Research Field
Research and development (R&D) and system integration of the advanced light-duty gas turbines, including the fundamental research of aero engine, the key technology R&D, the innovative system integration, and new product development.
Research Interests
Overall performance and structural design of light-duty aero engines; Flow mechanisms and design of high-load, high-efficiency, and high-operability compressor systems; Combustion organization and design methods for widerange and high-efficiency operation; Turbine design technologies integrating aerodynamic performance, cooling characteristics, and reliability; Structural strength and reliable design technologies for aero engines; Control system design and fault-tolerant control technologies for aero engines; Design and integration methods for high power density accessory systems; Testing and evaluation technologies for aero engines; System integration and key technology verification for light-duty aero engines.
Team Building
The laboratory currently has 171 employees, including 17 professors, 21 associate professors/senior engineers; 89 graduates and 4 postdoctoral researchers.
Project and Major Achievement
In 2024, more than 120 projects are being carried out, and 33 new projects have been approved, including 1 key project funded by the National Natural Science Foundation of China, 4 general projects funded by the National Natural Science Foundation of China, 1 key project funded by the Beijing Natural Science Foundation, 1 pilot project on critical core technologies by the Chinese Academy of Sciences, 1 pilot project on basic and interdisciplinary frontier research by the Chinese Academy of Sciences.
In the field of light-duty turbine engines, a series of single-shaft turbofan engines have been independently developed and have completed scientific research flight tests. Several turbojet engines have successfully undergone high-speed flight verification, and multiple turbofan engines have passed performance evaluation tests.
In terms of the thermal physics test device for key components of airbreathing engines, detailed designs of all systems, including the compressor matching test cabin, the combustor-turbine aero-thermal coupling test system, the air system test cabin, the intake-exhaust matching test cabin, and the gas supply system, have been completed and successfully reviewed. All critical procured or self-developed equipment has completed the bidding process and contract signing. The project has smoothly passed the 2024 annual process management evaluation.
In terms of basic research, studies were conducted on high-efficiency cost-performance ratio and equal-life design theories and methods for lightweight aero engines. A theoretical model for the integrated weighted cost-performance ratio of short-lifespan engines under multidimensional constraints was developed, along with equal-life design theories and methods for key components. Breakthroughs were achieved in simplification technologies for core components and systems, laying the foundation for a theoretical framework and methodology for highefficiency, cost-effective, equal-life design of short-lifespan engines. Research was also carried out on ignition and extinction characteristics under extreme conditions, including prediction and boundary expansion methods. Key insights were obtained into flame kernel formation, flame propagation and stabilization, flame lift-off/detachment, and extinction mechanisms. A comprehensive database, boundary prediction model, evaluation criteria, and optimization methods for ignition/extinction characteristics under extreme conditions were established. Further studies focused on modeling methods and experimental validation of low Reynolds number effects in compressors. Systematic investigations were conducted into how Reynolds number affects compressor characteristics, flow structures, and losses, leading to the development of a Reynolds number correction method for compressor performance. The degradation mechanisms of compressor performance under low Reynolds numbers were also explored, typical internal flow features were identified, and aerodynamic design and stability control methods suitable for highaltitude, low-Reynolds-number conditions were established.
Patent and Paper
A total of 85 academic papers were published during the year, including 48 indexed by SCI and 15 indexed by EI. Twenty-nine invention patents were filed; 32 were granted, and 3 software copyrights were registered.
Awards
The project “Key Technologies and Applications of In-Flight Rapid StartUp for Lightweight Turbine Engines” received the First Prize of the 2024 Technology Invention Award from the Chinese Society of Engineering Thermophysics. Two other achievements, “Novel Tandem Compression System for Aero Engines” and “High-Efficiency Cost-Performance SingleShaft Turbofan Engine Technology,” successfully passed the GF scientific and technological achievement appraisal.
Dean: LU Xin’gen 010-82543044 luxg@iet.cn
Deputy Dean: ZHAO Shengfeng 010-82543131 zhaoshengfeng@iet.cn
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Laboratory