放大型喷嘴对航空发动机燃烧性能的影响

Effect of flux magnified injector on aero-engine combustion performance

对比研究了某型航空发动机燃烧室点火电嘴附近的放大型喷嘴流量放大比例(δ)对燃烧性能的影响,主要包括:燃烧室出口温度分布、高空点火特性和慢车贫油熄火特性。试验结果表明:随着放大型喷嘴流量放大比例的减小,燃烧室出口温度分布的均匀性提高,出口温度分布系数(OTDF)减小;燃烧室高空点火特性受放大型喷嘴流量放大比例的影响较小,可以忽略不计;燃烧室慢车贫油熄火油气比随放大型喷嘴流量放大比例的增大而变小,并且一组放大型喷嘴中流量放大比例最大的喷嘴对其影响最为显著。

The combustion performance includes the combustor exit temperature profile,the in-flight ignition performance and the idle blowout characteristics. This paper studied the effects of the magnified-scale flow by magnified injectors near the igniter plugs of an aero-engine combustor on combustion performance. The test results showed that the decrease of the magnified-scale flow was associated with better combustor exit temperature profile and lower OTDF,as well as almost nothing to the in-flight ignition performance. The test results also showed that the higher magnified-scale flow led to lower combustor idle blowout characteristics, and the largest magnified-scale flow of the magnified injectors had the most significant effect.