乙烯和汽油多循环脉冲爆震发动机起爆特性比较  

Comparative ignition characteristics of ethylene and gasolene in multi-cycle pulse detonation engine

作　　者：程晓军[1] 范育新[1] 蔡迪[1] 韩启祥[1] 王家骅[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2013年第10期2276-2283,共8页Journal of Aerospace Power

基　　金：江苏省普通高校研究生科研创新计划(CXZZ12_0167)

摘　　要：为了研究脉冲爆震发动机(PDE)结构对其工作性能的影响,在内径为40mm、长为1 050mm的气动阀式脉冲爆震发动机样机上,进行了气态乙烯/空气和液态汽油/空气的多循环起爆特性试验研究.研究结果表明:在25,30Hz和40Hz下都能在乙烯/空气中成功触发爆震波,40Hz下产生C-J(Chapman-Jouguet)爆震波,传播速度为1 724m/s(低于C-J爆震波速度理论值1 832.45m/s的5.6%),峰值压力为3.01MPa(高于C-J爆震波压力理论值2.79MPa的7.88%).在相同结构下,汽油/空气未能完成由缓燃向爆震转变的过程.通过对比两种燃料下的试验结果发现:相对于气态燃料,液态燃料受其蒸发过程的影响,在爆震管内的火焰加速缓慢,需要更多的强化燃烧装置来加速火焰,带来的总压损失也更大.因此,对于液态燃料改善雾化和蒸发,提高可爆混气的质量是其实现低阻起爆的关键.To investigate the influence of the structure of multicycle pulse detonation engine （PDE） on its operation performance, experiments of ethyleneair and gasolineair mixtures initiation process in the aerovalve PDE of 1050 mm length and 40 mm inner diame ter were performed. The results show that the detonation wave can be successfully initiated in the ethyleneair with frequency of 25, 30 Hz and 40 Hz, and CJ （ChapmanJouguet） deto nation wave can be achieved at the frequency of 40 Hz with detonation wave propagation velocity of 1724m/s （less 5.6G than the CJ detonation wave velocity theoretical value 1 832.45 m/s） and peak wave pressure of 3.01MPa （higher 7. 880//oo than the CJ detonation wave pressure theoretical value 2. 79 MPa）. While the deflagration to detonation transition failed to complete in gasoleneair. By comparison of the two results, it was found that the evaporation process dominated the initiation process in liquid fuels, thus slowering the flame acceleration process in the detonation tube. More novel and optimizeddesigned reinforcedcombustion devices for accelerating the flame should be developed, which may cause higher total pressure loss. Thus, atomization and evaporation to improve the quality of the mixture is a key technology for detonation in the liquid fuel.

关 键 词：缓燃向爆震转变 爆震管 火焰传播速度 压力波速度 爆震波 

分 类 号：V231.22[航空宇航科学与技术—航空宇航推进理论与工程]