加力燃烧室火焰稳定装置流阻特性数值研究  

Numerical Study on Flow Resistance Characteristics of Flame Holder in an Afterburner

作　　者：陈翔 王一搏 刘云鹏 颜应文[1] CHEN Xiang;WANG Yibo;LIU Yunpeng;YAN Yingwen(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing,China 210016)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《热能动力工程》2024年第7期62-71,共10页Journal of Engineering for Thermal Energy and Power

基　　金：国家科技重大专项(J2019-Ⅲ-0004-0047)。

摘　　要：为降低加力燃烧室的流阻损失,避免发动机推力降低与耗油率上升,采用经试验数据验证的数值计算方法,研究了凹腔与支板两类火焰稳定装置结构参数变化对流场结构和流阻损失的影响规律,分析了火焰稳定器结构参数对回流率以及总压恢复系数的影响。所研究的加力燃烧室进口马赫数为0.385,凹腔火焰稳定装置倾斜角度范围为40~90°,深度为37~77 mm,支板火焰稳定器宽度范围为29~41 mm,尾缘扩张角度为0~15°。研究表明:凹腔倾斜角度对流场形态的影响较小,起主要影响的结构参数是凹腔深度,总压恢复系数随凹腔深度减小而逐渐增加;支板宽度减小会导致加力燃烧室内的回流区减小,总压恢复系数则单调增加;相较于中心锥回流区,支板尾缘和凹腔后回流区涡流强度更大,对流阻损失的影响更大;随支板火焰稳定器尾缘扩张角的增大,支板尾缘回流区变大,而凹腔-中心锥回流区由于受到压缩而逐渐减小,在扩张角度约为3.5°时总压恢复系数最大。To reduce wastage of engine thrust and fuel caused by the afterburner flow resistance loss,the influence of the structural parameter change of flame holders of cavity and strut on the flow field structure and flow resistance loss was studied by a numerical calculation method which had been verified by experimental data.The effect of the structural parameters of the flame holder on the reflux rate and total pres-sure recovery coefficient was analyzed.The Mach number at the inlet of the proposed afterburner was 0.385.The inclined angle range of the cavity flame holder was 40°to 90°with a depth of 37 to 77 mm.The width range of the strut flame holder was 29 to 41 mm with a trailing edge expansion angle of 0 to 15°.The results show the cavity depth influences the flow field more significantly rather than cavity inclined angle.And the total pressure recovery coefficient increases when the cavity depth decreases.With the decreasing of strut width,the recirculation zone in the afterburner shrinks,while the total pressure recovery coefficient increases monotonously.Compared with the central cone recirculation zone,the recir-culation zones at the tailing edge of the strut and behind the cavity have greater impact on the flow resistance loss with stronger vortex intensity.The recirculation zone at the tailing edge of strut grows and the integrated recirculation zone in cavity and central cone shrinks gradually caused by compression,with the incremental strut flame holder trailing edge expansion angle,which leads to the maximum total pressure recovery coefficient at expansion angle of about 3.5°.

关 键 词：加力燃烧室 火焰稳定装置 流阻特性 结构参数 总压恢复系数 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]