| 摘要: |
| 为了获得气氧/甲烷与气氢/气氧两种推进剂组合燃烧特性的异同,将氢/氧气-气喷注器的设计经验用于气氧/甲烷气-气喷注器设计,在同一燃烧室中针对气氧/甲烷与气氢/气氧同轴剪切喷注器燃烧特性开展了数值仿真与试验研究。结果表明:在喷注器设计参数相似的情况下,气氧/甲烷喷注器尺寸与气氢/气氧喷注器尺寸相当；在相同的燃烧室设计压力、结构尺寸,以及两种推进剂组合均完全燃烧的情况下,要产生相同的推力,气氧/甲烷(混合比3.5)推进剂流量约为氢/氧(混合比6.0)推进剂流量的1.27倍, 气氧/甲烷燃烧所需燃烧室特征长度约为氢/氧燃烧室特征长度的1.48倍,气氧/甲烷燃烧室壁面热载约为氢/氧燃烧室壁面热载的一半。 |
| 关键词: 气氧/甲烷 气氢/气氧 喷注器 特征长度 热载荷 |
| DOI： |
| 分类号: |
| 基金项目:国家“八六三”高技术资助项目。 |
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| Comparison of Combustion Characteristics for GO2/CH4and GH2/GO2Injectors |
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GAO Yu-shan1,2,JIN Ping1,CAI Guo-biao1
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(1.College of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;2. Xi’an Aerospace Propulsion Institute, Xi’an 710100, China)
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| Abstract: |
| In order to obtain the differences and connections of the GO2/CH4and GH2/GO2combustion characteristics, to provide experience of the GH2/GO2injector for guiding GO2/CH4injector design, comparison of GO2/CH4and GH2/GO2combustion characteristics for shear-coaxial injectors was conducted in the same combustion chamber by numerical simulation and experiment. The results show that under the similar design parameters, the size of GO2/CH4injector is almost equal to that of GH2/GO2injector. On condition that the pressure at design point and dimensions are the same,in order to produce the same thrust, the mass flow rate of GO2/CH4(mixture ratio 3.5)is about 1.27times as GH2/GO2(mixture ratio 6.0). Furthermore, combustion characteristic length of GO2/CH4 is approximately 1.48times as much as GH2/GO2combustion chamber, and the thermal load of the GO2/CH4combustion chamber is about half of the GH2/GO2combustion chamber. |
| Key words: GO2/CH4 GH2/GO2 Injector Characteristic length Thermal load |
