A mechanism of combustion mode transition for hydrogen fueled scramjet
A mechanism of combustion mode transition for hydrogen fueled scramjet
复制标题
氢燃料超燃冲压发动机燃烧模式转变机理
DOI：
10.1016/j.ijhydene.2014.04.090
复制
发表时间：
2014
影响因子：
7.2
通讯作者：
Deng Jun
中科院分区：
文献类型：
--
作者：
Yang Qingchun;Chang Juntao;Bao Wen;Deng Jun
在氢燃料超燃冲压发动机的真实的飞行过程中，燃烧模式的转换会反复发生。在无粘流动的假设下，建立了一系列的方程，以解析的方式识别燃烧模式的转变。分别研究了加热和加速诱导模跃迁的过程。本文提出了一种解析解，以了解冲压发动机-超燃冲压发动机工作模式之间的过渡条件。此外，本文还从物理的角度对模式转换过程作了定性的解释。模式转变与热阻塞效应和激波运动密切相关。模式转换过程是不连续的，而且非常快。在此过程中，燃烧室入口马赫数发生突变。
The combustion mode transition will occur repeatedly during the real flight of a hydrogen fueled scramjet. Under the assumption of inviscid flow, a series of the equations have been developed to identify combustion mode transition in an analytical way. The processes of heating and accelerating induced mode transition are investigated, respectively. This paper presents an analytical solution to understand the conditions for the transition between ramjet-scramjet operation modes. Besides, this paper also presents a qualitative explanation of the mode transition processes in the physical point of view. The mode transition is closely related to the thermal choking effects and shock wave motion. The process of mode transition is discontinuous and very fast. There is a sudden change with the combustor entry Mach number in this process.