马赫5一级定几何二元混压式进气道反压特性试验研究  

Experimental Investigation on Back-Pressure Characteristic of Ma 5 Fix-Geometry Two-dimensional Inlet with Mixed-Compression

作　　者：翁小侪[1,2,3,4] 郭荣伟[1,2,4] 

机构地区：[1]南京航空航天大学能源与动力学院 [2]南京航空航天大学江苏省航空动力系统重点实验室 [3]中国人民解放军94710部队 [4]先进航空发动机协同创新中心

出　　处：《南京航空航天大学学报》2015年第6期869-876,共8页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：对一种设计马赫数为5一级的定几何二元混压式亚燃冲压发动机进气道进行了风洞试验研究,得到了该进气道的反压特性,结果表明:设计状态时,随节流锥堵塞度的增加,进气道出口反压比不断增加,马赫数逐渐下降,总压恢复系数先下降后上升,通道内气流脉动的功率谱密度无明显峰值;节流锥堵塞比为72%时,进气道发生喘振,喘振基频约为48Hz;随节流锥堵塞比的降低,进气道喘振基频逐渐降低,进气道结束喘振后结尾激波先到达进气道进口处,然后稳定在进气道内收缩段内,随着节流锥堵塞比的进一步降低,结尾激波逐渐进入进气道扩张段。Experiments of a Ma 5 fix-geometry two-dimensional ramjet inlet with mixed-compression are conducted in a hypersonic wind tunnel.The results show that：under cruising condition,when the throttling ratio increases,at the exit of the inlet,the back pressure ratio rises,the Mach number decreases and the total pressure recovery coefficient declines firstly and rises then.The power spectrum of the dynamic pressure signals in the duct generally has no obvious peak value.When the throttling ratio is equal to 72%,buzz occurs in the inlet.The base frequency of the buzz is about equal to 48 Hz.As the throttling ratio decreases,the base frequency of the buzz declines and the terminal shock reaches the intake when the buzz ends.With a further decrease of the throttling ratio,the terminal shock firstly locates at the internal compression section and then enters the divergent section.

关 键 词：航空航天推进系统 二元进气道 喘振 总压恢复 功率谱 

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]