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Research of Combustion Control in Dual-Mode Ramjet Combustor with Staged Fuel Injection

双模态冲压发动机分级喷油燃烧控制研究

基本信息

批准号：
15206090
负责人：
MASUYA Goro
金额：
$ 17.22万
依托单位：
Tohoku University
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (A)
财政年份：
2003
资助国家：
日本
起止时间：
2003 至 2005
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-15206090/
关键词：
scramjet dual-mode combustion pseudo-shock wave mixing diverging duct

项目摘要

Supersonic flow with heat addition and combustion in rectangular ducts with diverging section, which are realistic configuration for the combustor of dual-mode ramjet engines, was investigated experimentally and numerically. Laser measurement methods of velocity and concentration were introduced for non-intrusive diagnostics of the flowfields with large separated regions.In the experimental study, one or two H2/N2 plasma torches were attached to the duct for heat addition to the supersonic airstream by electrical discharge and combustion of hydrogen in the feedstock of the torch, and formation of pseudo-shock wave and transition of combustion mode were observed. It was found that the divergence of the duct considerably suppress the formation of pseudo-shock waves and the transition of combustion mode. Results of experiments with various diverging angles indicated that the additional heat required to produce the pseudo-shock wave in the diverging duct could be estimated by the quasi-one … More dimensional theory. When the pseudo-shock wave was produced by the plasma torch in the constant area duct, another plasma torch in the diverging duct connected to the straight duct required certain amount of heat addition to affect the upstream section. From this result, it was shown that the staged fuel injection in the straight and diverging ducts could deliver more thrust than the single injection of the same total amount of fuel.In the numerical study, detailed features of the flowfield, such as the upstream propagation of the pseudo-shock wave front led by separation of thick boundary layer at the corner of the rectangular duct, and significant asymmetric separation in the diverging duct, were obtained. Numerical results validated the quasi-one dimensional theoretical evaluation of the heat addition required to compensate the influence of duct diverging.Using the particle image velocimetry, we obtained averaged three-dimensional velocity distributions in the flow up to 550m/s with shock waves and vortices. By the acetone planar laser induced fluorescence method, qualitative distribution of injectant in the whole flow field as well as the Mach number distribution near the injection port were obtained. These measurement techniques are applicable to the flow with the pseudo-shock wave and fuel injection. Less

对双模态冲压发动机燃烧室的实际构型--扩张段矩形通道内的超声速加热流动和燃烧过程进行了实验和数值研究。采用激光测速和浓度测量方法对大分离区流场进行了非侵入式诊断，实验中在管道上安装了一个或两个H_2/N_2等离子体炬，通过放电和氢气燃烧对超音速气流进行加热，观察到了伪激波的形成和燃烧模式的转变。结果表明，通道的扩张对伪激波的形成和燃烧模式的转变有明显的抑制作用。不同扩张角的实验结果表明，扩张通道中产生伪激波所需的附加热量可以用准1来估算 ...更多信息维度理论当等离子体炬在等面积管道中产生伪冲击波时，连接到直管道的发散管道中的另一个等离子体炬需要一定量的热量来影响上游部分。计算结果表明，在相同燃料量的情况下，在直通道和扩张通道中进行燃料分级喷射比单次喷射能够提供更大的推力，并详细分析了矩形通道拐角处厚边界层分离导致的拟激波阵面向上游传播、和显著的不对称分离。数值计算结果验证了准一维理论计算结果的正确性，并利用粒子图像测速技术得到了最大速度为550 m/s的有激波和涡的三维平均速度分布。采用丙酮平面激光诱导荧光法，定性地得到了喷注物在整个流场中的分布以及喷注口附近的马赫数分布。这些测量技术适用于有拟激波和燃油喷射的流动。少