基于正交试验的超燃燃烧室小肋片数值优化  

Numerical Optimization of Pylon Size in Supersonic Combustor Based on Orthogonal Experiment

作　　者：黄桂彬 吴达[1] 王应洋 夏雪峰[1] 

机构地区：[1]空军工程大学防空反导学院,西安710051

出　　处：《空军工程大学学报（自然科学版）》2017年第5期13-18,共6页Journal of Air Force Engineering University(Natural Science Edition)

摘　　要：为研究超燃燃烧室中小肋片长、宽、高对流场特性的影响及参数择优问题,采取正交试验设计方法对其进行了数值模拟。对比分析25种不同小肋片参数组合情况下其燃料与空气的混合效率、总压损失、穿透深度之间的差异。研究表明,小肋片高度对燃料和空气的混合效率影响程度最显著,其次是宽度和长度;长宽高对超燃燃烧室中总压损失、穿透深度影响程度不显著。经过优化后的小肋片燃料和空气的混合效率(0.712 439)高于正交试验里的所有结果,其总压损失(0.130 3)通过损失2%的总压换取了燃料与空气的混合效率37%的增强,其穿透深度(10.023)通过损失1%的穿透深度换取了燃料与空气的混合效率9%的增强,为小肋片的设计和改进提供了方法借鉴和参考依据。In order to analyze the influence of pylon＇s length, width, height to flow characteristics in the supersonic combustion, orthogonal experimental design method has been carried out to design different combinations of pylon size. By numerical simulation, the differences between different examples~ mixing efficiency, total pressure loss ratio, penetration depth has been contrastive analyzed. By intuitive method and ANOVA, it shows that height is the greatest influence on mixing efficiency, then the width, length is the worst. The size of pylon dose not have significant association with total pressure loss and penetration depth. The mixing efficiency of The optimized case（0. 712439） is higher than any cases of this paper, and its total pressure loss（0. 1303） lose 2% for improving 37% mixing, and penetration depth（10. 023） lose 1% for improving 9 % mixing. This paper provides a method reference for the designing and improvement of pylon.

关 键 词：超燃燃烧室 小肋片 尺寸参数 数值优化 正交试验 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]