强余旋一体化支板稳定器雾化特性研究  

Atomization characteristics under residual swirl condition for integrated struct flameholder

作　　者：吴杰 胡喆 刘金鹤 穆勇 何志霞[5] 阮昌龙 刘舆帅 WU Jie;HU Zhe;LIU Jinhe;MU Yong;HE Zhixia;RUAN Changlong;LIU Yushuai(Research Center of Fluid Machinery Engineering and Technology,Jiangsu University,Zhenjiang 212013,China;Laboratory of Light-Duty Gas-Turbine,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100049,China;Qingdao Institute of Aeronautical Technology,Qingdao 266000,China;School of Energy and Power Engineering,Jiangsu University,Zhenjiang 212013,China)

机构地区：[1]江苏大学流体机械工程技术研究中心,江苏镇江212013 [2]中国科学院工程热物理研究所轻型动力实验室,北京100190 [3]中国科学院大学航空宇航学院,北京100049 [4]青岛航空技术研究院,山东青岛266000 [5]江苏大学能源与动力工程学院,江苏镇江212013

出　　处：《推进技术》2024年第8期166-179,共14页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-Ⅲ-0004-0047);泰山学者工程。

摘　　要：本文在高温高速强余旋来流条件下,初步探索了带尾缘方案下支板一体化喷油稳定器结构的油气掺混工作特性,为后期研究回流区卷吸量和稳焰特性做准备。使用平面激光诱导荧光(PLIF)、平面米散射(PMIE)、相位多普勒粒子分析仪(PDPA)等设备,以航空煤油为介质,在来流温度300~1050 K,马赫数0.15~0.45,液气动量比20~250,来流角度-15°~15°,供油压差0.2~1.8 MPa等条件下,探究了来流参数、气液动量比、韦伯数等多因素对射流轨迹、雾化粒径的影响规律。试验表明:上喷式支板尾缘一体化喷油稳定器的整体射流轨迹与横向射流结构较类似,液气动量比越大,射流穿透深度增加越明显;气体韦伯数的影响机制比较复杂,当其增大时,射流穿透深度呈下降趋势,是来流与射流之间的压差力和各向剪切力的作用使得表面波增长迅速,不稳定性增强,叠加气液动量交换增大的结果;气流与支板夹角的正逆变化,即余旋角变化,使得垂直于来流气体方向的速度分量产生变化,流道内稳定器的喉部效应增大了湍流度,使射流轨迹变粗糙,穿透深度变短;通过分析PDPA数据,在射流覆盖区域呈现出了整体的粒径分布情况,显示出了射流轨迹、表面波主导破碎区、二次雾化区、粒径稳定区间的关系。In this paper,under the conditions of high temperature,high speed and strong cosine rotation flow,the fuel/air mixing characteristics of the Integrated Strut Flameholder with Trailing Edge(ISF-TE)were preliminarily studied,which was prepared for the later study of the entrainment and flame stabilization character⁃istics of the recirculation zone.Using Planar Laser Induced Fluorescence(PLIF),Planar Mie Scattering(PMIE),Phase Doppler Particle Analyzer(PDPA)and other equipments,with aviation kerosene as medium,the influenc⁃es of incoming flow parameters,gas-liquid momentum ratio,Weber number and other factors on jet trajectory and atomization particle size distribution were investigated under the conditions of incoming flow temperature range from 300 to 1050 K,Mach number range from 0.15 to 0.45,liquid-gas momentum ratio range from 20 to 250,incoming flow angle from-15°to 15°and fuel supply pressure difference range from 0.2 to 1.8 MPa.The re⁃sult shows that the overall jet trajectory of the up-jet ISF-TE is similar to that of the crossflow,and the penetra⁃tion depth increase with the increase of liquid-gas momentum ratio.The influence mechanism of the gas Weber number is complex.As it increases,there is a subtle downward trend in penetration depth,attributed to the heightened exchange of air-liquid momentum.This phenomenon results from the rapid growth of surface wave in⁃stability induced by both radial and tangential shear forces,as well as the pressure differential force generated be⁃tween the windward and leeward sides of the jet.The variation in the angle between the airflow and the ISF-TE,known as the cosine rotation angle,results in changes to the velocity component perpendicular to the direction of the incoming air,and the throat effect of the stabilizer in the flow channel increases the turbulence degree to make the jet trajectory rougher and the penetration depth shorter.By analyzing the PDPA data,the overall parti⁃cle size distribution is presented in the jet coverage area,showing the rela

关 键 词：加力燃烧室 一体化支板 雾化特性 PLIF PMIE PDPA 

分 类 号：V231.23[航空宇航科学与技术—航空宇航推进理论与工程]