可变内收缩比侧压式进气道自起动性能  

Self-starting characteristics for sidewall-compression inlet with variable internal contraction ratio

作　　者：潘瑾[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》2007年第3期278-281,321,共5页Journal of Propulsion Technology

基　　金：国家"八六三"计划702专题(2003AA723020)

摘　　要：为了寻求一种实现进气道自起动的方法,在数值模拟结果的前提下,开展了可移动唇口板的侧压式进气道自起动特性风洞实验。数值模拟结果发现,在侧压式进气道唇口板逐级后移和前伸过程中,存在起动迟滞现象。通过移动唇口板减小内收缩比,侧压式进气道能够实现自起动。实验结果表明:在来流Ma3.85条件下,唇口板后移时,该模型侧压式进气道自起动内收缩比在1.24至1.28之间,对于已起动的侧压式进气道,唇口板前伸到内收缩比为Ric=1.33,该进气道仍起动。　A combination of CFD simulation and experimental study was performed at Mach 3.85 with total pressure 0.7 MPa and total temperature 300 K.A three-dimensional sidewall-compression inlet with movable cowl is applied perform.Results show that self-starting Ric of the model inlet is between 1.24 and 1.28.For a model inlet which has started will keep starting condition until Ric reaches 1.33 by moving cowl forward.Delay phenomenon exists during the process of cowl backward and forward.The sidewall compression inlet model can realize self-starting by moving cowl backward.

关 键 词：冲压喷气发动机 侧压式进气道^+ 可变内收缩比^+ 数值仿真 风洞实验 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]