连续超声速射流对撞诱导激波聚焦的机理研究[J].推进技术,2016,37(12):2394-2400.HE Liming,DIAO Zhicheng,JIANG Yongjian,et al. Investigation on mechanism of chock focus induced by continuous supersonic jet collision[J].Journal of Propulsion Technology, 2016,37(12):2394-2400.(in Chinese)
[2] Roy G D,Frolov S M,Borisov A A,et al. Pulsed setonation propulsion:challenges,current status,and future perspective[J]. Progress in Energy and Combustion Science,2004,30(6):545-672.
[3] Abramowicz W,Wierzbicki T. Axical crushing of foam-filled columns[J]. International Journal of Mechanical Sciences,1988,30(3):263-271.
[4] Seitzberger M,Bammerstorfer F G,Degischer H P,et al. Crushing of axially compressed stell tubes filled with aluminium foam[J]. Acta Mechanica,1997,125(1):93-105.
[5] Leyava I A,Tangirala V,Dean A J. Investigation of unsteady flow field in a 2-stage PDE resonator[R]. AIAA-2003-0715.
[6] Taki S,Fujiwara T. A numerical study of detonation resonator[C]//In Application of Detonantion to Propulsion. Mosco:Torus Press,2004:257-261.
[7]李海鹏,何立明,陈鑫,等.凹面腔内激波聚焦起爆爆震波过程的数值模拟[J].推进技术,2010,31(1):87-91.LI Haipeng,HE Liming,CHEN Xin,et al. Numerical investigation by shock wave focusing over cavity reflector[J]. Journal of Propulsion Technology,2010,31(1):87-91.(in Chinese)
[8]荣康.环形向心射流诱导激波聚焦与起爆爆震的实验及数值模拟研究[D].西安:空军工程大学,2011.RONG Kang. Experimental research and numerical simulation of initiation detonation by shock wave focusing induced by circular centripetal jets[D]. Xi'an:Air Force Engineering University,2011.(in Chinese)
[9]张强,何立明,陈鑫,等.两级脉冲爆震发动机的理想热力循环及性能分析[J].推进技术,2012,33(4):499-504.ZHANG Qiang,HE Liming,CHEN Xin,et al. Ideal thermodynamic cycle and performance analysis of 2-stage pulse detonation engine[J].Journal of Propulsion Technology,2012,33(4):499-504.(in Chinese)
[10]曾昊,何立明,吴春华,等.不同形式扩张喷管对两级PDE性能的影响[J].推进技术,2013,34(8):1139-1146.ZENG Hao,HE Liming,WU Chunhua,et al. Investigation for effects of diverging nozzles on two-stage PDE performance[J]. Journal of Propulsion Technology,2013,34(8):1139-1146.(in Chinese)
[11]曾昊.两级脉冲爆震发动机的实验研究与数值模拟[D].西安:空军工程大学,2011.ZENG Hao. Experimental research and numerical simulation of2-stage pulse detonation engine[D]. Xi'an:Air Force Engineering University,2011.(in Chinese)
[12]荣康,何立明,张建邦,等.喷口导流环结构对激波聚焦起爆的影响分析[J].推进技术,2012,33(2):299-305.RONG Kang,HE Liming,ZHANG Jianbang,et al. Investigation on the effects of deflector structure on detonation initiation by shock wave focusing[J].Journal of Propulsion Technology,2012,33(2):299-305.(in Chinese)
[13] HAN Xu,ZHOU Jin,LIN Zhiyong. Experimental investigations of detonation initiation by hot jets in supersonic premixed airstream[J].Chinese Physics:B,2012,21(12):1-5.
[14]王栋.脉冲爆震发动机工作过程数值模拟研究[D].南京:南京理工大学,2007.WANG Dong. Numerical investigation on work process of pulse detonation engine[D]. Nanjing:Nanjing University of Science and Technology,2007.(in Chinese)
[15]蔡晓东,梁剑寒,林志勇,等.基于自适应网格加密的超声速可燃气热射流起爆详细反应数值模拟[J].航空动力学报,2014,29(10):2385-2392.CAI Xiaodong,LIANG Jianhan,LIN Zhiyong,et al. Adaptive mesh refinement-based numerical simulation of initiation in supersonic combustible mixtures using hot jet with detailed reaction model[J].Journal of Aerospace Power,2014,29(10):2385-2392.(in Chinese)
[16]何立明,刁志成,蒋永健,等.连续超声速射流对撞诱导激波聚焦的机理研究[J].推进技术,2016,37(12):2394-2400.HE Liming,DIAO Zhicheng,JIANG Yongjian,et al. Investigation on mechanism of chock focus induced by continuous supersonic jet collision[J].Journal of Propulsion Technology, 2016,37(12):2394-2400.(in Chinese)