前置翼片式涡流发生器对燃烧室氢气燃料掺混特性的影响  

Effect of front vane vortex generators on hydrogen fuel mixing characteristics in combustor

作　　者：吴龙 王江峰[1,2] 李龙飞 王丁[1,2] WU Long;WANG Jiangfeng;LI Longfei;WANG Ding(Key Laboratory of Unsteady Aerodynamics and Flow Control of Ministry of Industry and Information Technology,Nanjing 210016,China;College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]非定常空气动力学与流动控制工业和信息化部重点实验室,南京210016 [2]南京航空航天大学航空学院,南京210016

出　　处：《空气动力学学报》2023年第3期33-43,I0001,共12页Acta Aerodynamica Sinica

基　　金：国家数值风洞工程(NNW2019ZT7-B30,NNW2018-ZT3B08);江苏优势学科建设工程。

摘　　要：超声速来流与燃料的充分掺混是超声速燃烧的关键技术,直接关系到吸气式高超声速推进系统的总体性能。本文通过在射流口前安装翼片式涡流发生器以促进燃料与空气的掺混。基于SSTk-ω湍流模型的RANS方法,对带有翼片式涡流发生器的超燃冲压发动机燃烧室模型内氢气横向喷流冷流流场进行了数值模拟,对比分析涡流发生器高度和长度不同的条件下燃烧室内的流场结构、涡流强度、氢气与空气掺混特性、燃烧室总压损失的规律。结果表明,翼片式涡流发生器能够提高涡流强度并大幅提高燃烧室内的掺混性能。随着涡流发生器高度和长度的增加,流场结构间的干扰增强,导致涡流强度和穿透深度增加,从而提升掺混效率。与不安装涡流发生器情况相比,涡流发生器能提升氢燃料的穿透深度超过170%,减少燃料掺混距离70%以上。更加复杂的流场结构同时会增大燃烧室的总压损失,并随着涡流发生器高度和长度的增加而增大。相较于掺混性能的提升,总压损失的增大幅度相对小很多,说明通过合理的参数选择,翼片式涡流发生器能够有效提升燃烧室的掺混性能。The mixing process plays an important role in supersonic combustion,and sufficient mixing between the incoming supersonic air and the fuel is closely related to the overall performance of the airbreathing hypersonic propulsion system.In the present study,vane vortex generators are placed in front of the injector to promote the mixing of the fuel and the air.The three-dimensional compressible N-S equations and the two-equation SST k-ωturbulence model are used to simulate the cold flow field of the hydrogen transverse jet in a scramjet combustor.Effects of the vane vortex generator height and length on the flow field structure,vorticity intensity,mixing characteristics of hydrogen/air and total pressure loss in the combustor have been investigated.The results show that the vane vortex generator can greatly improve the vorticity intensity and the mixing performance of the combustor.With the increase of the vortex generator height and length,the interaction among flow field structures increases,resulting in the increase of the vorticity intensity and penetration depth,thus improves the fuel mixing efficiency in the combustor.Compared to the scheme without vortex generators,the penetration depth of the hydrogen jet can be increased by more than 170%,and the distance of the complete mixing can be reduced by more than 70%.More complex flow field structures also increase the total pressure loss of the combustor,and this effect increases with the height and length of the vortex generator.Compared to the improvement of the mixing performance,the increase of the total pressure loss is much smaller,indicating that the vane vortex generator can effectively improve the mixing performance of the combustor through reasonable parameter selection.

关 键 词：涡流发生器 横向喷流 超燃冲压发动机燃烧室 涡流强度 掺混特性 总压损失 

分 类 号：V434.13[航空宇航科学与技术—航空宇航推进理论与工程]