进口气流角对加力燃烧室流场的影响分析  

Influence Analysis of Inlet Flow Angle on the Flow Field of Afterburner

作　　者：文清兰 张琪 舒庆 Wen Qinglan;Zhang Qi;Shu Qing(AECC Guiyang Engine Design Research Institute,Guiyang 550081,China)

机构地区：[1]中国航发贵阳发动机设计研究所,贵州贵阳550081

出　　处：《航空科学技术》2021年第7期32-38,共7页Aeronautical Science & Technology

摘　　要：为研究低压涡轮出口气流角对加力燃烧室流场的影响,采用三维数值模拟方法,通过调整低压涡轮出口气流角,模拟加力燃烧室在不同气流角来流条件下的流场差异并开展影响分析。结果表明,气流角的增加将导致内涵进口的速度不均匀度、流阻损失增大,影响内涵燃油与内伸径向稳定器的匹配,恶化了内涵燃烧条件;随着进口气流角增大,整流支板根部吸力面产生流动分离,降低了支板通道的流通能力,使得整流支板出口速度及密流分布沿叶高方向存在较大的不均匀度,增大了内涵燃油匹配的难度;内伸径向稳定器后回流区范围随着进口气流角增大而减小,零速线范围最大相差约0.5个稳定器槽宽;同时随着进口气流角的增加,加力燃烧室混合器出口热混合效率提升约2%。In order to study the influence of outlet flow angle of low-pressure turbine on afterburner flow field,three-dimensional numerical simulation method was used to simulate the flow field difference of afterburner under different flow angle conditions by adjusting outlet flow angle of low pressure turbine,and the influence analysis was carried out.The results show that the increase of the flow angle will lead to the increase of velocity non-uniformity and flow resistance loss at the inner inlet,affect the matching between the inner fuel and the inner radial stabilizer,and worsen the inner combustion conditions.With the increase of inlet air flow angle,the suction surface at the root of the struts generates flow separation,which reduces the flow capacity of the strut passage,makes the velocity and dense flow distribution of the struts have a large degree of unevenness and increase the difficulty of matching the inner fuel.The range backflow area after the internal stabilizer decreases with the increase of inlet flow angle,and the maximum difference of zero-speed line range is about 0.5 stabilizer slot width.At the same time,with the increase of the inlet flow angle,the thermal mixing efficiency at the outlet of the afterburner mixer increases by about 2%.

关 键 词：加力燃烧室 低压涡轮 气流角 整流支板 回流区 热混合效率 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]