文献类型：期刊文献

中文题名：离心喷嘴喷雾特性对燃烧室火焰结构影响的测量分析

英文题名：Effect of Pressure-Swirl Atomizer Atomizing Characteristics on Flame Structure in Combustor

作者：陈坚 董清清 薛九天

第一作者：陈坚

机构：[1]贵州理工学院航空航天工程学院,贵阳550003;[2]贵州省高等学校航空发动机热管理与智能制造重点实验室,贵阳550003

第一机构：贵州理工学院航空航天工程学院

年份：2025

卷号：51

期号：3

起止页码：103-108

中文期刊名：航空发动机

外文期刊名：Aeroengine

收录：;北大核心:【北大核心2023】；

基金：国家自然科学基金(52166006);贵州省科学技术基金(黔科合基础-ZK[2021]一般279)资助。

语种：中文

中文关键词：离心喷嘴;喷雾锥角;索太尔平均直径;火焰结构;液态燃料;航空发动机

外文关键词：pressure-swirl atomizer;spray angle;Sauter mean diameter;flame structure;liquid fuel;aeroengine

摘要：航空发动机燃烧室多使用液态燃料,而液态燃料的燃烧过程通常伴随着雾化、蒸发及掺混的过程。在这个过程中,燃油的雾化质量将直接影响蒸发及掺混的效果,从而对燃烧室燃烧、点火及排放性能产生直接的影响。为了研究离心喷嘴喷雾特性对火焰结构的影响,采用激光粒度分析仪等雾化测量系统,针对离心喷嘴的流量、喷雾锥角,以及喷口下游不同轴向位置的液滴索太尔平均直径、液滴尺寸分布指数等进行测量,并将其与火焰结构特征相结合进行分析。结果表明:随着供油压力的提高,喷雾锥角逐渐增大,当供油压力达到0.3 MPa后,锥角基本保持为定值;喷嘴的流量逐渐增大,并与油压呈二次曲线增大关系;索太尔平均直径和液滴尺寸分布指数先迅速减小,之后其减小的程度减缓。在相同供油压力下,随着测点距离的增加,索太尔平均直径呈减小趋势,但液滴尺寸分布指数出现先减小(测点位置为20、30 mm)后增大(测点位置为40 mm)的趋势。火焰的初始扩张角度与喷雾锥角的变化趋势基本相同,同时燃油与气流之间的剪切力随着供油压力的提高而增大,增强了燃油的二次雾化,使得火焰的高亮度区域向燃烧室两侧转移,并基本稳定在剪切层,且其范围逐渐扩大并后移。
Liquid fuel is typically used in combustor of aeroengine,and the combustion process of liquid fuel is usually accompanied by atomization,evaporation,and mixing.In this process,the fuel atomization quality will directly affect the effectiveness of evaporation and mixing,thereby having a direct impact on the performances of combustion,ignition,and emission.In order to study the influence of spray characteristics of pressure-swirl atomizer on the flame structure,the atomization measurement systems,including laser particle size analyzer,were used to measure the flow rate,spray angle,the Sauter mean diameter(DSM)and the droplet size distribution index(N value)at different locations downstream of nozzle.These measurements were then analyzed in conjunction with the flame structure characteristics.The results show that with the increase of fuel supply pressure,the spray angle gradually increases,and when it reaches 0.3 MPa,the angle basically remains a constant value;the flow rate increases and exhibits a quadratic relationship with the fuel pressure;the DSM and N values initially decrease rapidly,after which the rate of reduction slows down.Under the same fuel supply pressure,DSM decreases with the increase of measuring point distance,but N value decreases first(h=20 mm,h=30 mm)and then increases(h=40 mm).The initial expansion angle of the flame follows a trend similar to that of the spray angle,while the shear force between the fuel and the airflow increases with the increase of fuel supply pressure,which enhances the secondary atomization of the fuel.This causes the high-brightness area of the flame to shift toward both sides of the combustor,stabilizing in the shear layer,with its range gradually expanding and moving backward.