基于中心分级的高温升燃烧室性能预估

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.

Capability prediction of high temperature rise center-staged combustor

Based on the increasing demand for high temperature rise combustor of high thrust-mass-ratio aeroengine, a design method of center-staged combustor was given and three-dimensional numerical simulation was conducted on the design model using the same diffuser, outer case and exit dimensions of single annular combustor. The capability of center-staged combustor was compared and analyzed with the numerical simulation results and experimental results obtained from single annular combustor. The results show that, by using the center-staged combustor, the total pressure recovery coefficient can be improved compared with the single annular combustor, and the outlet temperature distribution factor (OTDF) of the combustor is lower than that of single annular combustor in addition to higher temperature rise, but the CO and NO emissions are higher than that of single annular combustor in slow train state. At the designed 0.045 fuel/air ratio state, the temperature rise can reach 1360K, and the total pressure recovery coefficient is no less than 0.96; OTDF can be no more than 0.14; the radial temperature distribution factor (RTDF) at outlet can be no more than 0.10, with the combustion efficiency no less than 0.987.