| JF12激波风洞高Mach数超燃冲压发动机实验研究 |
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| 作者姓名： | 姚轩宇 王春 喻江 苑朝凯 姜宗林 司徒明 |
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| 作者单位： | 1.中国航空发动机研究院，北京 101304 |
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| 基金项目： | 国家自然科学基金11532014 |
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| 摘 要： | 针对高Mach数（Ma ≥ 7）超燃冲压发动机高气动阻力下的燃烧组织问题，提出一种双突扩燃烧室结构方案.使用数值模拟方法考察了射流与双突扩燃烧室组合方式的混合燃烧特性.设计了双突扩超燃冲压发动机模型，在力学研究所JF12长试验时间激波风洞内，开展了Ma=7.0和Ma=9.5的氢燃料点火和燃烧试验对比.在风洞有效试验时间100 ms内，实现了Ma=7.0和Ma=9.5超燃冲压发动机的成功点火与稳定燃烧.在Ma=7.0情况下，进气道采用三维压缩，燃烧室入口设计Mach数Mac=2.5，壁面压力分布实验结果显示燃烧放热靠近燃烧室扩张段上游；在Ma=9.5情况下，进气道采用二维压缩，燃烧室入口设计Mach数Mac=3.5，由于燃烧室流动速度特别高，燃烧放热靠近燃烧室扩张段下游.
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| 关 键 词： | 超燃冲压发动机 高Mach数 激波风洞 纯净空气 JF12风洞 |
| 收稿时间： | 2019-07-08 |
High-Mach-Number Scramjet Engine Tests in JF12 Shock Tunnel |
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| Affiliation: | 1.Aero Engine Academy of China, Beijing 101304, China2.SKL of High-Temperature Gasdynamics, Institute of Mechanics, CAS, Beijing 100190, China3.Beijing Power Machinery Research Institute, Beijing 100074, China |
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| Abstract: | A schematic configuration of dual-step supersonic combustor was proposed to overcome the high gasdynamic drag of scramjet engine in high-Mach-number flight (Ma ≥ 7). Numerical simulations were conducted to evaluate the coupled mixing and combustion features of fuel jet and dual-step flowfield. A scramjet model with dual-step was designed and tested in the JF12 Shock Tunnel, which can provide the pure air medium for simulating high-Mach-number scramjet tests. During the 100 ms test duration of JF12 Shock Tunnel, successful ignition and stable combustion of hydrogen-fueled scramjet models were realized in both simulation conditions of Ma=7.0 and Ma=9.5 and the experimental results were compared. In the simulation condition of Mach 7, three-dimensional inlet was used and the entrance Mach number of supersonic chamber was about Mac=2.5. The wall pressure distributions showed that the combustion took place in the upstream of expansion section of duct. In the simulation condition of Mach 9.5, two-dimensional inlet was used and the entrance Mach number of supersonic chamber was about Mac=3.5. The combustion took place near the exit of inner duct of scramjet model. |
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