Abstract: To analyze the effects of injection design on chamber combustion efficiency,design, numerical simulation and testing were performed on the 2kN GH₂/GO_2vortex-cooled chamber. Three H_2injection plates with different distribution diameters were designed, and parameters, such as thrust, gas temperature near to the chamber wall, and chamber pressure, etc. were measured during the test. By utilizing thermodynamic calculation, CFD analysis and testing,efforts were made to analyze the chamber combustion efficiency. Results show that among the three analyzed injection plates, the chamber combustion efficiency reaches the highest of 97.6% when the injector distribution diameter is the largest. Hot-fire test on transparent chamber was also performed. Visualization of the combusting flow field indicates that flame is confined within the 59.5% radius inner region of the chamber. According to calculating results, the combustion efficiency is affected by the combustion region, which is impacted by the H_2injector distribution diameter.  

Key words: Liquid rocket engine; Vortex-cooled thrust chamber; Hot-fire test; Combustion efficiency

摘要： 为了分析喷注器对涡流冷却推力室燃烧效率的影响,开展了2kN气氢/气氧涡流冷却推力室的设计、仿真与试验研究,设计加工了三种不同喷嘴分布直径的氢喷注面板,在试验过程中测量了推力、燃烧室圆筒段内壁面温度、内壁面压力等参数,利用热力计算、流场仿真与试验测量结果对涡流冷却推力室燃烧效率进行了分析。结果表明,在所分析的三种喷注面板中,喷嘴分布半径最大的推力室燃烧效率最高,为97.6%。同时开展了透明燃烧室的试验研究,高温火焰在燃烧室圆筒段59.5％半径以内区域,验证了内外涡流结构的存在。仿真结果表明,氢喷嘴分布直径影响燃烧区域的分布,从而影响燃烧效率。 

关键词: 液体火箭发动机;涡流冷却推力室;热试车;燃烧效率 