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

在实验和本质上研究了矩形导管中的超音速流，并在矩形管道中具有不同的矩形管道和不同的截面的组合，这是双模式撞线发动机复合材料的现实构型。引入了速度和浓度的激光测量方法，用于对流场的非冲突诊断，具有较大的分离区域。在实验研究中，将一两个H2/N2等离子火炬连接到管道中，以加热导管，以通过电气和液体组合液体组合的氢和氢的组合来加热，以使其添加到超音速空气中，并将其组合起来。观察到。发现管道的差异大大抑制了伪震波的形成和组合模式的过渡。具有各种不同角度的实验的结果表明，在差异导管中产生伪震浪所需的额外热量可以通过准中的……更维度理论来估计。当等离子火炬在恒定区域管道中产生伪震波时，连接到直管的不同导管中的另一个等离子火炬需要一定量的加热，以影响上游部分。从这个结果表明，直脉和发散管道中的分期燃料注入可能比单一注入相同的燃料的单一注入更大的推力。在数值研究中，流场的详细特征，例如，伪浪冲浪前的上游传播是由厚边界分离在厚度的厚边界层的分离和大量的duct and dever and verricmetrict and the and verricmets and verricments and verricmets and the and dermetsmets的分离。数值结果验证了对质量添加的添加加热的准理论评估，以补偿管道发散的影响。使用粒子图像速度计，我们以冲击波和涡流的流量中获得了高达550m/s的平均流量中的三维速度分布。通过丙酮平面激光诱导的荧光法，获得了整个流场中注射的定性分布以及注射端口附近的马赫数分布。这些测量技术适用于伪震浪和燃油注入的流量。较少的