进气畸变对某航空发动机燃烧室出口温度场的影响

徐兵; 李前翔; 刘新生; 孟坤; 李朋玉

doi:10.3969/j.issn.2095-1248.2023.05.001

沈阳航空航天大学学报 ›› 2023, Vol. 40 ›› Issue (5) : 1 -8. DOI: 10.3969/j.issn.2095-1248.2023.05.001

航空宇航工程

进气畸变对某航空发动机燃烧室出口温度场的影响

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Effect of inlet distortion on the temperature field at the outlet of an aero-engine combustor

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摘要

为了研究进气畸变对某燃烧室出口温度场性能的影响，根据压气机部件试验出口压力分布设计了畸变板，将其加装到燃烧室前开展部件试验，并使用火焰面生成流形模型（flamelet generated manifolds，FGM）进行均匀流进气、畸变进气的燃烧仿真，分析畸变引起变化的原因。结果表明：燃烧室进气畸变会带来扩压器后的三股流分配变化，使得火焰筒头部进气量减少和掺混孔后燃气掺混效果下降，最终导致燃烧室出口温度分布系数（overal temperature distribition factor，OTDF）和径向温度分布系数（radial temperature distribition factor，RTDF）变差。

Abstract

In order to study the effect of inlet distortion on the temperature field performance at the outlet of an aero-engine combustor，a distortion plate was designed and installed in front of the combustor for component testing based on the outlet pressure distribution of compressor components testing.The combustion simulation of uniform flow intake and distorted intake was carried out using the flamelet generated manifolds （FGM） model，and the reasons for the changes caused by the distortion were analyzed.The results show that the inlet distortion of the combustor will cause changes in the three-stream distribution behind the diffuser，which will reduce the inlet volume at the flame tube head and the gas mixing effect after the mixed hole and ultimately lead to a deterioration in the OTDF and RTDF at the combustor outlet.