清华大学学报（自然科学版）2025，Vol.65Issue(12)：2410-2448,39.DOI:10.16511/j.cnki.qhdxxb.2026.26.008
涡轮基组合循环发动机模态转换技术研究进展
Research progress in mode transition technologies for turbine-based combined cycle engines
摘要
Abstract
[Significance]Turbine-based combined cycle(TBCC)engine is an ideal propulsion system for hypersonic flight,with a wide-speed range,large flight envelope,and horizontal takeoff and landing capability.The TBCC engine,comprising an air-breathing gas turbine and a ramjet,has become a key aspect of current and future aerospace research.When the TBCC engine operates across a wide-speed range(Ma 0-7.0),it undergoes a mode transition between the gas turbine and the ramjet.This transition requires coordinated operation among various components and subsystems,involving a broad disciplinary scope,high technical complexity,and significant implementation challenges.Consequently,the mode transition has become a critical bottleneck in the development of TBCC engines.[Progress]This study systematically reviews the development progress of TBCC engines across various countries and analyzes the"thrust gap"phenomenon and the multi-component matching challenges that occur during mode transition.The review encompasses four key aspects:(1)Intake system design and regulation technology:Current mature approaches,such as boundary layer bleeding and vortex generators,offer limited adjustability,making precise and rapid flow control challenging.Axisymmetric intakes,favored for their simplicity in series-configured TBCC engines during mode transitions,still require enhanced variable-geometry capabilities to improve performance.Additionally,two-dimensional and three-dimensional inward-turning intakes provide greater regulation flexibility and effectively suppress inlet coupling interference;however,their control strategies within intake systems demand further in-depth investigation.(2)High-performance turbine and ramjet engine design,as well as rocket-assisted boost technology:Modified high-speed turbine engines utilizing inlet pre-cooling show greater potential,compared to newly developed ones,though their advancement hinges on the creation of lightweight pre-coolers that can operate across wide temperature ranges.For wide-speed ramjet technologies,methods such as rotating detonation combustion,advanced inlet designs,and combustion optimization can effectively extend the operational Mach number range.However,integrating these technologies into com bined-cycle engines requires further in-depth research.While rocket-assisted thrust augmentation directly addresses the"thrust gap,"incorporating an additional rocket engine may introduce significant structural complexity.(3)Exhaust system design and regulation technology:Future directions focus on efficient aerodynamic profile design and active control of shockwave-boundary layer interactions.Regarding nozzle configurations,both two-dimensional and three-dimensional nozzles can satisfy the exhaust expansion requirements of com b ined-cycle engines.Two-dimensional nozzles offer simpler structures but pose significant challenges for aerodynamic integration.In contrast,three-dimensional nozzles provide superior performance and better integration potential with the overall propulsion system;however,they involve greater design,manufacturing,and control complexities.(4)The combined-cycle engine system integration,mode transition control,and experimental testing technologies:The United States has conducted relatively comprehensive research,having completed integrated engine model-level mode transition tests and comparative analyses of various control algorithms.Nevertheless,most existing studies remain theoretical or limited to model validation.[Conclusions and Prospects]Many conducted mode transition experiments have not fully addressed the variable-geometry adjustment of the inlet and exhaust systems or the dynamic cooperative control of the fully integrated engine.Consequently,future research should prioritize cross-system integrated cooperative control for combined-cycle engines,the development of advanced test facilities capable of simulating wide-range flight environments,and full-scale engine validation of mode transition processes.Key future research directions include optimizing off-design performance and multi-physics coupling in intake system design,advancing rotation detonation combustion technology,developing three-dimensional nozzle control and multi-duct collaborative matching techniques,and establishing a full-chain research and development system for TBCC engines.关键词
组合循环发动机/模态转换/推力陷阱/进排气系统/整机集成Key words
combined cycle engines/mode transition/thrust trap/intake and exhaust system/integrated integration分类
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裴希同,王兵,齐承鲁,钱秋朦,谢峤峰,李子万,王鑫煜..涡轮基组合循环发动机模态转换技术研究进展[J].清华大学学报（自然科学版）,2025,65(12):2410-2448,39.基金项目
国家自然科学基金重点项目(12441201) （12441201）
