Research Fields
Focus on the research and development (R&D) and system integration of the advanced light-duty gas turbines, and include the fundamental research of aero engine, the key technology R&D, the innovative system integration and new product development.
Team Building
The laboratory currently has 117 employees, including 10 professors，22 associate professors/senior engineers, 46 graduates and 3 postdoctoral researchers.
Projects and Major Achievements
There are more than 50 research projects including 18 new in 2020. Namely, 3 aero engine and gas turbine special grants, 1 key deployment project of the Chinese Academy of Sciences, and 1 strategic pilot science and technology special project of the Chinese Academy of Sciences, 13 sub-projects of aero engine and gas turbine special grants, and 3 industry cooperation projects. Meanwhile, 11 projects (including exploration projects, pilot projects, and instrument development projects of the Chinese Academy of Sciences, etc.) were finished. Integration of light-duty aero-engines:
1. For light-duty turbofan engines, based on engine test data, various engine components and systems were improved, and light-duty turbofan engine performance test was completed; the high-altitude platform simulation tests of the light-duty turbofan engine were carried out, and the engine performance in the full envelope was obtained; the 150-hour long-term and intake distortion tests for small turbofan were finished, the reliability of the engine was further verified, and it was shown to be suitable for the first flight test.
2. For light-duty turbojet engines, we have carried out the key technology research on high unit windward thrust turbojet engines for supersonic UAVs, and completed the manufacturing and assembly of light turbojet engines, and made breakthroughs in the low fuel consumption design and fast start technology of the light turbojet engines, a high efficiencycost ratio light-duty turbojet engine was achieved; the development of a lightduty turbojet engine with afterburner was finished, and it was already installed on an unmanned aerial vehicle for flighting test.
Fundamental research and key technologies:
1. The theoretical research on the quantitative evaluation of the comprehensive weighted efficiency-cost ratio of short-life engines was completed. The quantitative evaluation model of the comprehensive weighted efficiency-cost ratio of short-life engines was initially established.
2. The internal complex flow mechanism and key influence parameters of the front tandem rotor fan were developed. Breakthrough progress on the key design technology was achieved. The design method of the front tandem rotor fan was established.
3. The design method of ultra-high pressure ratio centrifugal compressor was carried out. The design method of the multi-flow blade, tandem impeller and integrated tubular expansion, etc. was also explored.
4. The experiments on aerodynamic atomization characteristics, ignition and cross-fire of combustion chambers at high altitudes were carried out. The image processing methods for flame propagation paths and dynamic characteristics were developed. The basic data on combustion chamber ignition characteristics at high altitudes were obtained. It provides support for the highaltitude re-ignition technology of the engine combustion chamber.
5. The study of the secondary flow mechanism in the end wall of the high-load low-pressure turbine at high altitude and low Reynolds number has been carried out. The mechanism of the secondary flow physics in the end wall of the low-pressure turbine by the coupling of the wake and the non-axisymmetric end wall has been explored.
Verification platform constructions:
1. The installation and test of the superrotation test facility were completed. The first domestic test facility with radial growth and other test capabilities was developed.
2. The aero-engine aerodynamic stability test facility, control and accessory system reliability test platform, spindle high and low cycle coupling fatigue and static strength test platform, casing fatigue and static strength test platform, control and accessory environmental adaptability test platform, high altitude and complex flow combustion chamber basic verification test platform, Reynolds number variable compressor test platform, low-speed and large-size centrifugal compressors test platform, etc. was planned and built. These facilities provide support for the development of light-duty jet engines.
Patents and Paper
A total number of 52 academic papers were published in this year, of which 38 were SCI, 14 were EI, and 46 patents were submitted and 28 were licensed.
Awards
A total of 52 research papers were published this year, of which 38 were indexed by SCI and 14 were indexed by EI; 46 patents were applied and 28 patent were authorized; the second prize of National Science and Technology Progress Award in 2020 was achieved; Two scientific and technological achievements of "a turbojet engine technology" and "a turbofan engine technology" passed expert appraisal; The "Advanced Light-duty Aero Engine Research Team" won the 2020 National Defense Science and Technology Industry Outstanding Contribution Award; the "Advanced Light-duty Aero Engine" achievement was selected as a major landmark achievement of the Chinese Academy of Sciences' first action plan, and was rated as outstanding in the direction of major breakthroughs.
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