摘要
研制基于超声速燃烧的高效吸气式推进装置(运行Mach数在3.5以上)需要寻求改善混合效率的有效机制,这对于采用常规碳氢燃料(特别是可以增加密度的液体燃料)的装置尤为重要.延长混合时间的一种途径是在飞行器燃料室的上游喷入部分燃料.壁面喷射一直是超声速气动力学最具挑战性的课题,这里包括使比冲损失最小、改善燃料-空气的混合、减少入口段/燃烧室的相互作用以及增进火焰稳定性等.综述了超声速入口段或燃烧室的隔离器中液体燃料(个别情况下为气体燃料)喷射的研究进展.在这些研究中,燃料都是从后掠型细支架尾迹中的壁面处喷射出来的,动压比很低(q_(jet)/q_(air)=0.6～1.5).它们涉及入口段和燃烧室的隔离器中单个支架/喷射器的几何结构及其组合方式、各种各样的喷射条件、不同的引射剂,并且评估了这些因素对于燃料羽流喷散、比冲损失以及混合效率的影响.述评引用了46篇参考文献.
Developing an efficient, supersonic combustion-based, air breathing propulsion cycle operating above Mach 3.5, especially when conventional hydrocarbon fuels are sought and particularly when liquid fuels are preferred to increase density, requires mostly effective mechanisms to improve mixing efficiency. One way to extend the time available for mixing is to inject part of the fuel upstream of the vehicle＇s combustion chamber Injection from the wall remains one of the most challenging problems in supersonic aerodynamics, including the requirement to minimize impulse losses, improve fuel-air mixing, reduce inlet/combustor interactions, and promote flame stability. This article presents a review of studies involving liquid and, in selected cases, gaseous fuel injected in supersonic inlets or in combustor＇s insulators. In all these studies, the fuel was injected from a wall in a wake of thin swept pylons at low dynamic pressure ratios （qjet/qair =0.6-1.5）, including individual pylon/injector geometries and combinations in the inlet and combustor＇s isolator, a variety of injection conditions, different injectants, and evaluated their effects on fuel plume spray, impulse losses, and mixing efficiency. This review article cites 46 references.
出处
《力学进展》
EI
CSCD
北大核心
2009年第2期236-248,共13页
Advances in Mechanics
关键词
流体力学
混合
射流穿透
fluid mechanics, mixing, jet penetration
