固体火箭技术2026，Vol.49Issue(4)：508-519,12.DOI:10.7673/j.issn.1006-2793.2026.04.003
串联型平动式TBCC进气道模态转换方案设计及流动特性研究
Mode transition scheme design and flow characteristics of tandem translational TBCC inlet
王璟驿 1辜天来 2袁化成1
作者信息
- 1. 南京航空航天大学 能源与动力学院,南京 210016
- 2. 中国运载火箭技术研究院研究发展中心,北京 100076
- 折叠
摘要
Abstract
A mode transition scheme for a tandem TBCC inlet was proposed,which utilizes a translating splitter plate to realize flow-path switching.Three geometric profiles of the transition device,namely convex,triangular,and concave,were designed.Two-dimensional numerical simulations were performed to investigate the flow field and aerodynamic characteristics of each profile during mode transition under different geometric parameters(radius of curvature R1 for Configuration A,inclination angle θ for Configuration B,and radius of curvature R2 for Configuration C).Taking the comprehensive optimization of the total pressure recovery coefficients for the turbine and ramjet flow paths as the selection criterion,the variant of configuration A with R1=0.30Rₑ(where Rₑ denotes the inlet exit radius)is selected as the optimal geometric profile-parameter combination and adopted as the baseline configuration for subsequent back-pressure characteristic studies.Numerical results under full operating conditions demonstrate that the proposed scheme can effectively control the opening and closing of the ramjet flow path,and can precisely coordinate the flow distribution between the two flow paths via their back-pressure regulation to meet the operational requirements of the downstream engine.关键词
TBCC/模态转换/数值仿真/进气道/组合动力Key words
TBCC/mode transition/numerical simulation/inlet/combined power分类
航空航天引用本文复制引用
王璟驿,辜天来,袁化成..串联型平动式TBCC进气道模态转换方案设计及流动特性研究[J].固体火箭技术,2026,49(4):508-519,12.
