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针对高推质比航空发动机高温升燃烧室的需求,提出一种中心分级燃烧室的设计方案,在保证与现有单环腔燃烧室扩压器尺寸、外机匣最大直径及燃烧室出口尺寸相同的情况下,对设计模型进行了三维数值模拟,并与现有的单环腔燃烧室数值模拟结果及试验结果进行了对比分析.研究结果表明:采用中心分级燃烧室,在获得更高温升的同时,可获得比单环腔燃烧室更高的总压恢复系数和比单环腔燃烧室更低的燃烧室出口温度分布系数(OTDF),其慢车工况下的CO排放和NO排放略高于单环腔燃烧室;在设计总油气比为0.045的情况下,温升可达1360K,总压恢复系数大于等于0.96,OTDF小于等于0.14,出口径向温度分布系数(RTDF)小于等于0.10,燃烧效率大于等于0.987.
In order to meet the demand of high-temperature-to-high ratio aeroengine high temperature rise combustion chamber, a design scheme of center staged combustion chamber is put forward. In order to ensure the size of diffuser, the maximum diameter of outer casing and the exit of combustion chamber In the same situation, the three-dimensional numerical simulation of the design model was carried out and compared with the existing single-ring cavity combustion chamber numerical simulation results and the experimental results.The results show that: the use of central staged combustion chamber, access to higher temperature rise , The total pressure recovery coefficient and the lower combustor outlet temperature distribution coefficient (OTDF) of single-chamber combustor are obtained, and the CO and NO emissions of the combustor in the idle condition are slightly lower Higher than that of the single-ring cavity combustion chamber; at a designed total oil-gas ratio of 0.045, the temperature rise can reach 1360K, the total pressure recovery coefficient is greater than or equal to 0.96, the OTDF is less than or equal to 0.14 and the exit radial temperature distribution coefficient (RTDF) is less than or equal to 0.10 , The combustion efficiency is greater than or equal to 0.987.