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保持单环腔主燃烧室的扩压器,外机匣最大直径尺寸以及喷口不变的前提下,将其火焰筒结构重新设计为并联式双环腔结构,设计了6种不同旋流器组合的双环腔结构燃烧室.采用相同的物理模型(包括湍流模型、辐射模型、喷雾模型及污染排放模型等),对单、双环腔主燃烧室分别进行全流程的三维计算.给出了燃烧室的总压恢复系数、燃烧效率、燃烧室出口温度分布系数、污染排放指标等燃烧室性能参数.对比分析了单、双环腔燃烧室的计算结果.结果表明,双环腔燃烧室置换单环腔燃烧室是可行的,该研究可为大飞机低污染大法动机的设计提供技术支持.
Maintaining single-chamber main chamber diffuser, outer casing maximum diameter size and the premise of the nozzle unchanged, the flame tube structure redesigned as parallel double-ring cavity structure, the design of a combination of six different cyclone Double-chamber cavity combustion chamber.The three-dimensional calculation of the whole process of single-chamber and double-chamber cavity main combustion chambers are carried out by the same physical model (including turbulence model, radiation model, spray model and pollution emission model) The total pressure recovery coefficient, the combustion efficiency, the temperature distribution coefficient of the outlet of the combustion chamber and the pollution emission index were calculated and compared.The results of calculation of single and double ring cavity combustion chambers were compared and analyzed.The results showed that the double ring chamber replaced the single ring chamber It is feasible that the study will provide technical support for the design of large aircraft with low pollution Dafa motivation.