内收缩段泄流对超声速进气道的影响研究  

Impact of Internal Contraction Section Bleed on Supersonic Inlet

作　　者：王肖 谢文忠[1] 阳未 张德平 WANG Xiao;XIE Wen-zhong;YANG Wei;ZHANG De-ping(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Sichuan Aerospace Institute of System Engineering,Chengdu 610100,China)

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 [2]四川航天系统工程研究所,四川成都610100

出　　处：《推进技术》2020年第2期324-333,共10页Journal of Propulsion Technology

摘　　要：通过对典型二元超声速进气道进行数值仿真,研究了内收缩段中泄流位置对进气道自起动性能及抗反压能力的影响规律和影响机制。研究结果表明:泄流腔改善进气道自起动性能和抗反压能力的内在机制不尽相同,泄流腔位置决定了进气道在临界不起动状态下的泄流量、临界不起动模式和临界反压状态下的泄流量,其中临界不起动状态下的泄流量和临界不起动模式共同影响进气道的自起动性能,而进气道的抗反压能力则主要由临界反压状态下的泄流量决定。在本研究范围内,当泄流腔前缘到进气道内通道入口与下壁面交点的轴向无量纲距离Le=0.31时,进气道自起动性能最好;当Le=0.15时,临界压比和总压恢复系数最高。The numerical simulation of a typical 2D supersonic inlet is carried out to study the effects of the bleed position in the internal contraction section on the self-starting performance and limiting backpressure of the inlet.The results show that the mechanism of the bleed chamber to improve the self-starting performance and anti-backpressure ability of the inlet is different.The position of the bleed chamber determines the discharge of the inlet in the critical unstarting state,the critical unstarting mode and the discharge flow in the critical back pressure state,in which the discharge flow and the critical unstarting mode in the critical unstarting state jointly affect the self-starting performance of the inlet,while the anti-back pressure ability of the inlet is mainly determined by the discharge flow of critical back pressure state.In the scope of this study,when the dimensionless axial distance from the leading edge of the discharge chamber to the intersection point of the inlet entrance and the inlet down wall is equal to 0.31,the self-starting performance of the inlet is the best,and the critical pressure ratio and total pressure recovery coefficient are the highest when it is equal to 0.15.

关 键 词：超声速进气道 泄流 自起动能力 抗反压能力 

分 类 号：V235.2[航空宇航科学与技术—航空宇航推进理论与工程]