回流型内燃波转子过渡段与燃料填充段耦合特性研究  

Coupling characteristics between transition duct and fuel filling duct in a reverse-flow combustor wave rotor

作　　者：何志军 李建中[1] 巩二磊[1] 金武 姚倩 郑仁传 冯战 HE Zhijun;LI Jianzhong;GONG Erlei;JIN Wu;YAO Qian;ZHENG Renchuan;FENG Zhan(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《燃气涡轮试验与研究》2024年第3期46-52,共7页Gas Turbine Experiment and Research

基　　金：国防科技基础研究项目(1002TJA21007);江苏省自然科学基金(BK20210278)。

摘　　要：为了在回流型内燃波转子进气过渡段内形成高质量的燃料分布,提出一种新型液态燃料喷注结构。采用数值模拟方法,模拟了不同喷油孔喷射位置与射流角度下液态燃料的填充效果,并结合液滴驻留时间、索太尔平均直径以及燃料分布不均匀度,分析了喷油孔喷射位置和射流角度对过渡段与燃料填充段耦合特性的影响规律。研究结果表明,喷射位置为40 mm和60 mm时,在进气过渡段出口截面可以形成相对均匀的燃料分布;增大射流角度后,弯管掺混区形成了较大尺度和较强强度的涡流,使得出口截面燃料分布更加均匀。In order to achieve high-quality fuel distribution in the intake transition duct of a reverse-flow wave rotor combustor,a novel liquid fuel injection structure was proposed.Numerical simulation was used to model the liquid fuel filling effect under different injection hole positions and jet angles.The coupling characteristics between the transition duct and fuel filling duct were analyzed by combining parameters such as droplet residence time,Sauter mean diameter and fuel distribution non-uniformity.The results show that when the injection positions are at 40 mm and 60 mm,a relatively uniform fuel distribution can be achieved at the outlet cross-section of the intake transition duct.With the increase in jet angle,larger scale and stronger intensity vortices are formed in the mixing zone of the bent duct,which further improves the uniformity of fuel distribution at the outlet cross-section.

关 键 词：回流型内燃波转子 液态燃料喷注 燃料填充 燃料分布 索太尔平均直径 航空发动机 

分 类 号：V232.1[航空宇航科学与技术—航空宇航推进理论与工程]