| 乙烯燃料超燃冲压发动机燃烧过程研究 |
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| 引用本文： | 钟富宇,乐嘉陵,田野,岳茂雄.乙烯燃料超燃冲压发动机燃烧过程研究[J].实验流体力学,2021,35(1):34-43. |
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| 作者姓名： | 钟富宇 乐嘉陵 田野 岳茂雄 |
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| 作者单位： | 中国空气动力研究与发展中心 高超声速冲压发动机技术重点实验室, 四川 绵阳 621000 |
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| 基金项目： | 国家自然科学基金青年基金51706237博士后基金面上项目2019M653953 |
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| 摘 要： | 在来流马赫数2.0的直连式燃烧设备上，研究了氢气引燃条件下带凹腔的超燃冲压发动机燃烧室内，从氢点火到氢与乙烯混合燃烧，再到乙烯单独燃烧的全过程的燃烧流动特性，通过纹影、火焰自发光、CH自发光以及OH-PLIF等手段瞬时同步研究了流场结构和火焰发展。先锋氢与乙烯的当量比分别约为0.33和0.10。整个燃烧过程分6个阶段，第一阶段为先锋氢注入之前的无反应流动，试验测定振荡频率约为400 Hz。第二阶段用于揭示先锋氢被点燃之前的流动特性，由于先锋氢的注入而产生的激波在下壁面反射并与凹腔内的激波相互作用，导致监测点压力增大。第三阶段描述了先锋氢的燃烧过程，从点火、火焰稳定直到壁面压力稳定，历时约26.0 ms。在0.1 ms内先锋氢点火对燃烧流场及流动结构产生重大影响，试验测量先锋氢燃烧产生的激波串的运动速度约为20 m/s，先锋氢稳焰模式为凹腔回流区稳定燃烧。第四阶段为氢气和乙烯混合燃烧，此阶段燃烧变得更加剧烈，激波串被推入隔离段内，以至于超出了观测范围，该阶段乙烯稳焰模式为剪切层稳定燃烧。第五阶段为乙烯的燃烧流动，当先锋氢停止喷注后，乙烯火焰在凹腔内的位置由上游向下游移动。最后一个阶段是乙烯单独燃烧直到火焰熄灭。初步分析表明，乙烯燃烧的CH自发光图片能定性研究其燃烧效率。
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| 关 键 词： | 超燃冲压发动机 乙烯 点火 稳焰 燃烧特性 |
| 收稿时间： | 2020-08-02 |
Investigation of the combustion process in an ethylene-fueled scramjet combustor |
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| Affiliation: | Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China |
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| Abstract: | An experimental investigation was conducted in a direct-connect supersonic combustion facility simulating the inflow condition of Ma=2.0 to investigate the combustion process in an ethylene-fueled scramjet combustor with cavity and pilot hydrogen. The structure of the flow field and the flame development were visualized using the schlieren imaging, the flame luminosity imaging, the CH luminosity imaging and the planar laser-induced fluorescence (PLIF) of the OH radical. The equivalence ratios of pilot hydrogen and ethylene were about 0.33 and 0.10, respectively. The whole combustion process could be divided into six stages. In the first stage, there was a non-reaction cold flow before the hydrogen injection. And the frequency of oscillation was measured to be around 400 Hz, experimentally. In the second stage, the flow characteristics before the pilot hydrogen ignition were revealed, due to the hydrogen injection an oblique shock wave was generated, reflected on the bottom wall, and then interacted with the shock waves below the cavity, thus leading to the increase of the monitor pressure. The third stage was the hydrogen combustion, including ignition and flame stabilization. The process from the ignition of pilot hydrogen to the combustion stabilization lasted around 26.0 ms. In the first 0.1 ms, the ignition of pilot hydrogen had great effect on the flow field structures. The moving speed of the shock train caused by the combustion of pilot hydrogen was around 20 m/s. The stabilization mode of the pilot hydrogen flame was cavity recirculation stabilized combustion. The fourth stage was the intense combustion process of hydrogen and ethylene. The shock waves were pushed into the isolator, and thus exceeded the observation range. The ethylene flame stabilization mode was shear layer stabilized combustion. The combustion characteristics of ethylene were revealed in the fifth stage. When the pilot hydrogen was ceased, the ethylene flame moved from the cavity step to the cavity ramp. The last stage involved the combustion and flame blowout of pure ethylene. Preliminary analysis indicates that the CH luminosity images of ethylene combustion can be used to investigate combustion efficiency qualitatively. |
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