单通道内燃波转子燃烧性能实验  

Experiment on combustion performance of single channel wave rotor combustor

作　　者：巩二磊[1] 李建中[1] 韩启祥[1] 刘博强[1] 

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016

出　　处：《航空动力学报》2016年第5期1127-1132,共6页Journal of Aerospace Power

基　　金：国家自然科学基金(51476077);江苏省研究生培养创新工程(KYLX-0299)

摘　　要：建立简化单通道内燃波转子系统,以连续热射流的点火方式,采用实验方法研究了点火位置,射流作用时间,初始预混气当量油气比对波转子通道内点火及燃烧性能的影响.结果表明:随着射流逐渐推近,喷管出口距波转子通道38mm附近时,对点火不利,但点火位置对火焰锋面发展影响不大;在不同当量油气比下,射流作用时间对波转子通道内燃烧过程压力增益具有不同的影响规律,同时火焰锋面倾斜角随着射流作用时间增加而有所减小;当量油气比为2.0时不利于波转子内组织燃烧,且此时火焰锋面出现反向倾斜,倾斜角高达58°.An experimental system of a simplified single channel wave rotor combustor was established. Experimental investigations were conducted to evaluate the influences of ig- niting position, jet acting time and initial pre-mixing equivalence fuel/air ratio of premixed gas on the combustion performance. Continuous hot jet was applied to ignite the premixed gas. Results show that ignition is most difficult when the distance between the nozzle exit and the wave rotor channel is approximately 38 ram. However, the igniting position has little influence on development of the flame front. The influences of jet acting time on the pressure gain depend on equivalence fuel/gas ratio. The tilt angle of flame front decreases as jet acting time increases. When the equivalence fuel/gas ratio is 2.0, the combustion is unsatisfactory in the wave rotor. Meanwhile, reverse inclination of the flame front emerges with 58 degree tilt angle.

关 键 词：内燃波转子 增压燃烧 点火位置 射流作用时间 当量油气比 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]