涡轮基组合循环发动机模态转换技术研究进展

裴希同, 王兵, 齐承鲁, 钱秋朦, 谢峤峰, 李子万, 王鑫煜

清华大学学报（自然科学版） ›› 2025, Vol. 65 ›› Issue (12) : 2410-2448.

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清华大学学报（自然科学版） ›› 2025, Vol. 65 ›› Issue (12) : 2410-2448. 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

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Research progress in mode transition technologies for turbine-based combined cycle engines

Author information +
文章历史 +

摘要

涡轮冲压组合循环发动机是高超声速飞行器实现宽速域、大空域和水平起降等飞行能力的理想动力装置, 由航空燃气涡轮发动机与冲压发动机组合而成, 是当前以及未来空天领域研究的重点。涡轮冲压组合循环发动机在宽速域(Ma为0~7.0)运行时, 存在涡轮发动机与冲压发动机之间的模态转换。模态转换过程需要各部件和系统间密切配合和协同调控, 具有涉及学科范围广、技术复杂度高和实现难度大等特点, 已成为制约涡轮冲压组合循环发动机技术发展的关键问题。该文首先系统总结了世界各国或组织对于涡轮冲压组合循环发动机的研究进展, 分析了模态转换过程存在的“推力陷阱”和整机多部件协同调控等问题; 随后, 从进气系统设计及调节技术, 高性能涡轮及冲压发动机整机设计与火箭助燃增推技术, 排气系统设计及调节技术, 组合发动机系统集成、模态转换控制与试验测试技术等4个维度进行综述, 并详细对比分析了不同类型的关键技术, 总结了各类关键技术的研究进展。结果表明, 进气系统非设计点性能与多物理场耦合设计、旋转爆震新型燃烧技术研发、三维喷管调控与多流道协同匹配技术研发和全链条研发体系建设将成为涡轮冲压组合循环发动机领域未来研究的重点。该文研究结果可为涡轮冲压组合循环发动机技术从理论研究迈向工程应用奠定基础。

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 combined-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 combined-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

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裴希同, 王兵, 齐承鲁, 等. 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 https://doi.org/10.16511/j.cnki.qhdxxb.2026.26.008
Xitong PEI, Bing WANG, Chenglu QI, et al. Research progress in mode transition technologies for turbine-based combined cycle engines[J]. Journal of Tsinghua University(Science and Technology). 2025, 65(12): 2410-2448 https://doi.org/10.16511/j.cnki.qhdxxb.2026.26.008
中图分类号： V236   

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