摘要
本文在二元试验燃烧室上,对四种掺混孔设计方案作了燃烧室出口径向平均温度分布的试验研究。试验时燃烧室进口不加温,温升范围280°～570℃,燃烧室出口为常压。试验结果表明:不同掺混孔设计方案,对燃烧室出口平均径向温度分布的影响是有规律可循的。本文同时建立了预估燃气涡输发动机主燃烧室出口平均径向温度分布的半经验半分析模型。该模型能够由第一次试验得到的出口温度分布,推算出燃烧室掺混区设计修改后或工作状态改变后,燃烧室出口平均径向温度分布曲线的变化。模型计算结果和从二元试验燃烧室出口测得的平均径向温度分布非常吻合,为调试燃烧室出口平均径向温度分布提供了定量的设计工具。
On a two dimensional experimental combustor exit radial temperature profiles formed by four configurations of dilution hole design have been studied experimentally.The inlet air is of room temperatire,and the combustor temperature rise ranges from 280℃to 570℃,and the combustor pressure is atmospheric pressure.From the experimental results the effect of different configurations of dilution hole desion on combustor exit radial temperature profiles showe 1 certain regularity.In the present study,a semi-empirical & semi-analytical model has been developed for predicting the exit radial temperature profiles from gas turbine combustors.The model can predict the effect of change in dilution zone design or combustor operating conditions on the change of combustor exit radial temperature profiles based on exit temperature measurement before the change.The predictions have been compared with the measured exit radial temperature profiles,the comparison showed excellent agreement.The model provides a quantitative design tool for the adjustment of temperature profile of gas turbine combustor.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1989年第1期51-61,共11页
Journal of Beijing University of Aeronautics and Astronautics
关键词
燃烧室
出口温度
径向分布
combustor,exit temperature,radial distribution,dilution mixing,jet mixing.
