一种组合循环发动机变几何进气道方案  

Investigation of a variable geometry combined cycle engine inlet with double passage

作　　者：刘晓伟[1] 石磊[1] 刘佩进[1] 何国强[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2016年第6期746-750,共5页Journal of Solid Rocket Technology

摘　　要：用于空天往返的组合循环发动机工作马赫数范围宽．为此提出了一种采用双通道调节的变几何进气道设计方案：用一道隔板将进气道内压段分为上下2个通道，低马赫数时，上下2个通道同时进气，高马赫数时，通过旋转外压段最后一道压缩面关闭下通道后，仅上通道进气，从而实现进气道压缩角和收缩比的大范围调节。研究表明，该变几何进气道在Ma=2．2—7．0范围内具有较高的总压恢复系数，尤其是具有很高的流量系数，且大部分区间出口马赫数合适，该变几何进气道方案调节过程简单、可靠，容易实现。Combined cycle engines, used for the spaceflight launch vehicle, have wide Mach number operation range.Therefore, a variable geometry inlet scheme with double passage regulation was put forward in the paper.The inlet inner passage was divided into two passages by a baffle.The lower passage could be close by rotating the last compress face at high fight Mach number, so only the upper passage allows air flow into the engine. The wide operation range regulation of inlet compress angle and contraction ratio could be achieved at the same time.Investigation shows that：present variable geometry inlet has higher total pressure recovery coefficient from flight Mach number 2.2 to 7.0, especially higher flow coefficient, and proper exit Mach number during most of the Mach number range.h is most important that the inlet has high mass flow during the wide flight Mach number.In addition, the regulation process is simple, dependable and easily actualized.

关 键 词：组合循环发动机 变几何进气道 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]