| 进口条件对超燃冲压发动机氢气燃烧流场特性的影响分析 |
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| 作者姓名： | 王钰涵 王江峰 李龙飞 |
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| 作者单位： | 南京航空航天大学航空宇航学院，南京 210016 |
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| 基金项目： | 南京航空航天大学研究生创新基地(实验室)开放基金kfjj20170122 |
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| 摘 要： | 对不同进口条件下的超燃冲压发动机燃烧室内氢气喷流超声速燃烧流动特性进行了数值模拟与分析.宽范围超燃冲压发动机是吸气式高超声速飞行器推进系统设计中的热点问题之一，受实验设备硬件条件及实验技术限制，数值模拟技术仍然是超燃冲压发动机燃烧室内燃气燃烧特性及流场特性的主要研究手段.采用基于混合网格技术的多组元N-S方程有限体积方法求解器，在不同进口Mach数及压强条件下，对带楔板/凹腔结构的燃烧室模型氢气喷流燃烧流场进行了数值模拟，对比分析了氢气喷流穿透深度、喷口前后回流区结构、掺混效率及燃烧效率等流场结构与典型流场参数的变化特性及影响规律.研究成果可为宽范围超燃冲压发动机喷流燃烧流动特性分析提供参考.
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| 关 键 词： | 氢气横向喷流 超声速燃烧 超燃冲压发动机 流动特性 数值模拟 |
| 收稿时间： | 2018-04-02 |
Numerical Analysis of Hydrogen Jet Combustion Flows in Scramjet under Different Inlet Conditions |
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| Affiliation: | College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | The characteristics of hydrogen transverse jet supersonic combustion flow field of scramjet under different inlet conditions were numerically simulated and analyzed. Numerical simulation technology is the main method to study the fuel combustion and flow field structure of wide range scramjet, due to the limitation of experimental technology and equipment. Based on the hybrid mesh, the finite volume method for multi-component N-S equations solver was used to simulate the flow of hydrogen transverse jet combustion in the supersonic combustor with wedge/cavity structure, with different Mach numbers and pressures of inlet. The penetration depth of the hydrogen jet, the structure of separation around jet, the mixing efficiency and the combustion efficiency were discussed to show the change of flow field. The results can offer some references for the analysis of the jet combustion flow field in a wide range scramjet. |
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