超高温升中心分级燃烧室设计及计算分析

针对航空发动机高推重比、高温升的需求,提出1种中心分级旋流燃烧室的设计方案。在保证与现有单环腔燃烧室(SAC)进出口尺寸、机匣尺寸限制不变的情况下,对设计模型进行了3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:设计油气比为0.045时,设计中心分级燃烧室温升可达1356 K,出口温度分布可达0.137,出口径向温度分布可达0.096;此外,与SAC相比,中心分级燃烧室可获得更低的总压损失,更低的出口温度分布系数以及高工况下可获得更高的燃烧效率;污染排放性能表明,中心分级燃烧室在慢车点CO排放比SAC的稍高,在设计点NOx排放按g/kg燃油计比SAC的低。

Design and Computational Analysis of Ultra-High Temperature Rise Concentric Staged Combustor

Based on the increasing demand for high thrust-to-weight ratio and high temperature rise aircraft engines, a design method of concentric staged combustor was proposed. In ensuring the same inlet/exit size and case size with single annular combustor (SAC), threedimensional reaction flow simulation were conducted on the design model with the fluent software. Finally, the capability was compared and analyzed with the numerical simulation results and experimental results obtained from SAC. The results show that, at the design fuel/air ratio of 0.045, the temperature rise of design concentric staged combustor is 1356 K, outlet temperature is 0.137, and exit temperature distribution factor is 0.096, which can meet the design requirment of ultra-high temperature rise combustor. In addition, compared to SAC,the concentric staged combustor can obtain higher total pressure recovery coefficient, lower outlet temperature, fine profile factor, and higher combustion efficiency at high power state. Pollution emissions performance shows that CO emissions of the concentric staged combustion is slightly higher than that of the SAC at idle condition, and the NOx emissions is lower than the ones of the SAC at design condition.