| 摘要: |
| 固体火箭燃气超燃冲压发动机具有高比冲、结构简单、流量易调节等优点，然而在超声速空气流的燃烧室中，如何让燃料更好地与空气掺混，增加颗粒停留时间，在较短时间内释放出更多的燃烧焓成为目前研究的重点。提出了一种基于中心支板燃气喷注的含硼固体火箭超燃冲压发动机方案，开展了模拟马赫数6.0、高度25 km来流条件下的地面直连试验和数值仿真研究，验证了该方案的合理性和优势，并获取了燃烧室内的燃烧特性，探寻了固体燃气喷注方式对燃烧室性能的影响规律。结果显示，相比于中心支板喷注方案，侧壁喷注存在总压损失大、反压激波串长度大、进气要求严苛等问题，但能够增强掺混，提高燃烧效率,缩短燃烧所需距离；而在中心支板式固体冲压发动机中，在燃烧室侧壁面引入较小流量的一次燃气，可以增大固体颗粒在燃烧室内的穿透深度，提高燃烧效率和燃烧室性能。 |
| 关键词: 两相燃烧 固体冲压发动机 直连试验 数值仿真 |
| DOI： |
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| 基金项目: |
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| Influence of Gas Injection Conditions on Combustion Performance of Central Strut Solid Ramjet |
| ZENG Jia,WANG Guohui,HUANG Hui,FAN Jian,ZHU Pingping |
| (China Academy of Launch Vehicle Technology，Beijing 100076，China;Beijing Institute ofAstronautical Systems Engineering，Beijing 100076，China) |
| Abstract: |
| The solid rocket gas scramjet has the advantages of high specific impulse, simple structure, easy flow adjustment, etc. However, in the afterburning chamber with supersonic air flow, how to make the fuel better mixed with air, increase the particle residence time, and release more combustion enthalpy in a shorter time has become the focus of current research. This article proposes a boron based solid ramjet scheme based on central strut injection, and conducts ground direct-connect test and numerical simulations under inflow conditions at mach 6.0 and altitude of 25 kilometers to verify the feasibility and performance of this scheme, obtains the combustion characteristics of the combustion chamber, and explores the influence of solid gas injection mode on the performance of the combustion chamber. The results show that compared to the central strut injection scheme, the side injection has problems such as large total pressure loss, long back pressure shock wave string and strict intake requirements. However, it can enhance mixing, improve combustion efficiency, and shorten the required distance for combustion. By introducing small flow of primary gas from the side wall of the central strut injection combustion chamber, the Penetration depth of solid particles can be increased，and the combustion efficiency and performance of the combustion chamber can be improved. |
| Key words: Two phase combustion Solid ramjet Direct-connect test Numerical simulation |