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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。
In order to analyze the influence of injector on the combustion efficiency of vortex cooling thrust chamber, the design, simulation and experimental study of 2kN gas-hydrogen / oxygen-oxygen vortex cooling thrust chamber were carried out. Three kinds of hydrogen injection panels with different nozzle distribution diameters were designed and processed, Thrust, temperature of the inner wall of the cylinder chamber, inner wall pressure were measured during the test. The combustion efficiency of the thrust chamber was analyzed by thermodynamic calculation, flow field simulation and experimental measurement results. The results show that among the three injection panels analyzed, the thrust chamber with the largest nozzle distribution has the highest combustion efficiency of 97.6%. At the same time, the experimental research of transparent combustion chamber was carried out. The high-temperature flame in the area of 59.5% of the cylindrical section of the combustion chamber verified the existence of internal and external vortex structures. The simulation results show that the distribution diameter of hydrogen nozzle affects the distribution of combustion area, thus affecting the combustion efficiency.