凹腔驻涡与支板稳焰组合加力燃烧室模型冷态流场试验  

Experimental investigation on cold flow characteristics of afterburner with cavity/strut hybrid flameholders

作　　者：秦伟林[1] 何小民[1] 金义[1] 蒋波[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》2012年第6期1347-1354,共8页Journal of Aerospace Power

摘　　要：利用粒子图像测速仪(PIV)对凹腔驻涡与支板稳焰组合加力燃烧室模型进行冷态流场测量,获得该加力燃烧室流场的变化规律和压力损失的变化情况.试验结果表明:随着偏转角(5°～17°)的增大,支板稳定器的整流效果变差,得到的流场的均匀性变差;随着进口马赫数(0.18～0.30)的增加,凹腔内旋涡结构变得完整,从凹腔出来的气流沿径向支板稳定器的穿透能力增加.气流在支板稳定器后形成了低速区回流区,随着进口马赫的增加,回流区的宽度有所增加;加力燃烧室的总压损失随进口马赫数的增加而增大,较常规V型稳定器的总压损失大.Particle image velocimetry （PIV） was used to experimentally study the cold flow field of a model rectangular afterburner with cavity/strut hybrid flameholders. The varieties of the total pressure loss coefficient and the cold flow field were obtained. The results show： with the inlet deflective angle （5°～17°）increases, the flow field after the strut flameholders becomes less uniform, indicating worse rectification of the flameholders. As the inlet Mach number （0.18-0.30） increases, the trapped vortexes in the cavity become more stable and the radial penetrating depth of the air from the cavities increases. The width of the recirculation zone and the total pressure loss increase when the inlet Mach number in- creases. The total pressure loss coefficient of the afterburner is higher than that of an after- burner with V-gutters.

关 键 词：加力燃烧室 粒子图像测速仪 凹腔与支板稳定器 回流区 整流 总压损失 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]