高超侧压式进气道简单唇口调节方案设计  

Concept of a varied geometry scramjet inlet with rotatable cowl

作　　者：金志光[1] 张堃元[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2008年第1期43-48,共6页Journal of Propulsion Technology

基　　金：国家"八六三"基金项目(2003AA723020)

摘　　要：为最大限度提高侧压式进气道流量系数,在定几何进气道基础上设计了一种唇口可调节的简单变几何方案。唇口设计成前伸的后掠三角形以完全挡住第二溢流窗同时排移侧板分离涡。利用Fluent软件研究了变几何进气道马赫6,马赫4下的气动性能,并与定几何直唇口进气道进行了比较。研究发现,简单的唇口调节措施能在显著改善进气道各项总体性能参数的同时获得更高的流量系数:马赫6设计状态下,可调进气道流量系数达0.93;马赫4非设计状态下,流量系数为0.71,能实现自起动。马赫5.3风洞试验结果表明,高马赫数来流条件下,可调进气道三角形尖唇口对改善下游隔离段内的流动结构具有明显效果。Based on a fixed geometry sidewall compression scramjet inlet, a varied geometry inlet with rotatable cowl was designed to increase the mass capture ratio. The cowl was designed as a triangle located at a forward place so that the mass flow spilling from the second spillage window can be entirely captured and the vortexes originated from the separated region on the sidewalls can spill out of the inlet from both sides of the cutback cowl. The performance of the varied geometry inlet was numerically studied at Mach number 6 and 4. Comparisons were made between the varied inlet and the fixed one. Numerical results indicate that most of the performance parameters of the varied inlet were obviously improved, among which higher mass capture ratio with 0.93 at Mach 6 and 0. 71 at Mach 4 was obtained. Numerical and experimental investigation shows for high free-stream Mach number the triangle cowl of the varied inlet has an obvious effect on the flow improvement in the downstream isolator.

关 键 词：超音速冲压喷气发动机 进气道 流量系数 风洞实验 数值仿真 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]