| 摘要: |
| 为了研究超声速燃烧室内燃料与空气快速掺混过程的流场特性，基于可压缩Navier-Stokes方程，采用大涡模拟方法和高精度WENO-TCD混合格式对来流马赫数为2.68，喷压比为36的超声速横向射流流场结构进行数值研究。数值结果清晰描述了超声速主流与横向射流相互作用过程的流场结构特征，得到了三维激波形态的演变规律以及它们在强化混合过程中的作用。另外，因桶形激波背风面低压区处的斜压效应，射流气体在桶形激波背风面形成一对螺旋向上的反向涡对，反向涡对的卷吸作用诱导进入壁面边界层的主流向上运动，形成冲击射流。冲击射流以v=557m/s的法向速度向上冲击桶形激波背风面，因而在桶形激波背风面留下类三角锥面凹痕。 |
| 关键词: 超声速横流 横向声速射流 激波 反向旋转涡对 大涡模拟 |
| DOI：10.13675/j.cnki.tjjs.210730 |
| 分类号:V211.3 |
| 基金项目:国家自然科学基金面上项目（12072162）；国家自然科学基金青年基金（2102196）；中国博士后科学基金（2021TQ0154）；江苏省自然科学基金青年基金（SBK2021041823）。 |
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| Three-Dimensional Flow Characterizes of Transverse Jet Injection into Supersonic Crossflow |
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ZHANG Huan-hao1, XIAO Yan-feng1, ZHENG Chun2, CHEN Zhi-hua1, XUE Da-wen3, ZHU Shi-quan4, SONG Wei-hong5
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1.Key Laboratory of Transient Physics,Nanjing University of Science and Technology,Nanjing 210094,China;2.School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China;3.School of Naval Architecture and Maritime,Zhejiang Ocean University,Zhoushan 316000,China;4.School of Energy and Power Engineering,Zhengzhou University of Light Industry,Zhengzhou 450001,China;5.Heilongjiang North Tool Corporation Co.,Ltd,Mudanjiang 157000,China
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| Abstract: |
| To study the flow characteristics of the rapid mixing process of fuel and air in supersonic combustion chamber， this paper is based on the compressible Navier-Stokes equation， a sonic jet injected into a Mach 2.68 crossflow over a flat plate with a jet-to-crossflow pressure ratio of 36 is investigated numerically with the use of large eddy simulation （LES） and combination of the high-order hybrid WENO-TCD schemes. Numerical results illustrate clearly the detailed flow field of the interaction between supersonic crossflow and sonic jet， the three-dimensional shape development of the shock waves and their role in strengthening the mixing process are obtained. In addition， the results also found that due to the baroclinic effect at the low-pressure area of the leeward side of the barrel shock， the jet gas forms a pair of spiral upward counter-rotating vortex pairs on the leeward side of the barrel shock. The entrainment of the counter-rotating vortex pairs guides the mainstream entering the wall boundary layer upward to form an impact jet， and impacts the leeward side of the barrel shock at a normal velocity of v=557m/s. Therefore， a triangular concave indentation is left on the leeward side of the barrel shock wave. |
| Key words: Supersonic crossflow Transverse sonic jet Shock wave Counter-rotating vortex pair Large eddy simulation |
