航空学报2026，Vol.47Issue(6)：1-16,16.DOI:10.7527/S1000-6893.2025.32842
外并联型进气道模态转换过程中低速通道再起动特性
Restart characteristics of low-speed duct during mode transition in an over-under inlet
摘要
Abstract
This paper investigates the unsteady flow characteristics within the inlet during the ram-to-turbo transition of a Turbine-Based Combined Cycle(TBCC)engine.Through a combined approach of wind tunnel test and Computa-tional Fluid Dynamics(CFD)simulations,it analyzes the evolution of the inlet shock system and the static pressure variation patterns along critical flow path locations,and acquires the dynamic restart characteristics of the low-speed duct during inlet mode transition and the influence of flow splitter rotational speed on this process.The results indicate that during the progressive opening of the low-speed duct under turbine-mode startup conditions,six distinct phases occur:in phase 1,flow splitter deployment initiates boundary layer ingestion into the duct,causing minor static pres-sure drop;in phase 2,supersonic core flow enters the duct,triggering significant static pressure rise;in phase 3,flow accumulation induces pressure buildup and shock train forward propagation,followed by shock traversal past the bleed cavity,with subsequent cavity depressurization causing shock recession;in phase 4,cyclic expansion/contrac-tion of the low-speed duct separation bubble induces shock oscillation;in phase 5,shock expulsion along the separa-tion bubble triggers inlet buzz;in phase 6,reduction in downstream Throttling Ratio(TR)terminates buzz,enabling low-speed duct restart.During the low-speed duct restart process,the rotational speed of the flow splitter vanes influ-ences both the frequency and amplitude of pressure oscillations within the flow path,with lower rotational speeds re-sulting in reduced oscillation frequencies and increased amplitudes.Moreover,during low-speed duct restart,the rota-tional speed also affects the onset timing of buzz,where lower speeds more readily trigger inlet buzz in the low-speed duct.This study provides a theoretical foundation for achieving smooth mode transition in combined-cycle engines.关键词
外并联型进气道/模态转换/喘振/再起动/风洞试验Key words
over-under inlet/mode transition/buzz/restart/wind tunnel test分类
航空航天引用本文复制引用
张悦,杨刚,谭慧俊,张晗天,庞明池,张龙芝,高夏豪..外并联型进气道模态转换过程中低速通道再起动特性[J].航空学报,2026,47(6):1-16,16.基金项目
国家自然科学基金(12172175) （12172175）
航天液体动力全国重点实验室基金(2024JJ015010) National Natural Science Foundation of China(12172175) （2024JJ015010）
Fund of National Key Laboratory of Aerospace Liquid Propulsion(2024JJ015010) （2024JJ015010）
