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Numerical study on the induced-ramp mixed and combustion characteristics of rocket-based combined cycle engine

机译：基于火箭组合循环发动机诱导斜坡混合燃烧特性的数值研究

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In the study, the supersonic flow mechanism and mixed characteristics are discussed by changing the ramp angle and momentum flux ratio of the rocket-based combined cycle engines. The three-dimensional Reynolds-averaged Navier-Stokes equations, the shear stress transport k-omega turbulence model, and the Eddy-dissipation concept model are adopted to analyze the flow field structure. The results reveal that the oblique shock wave causes the rocket gas and parallel shear layer to slope downward, thus promoting more efficient combustion. The oblique shock wave interacts with the bottom wall boundary layer and forms a low-velocity region. The increase of the ramp angle is beneficial for jet to enter the combustion chamber. The ramp angle increases from 20 degrees to 40 degrees, and the combustion efficiency increases by about 49%. Furthermore, the increase of the momentum flux ratio is conducive to induce vortex structure, and the best penetration depth of jet fuel is obtained when the momentum flux ratio is 0.72. (c) 2021 Elsevier Masson SAS. All rights reserved.
机译：在该研究中，通过改变基于火箭的组合循环发动机的斜坡角和动量磁通比来讨论超音流机构和混合特性。采用三维雷诺平均天线，采用剪切应力传输K-Omega湍流模型和涡流概念模型来分析流场结构。结果表明，倾斜冲击波使火箭气体和平行剪切层向下倾斜，从而促进更有效的燃烧。倾斜冲击波与底壁边界层相互作用并形成低速区域。斜坡角的增加是有益的，射流进入燃烧室。斜坡角度从20度增加到40度，燃烧效率增加约49％。此外，动量磁通比的增加有利于诱导涡旋结构，并且当动量磁通比为0.72时获得最佳渗透燃料的渗透深度。 （c）2021 Elsevier Masson SAS。版权所有。

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