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首页> 外文期刊>International Journal of Heat and Mass Transfer >Study on main flow and fuel injector configurations for Scramjet applications
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Study on main flow and fuel injector configurations for Scramjet applications

机译：研究Scramjet应用中的主流和喷油嘴配置

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摘要

A parametric study of combustor inlet configuration for supersonic combustion ramjet (Scramjet) engine has been conducted by solving two-dimensional full Navier-Stokes equations. The main stream is air of Mach 5 entering through the configured inlet of the combustor and gaseous hydrogen is injected from the configured jet on the side wall. The parameters included are air stream angle and injection angle. On the effect of air stream angle, strong interaction between main and injecting flows can be observed for smaller angle causing sharp increase in mixing efficiency on the top of injector. Also high momentum of air stream towards the side wall causes no recirculation at the upstream of injector and the system becomes unable for flame holding. For the variation of injection angle, results show that in upstream of injector the mixing is dominated by recirculation and in downstream the mixing is dominated by mass concentration of hydrogen. Upstream recirculation is dominant for injecting angle 60° and 90°. Incorporating the various effects, perpendicular injection shows the maximum mixing efficiency and its large upstream recirculation region has a good flame holding capability.
机译：通过求解二维完整的Navier-Stokes方程，对超音速冲压冲压发动机（Scramjet）的燃烧器进气口配置进行了参数研究。主流是通过燃烧器的配置入口进入的马赫数5的空气，并且从配置在侧壁上的射流注入气态氢。包括的参数是气流角和喷射角。在气流角度的影响下，对于较小的角度，可以观察到主流与喷射流之间的强烈相互作用，从而导致喷射器顶部的混合效率急剧增加。而且，朝向侧壁的空气流的高动量导致在喷射器的上游没有再循环，并且系统变得不能保持火焰。对于喷射角的变化，结果表明，在喷射器的上游，混合主要由再循环控制，而在下游，混合主要由氢气的质量浓度控制。上游再循环对于喷射角为60°和90°来说是主要的。结合各种效果，垂直喷射显示出最大的混合效率，并且其较大的上游再循环区域具有良好的火焰保持能力。

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