预爆震管工作特性实验研究
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摘要
以氢气为燃料,氧气为氧化剂,利用动态气体填充方式,分析了不同阻塞比、不同管径和不同当量比对预爆震管工作特性的影响,并研究了点火后管内爆震波的形成和传播特点;实验表明:在恰当的阻塞比条件下,预爆震管内的湍流燃烧强度和压力脉动强度得到加强,有利于强化管内爆震波传播;管内爆震波传播速度、强度与预爆震管管径成正比;其次适当增加预爆震管内预混气体当量比,有利于促进爆震波形成与发展。
Using hydrogen as fuel,oxygen as oxidant,it used the dynamic gas filling way to analyze the working characteristics of pre-detonation tube under the different blocking ratio,different pipe diameter and equivalent ratio. and study the characteristics of detonation wave in the detonation tube after the ignition. The experimental results shows that the turbulent combustion and pressure pulsation intensity in the are strengthened under the proper blocking ratio,which is helpful to enhance the propagation of detonation wave in the tube. The propagation speed and strength of the detonation wave are directly proportional to the diameter of the pre-detonation tube. Secondly,increasing the gas equivalent ratio is beneficial to the formation and development of detonation wave.
Using hydrogen as fuel,oxygen as oxidant,it used the dynamic gas filling way to analyze the working characteristics of pre-detonation tube under the different blocking ratio,different pipe diameter and equivalent ratio. and study the characteristics of detonation wave in the detonation tube after the ignition. The experimental results shows that the turbulent combustion and pressure pulsation intensity in the are strengthened under the proper blocking ratio,which is helpful to enhance the propagation of detonation wave in the tube. The propagation speed and strength of the detonation wave are directly proportional to the diameter of the pre-detonation tube. Secondly,increasing the gas equivalent ratio is beneficial to the formation and development of detonation wave.
引文
[1] WOLANSKI P. Development of continuous rotationg detonation engine[R]. Deflagratiove and Detonative Combustion,Moscow,2010.
[2] NETTLETON M A. Recent work on gaseous detonation(Review)[J]. Shock Waves,2002(12):3-12.
[3] LEE J H S. The detonation phenomenon[M]. Cambridge:University Press,2008:327-339.
[4]刘世杰,林志勇,覃慧,等.连续旋转爆震发动机研究进展[J].飞航导弹,2010(2):70-75.
[5] ZHOU S,MA H,LI S,et al. Effects of a turbine guide vane on hydrogen-air rotating detonation wave propagation characteristics[J]. International Journal of Hydrogen Energy,2017,42(31):20297-20305.
[6] JONES D A,SICHEL M,ORAN E S. Reignition of detonation by reflected shocks[J]. Shock Wave,1995,5(1/2):47-57.
[7] ZHOU S,MA H,LIU D,et al. Experimental study of a hydrogen-air rotating detonation combustor[J]. International Journal of Hydrogen Energy,2017,42(21):14741-14749.
[8]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.
[9]李牧,多循环爆震研究[D].西安:西北工业大学,2007.
[10]林伟,韩旭,刘世杰等倾斜横向射流起爆爆震波的二维模拟[C]//第十届全国激波与激波管学术会议论文集.中国力学学会激波与激波管委员会,黄山:2010:195-200.
[11]刘云峰,余荣国,王建平.脉冲爆震发动机快起爆的二维数值模拟[J].推进技术,2004,25(5):454-457.
[12] RAGLAND K W,COSENS G L,CULLEN R E. Detonaition of Hydron-Oxygen an low Temperature and High pressure[J]. AIAA Journal,1964,2(1):142-144.
[13] SCOTT W T,PUAL I K,FREDERICK R S,JOHN L H.Thermal Managerment for a Modular rotating Detonation engine[R]. AIAA2013-1176,2,2013.
[14] ZHOU S,MA H,MA Y,et al. Experimental study on a rotating detonation combustor with an axial-flow turbine[J].Acta Astronautica,2018,151:7-14.
[15]林伟,周进,林志勇,等.热射流起爆过程数值模拟研究[J]国防科技大学学报,2015,37(1):70-77,89.
[16]王治武,陈星谷,郑龙席,等.横向射流起爆爆波数值研究[J].推进技术,2013,34(3):422-427.
[17]曾昊,何立明,章雄伟,等.横向爆震射流起爆爆震过的数值模拟[J].应用力学学报,2010,27(3):543-548.
[18]林伟,爆震燃烧热射流起爆机理研究[D].长沙:国防科学技术大学,2010.
[2] NETTLETON M A. Recent work on gaseous detonation(Review)[J]. Shock Waves,2002(12):3-12.
[3] LEE J H S. The detonation phenomenon[M]. Cambridge:University Press,2008:327-339.
[4]刘世杰,林志勇,覃慧,等.连续旋转爆震发动机研究进展[J].飞航导弹,2010(2):70-75.
[5] ZHOU S,MA H,LI S,et al. Effects of a turbine guide vane on hydrogen-air rotating detonation wave propagation characteristics[J]. International Journal of Hydrogen Energy,2017,42(31):20297-20305.
[6] JONES D A,SICHEL M,ORAN E S. Reignition of detonation by reflected shocks[J]. Shock Wave,1995,5(1/2):47-57.
[7] ZHOU S,MA H,LIU D,et al. Experimental study of a hydrogen-air rotating detonation combustor[J]. International Journal of Hydrogen Energy,2017,42(21):14741-14749.
[8]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.
[9]李牧,多循环爆震研究[D].西安:西北工业大学,2007.
[10]林伟,韩旭,刘世杰等倾斜横向射流起爆爆震波的二维模拟[C]//第十届全国激波与激波管学术会议论文集.中国力学学会激波与激波管委员会,黄山:2010:195-200.
[11]刘云峰,余荣国,王建平.脉冲爆震发动机快起爆的二维数值模拟[J].推进技术,2004,25(5):454-457.
[12] RAGLAND K W,COSENS G L,CULLEN R E. Detonaition of Hydron-Oxygen an low Temperature and High pressure[J]. AIAA Journal,1964,2(1):142-144.
[13] SCOTT W T,PUAL I K,FREDERICK R S,JOHN L H.Thermal Managerment for a Modular rotating Detonation engine[R]. AIAA2013-1176,2,2013.
[14] ZHOU S,MA H,MA Y,et al. Experimental study on a rotating detonation combustor with an axial-flow turbine[J].Acta Astronautica,2018,151:7-14.
[15]林伟,周进,林志勇,等.热射流起爆过程数值模拟研究[J]国防科技大学学报,2015,37(1):70-77,89.
[16]王治武,陈星谷,郑龙席,等.横向射流起爆爆波数值研究[J].推进技术,2013,34(3):422-427.
[17]曾昊,何立明,章雄伟,等.横向爆震射流起爆爆震过的数值模拟[J].应用力学学报,2010,27(3):543-548.
[18]林伟,爆震燃烧热射流起爆机理研究[D].长沙:国防科学技术大学,2010.