Study on the high speed scramjet characteristics at Mach 10 to 15 flight condition
Study on the high speed scramjet characteristics at Mach 10 to 15 flight condition
复制标题
10~15马赫飞行条件下高速超燃冲压发动机特性研究
DOI：
10.1007/978-3-540-27009-6_142
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发表时间：
2005
期刊：
影响因子：
--
通讯作者：
S. Ueda
中科院分区：
文献类型：
--
作者：
Masahiro Takahashi;K. Itoh;H. Tanno;T. Komuro;Tsunami;Kazuo Sato;S. Ueda
一台超燃冲压发动机模型在大型自由活塞激波风洞中进行了试验，该模型旨在建立与马赫数12飞行相对应的自由流动条件下的稳定和强燃烧。原发动机模型的燃烧试验表明，燃烧室中获得的燃烧放热不足以维持强烈的燃烧。对于一种新的超燃冲压发动机模型，增加了进气压缩比以提高燃烧室入口处的静态温度和流动密度。由于气动设计的改变，燃烧产生的压力升高，燃烧室内强燃烧条件的持续时间延长。新发动机模型采用了超混合器喷油器，旨在通过引入流向涡来增强混合和燃烧。结果表明，超混合器喷油器能有效地促进燃烧放热，建立燃烧室内稳定、强烈的燃烧。
A scramjet engine model, designed to establish steady and strong combustion at free-stream conditions corresponding to Mach 12 flight, was tested in a large free-piston driven shock tunnel. Combustion tests of a previous engine model showed that combustion heat release obtained in the combustor was not sufficient to maintain strong combustion. For a new scramjet engine model, the inlet compression ratio was increased to raise the static temperature and density of the flow at the combustor entrance. As a result of the aerodynamic design change, the pressure rise due to combustion increased and the duration of strong combustion conditions in the combustor was extended. A hyper-mixer injector designed to enhance mixing and combustion by introducing streamwise vortices was applied to the new engine model. The results showed that the hyper mixer injector was very effective in promoting combustion heat release and establishing steady and strong combustion in the combustor.