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2024 International Conference on aerospace, Mechanical and Materials engineering, AMME 2024

作者： Cao, Bo Yu, Yi Sun, Jingchuan Zhang, Lina Hangzhou International Innovation Institute Beihang University Hangzhou311115 China Tianmushan Laboratory Hangzhou310023 China Research Institute of Aero-engine Beihang University Beijing China AECC Hunan Aviation Powerplant Research Institute Hunan412002 China National Key Laboratory of Science and Technology on Aero-engine Aero-thermodynamics Beihang University Beijing China

The continuous escalation of turbine inlet temperatures in aero-engine applications has rendered traditional air-cooling techniques insufficient to undertake the efficient cooling of turbine guide vanes solely. In this context, oil-cooling technology has emerged as a potent complement to air-cooling methods. The stable operating temperature limit of fuel, when used as a coolant, is merely 523 K. In contrast, turbine guide vanes operate at temperatures as high as 1, 900 K, with material allowable temperatures strictly constrained within 1, 373 K. Designing efficient and safe oil-cooled blade structures becomes paramount to the successful application of oil-cooling technology. This paper presents a layered oil-cooled turbine blade structural design scheme, which ingeniously integrates insulation and heat conduction mechanisms, effectively enhancing the oil-cooling system's adaptability to complex thermal flow environments and notably optimizing the uniformity of temperature distribution on the blade surface. Leveraging commercial simulation software, reduced order models and high-fidelity response surface models of the oil-cooled blades were constructed to conduct a parametric analysis of the layered oil-cooling structure. Under the conditions of ensuring cooling effectiveness and preventing fuel overheating, optimal design parameters for the internal structure of the layered oil-cooled turbine blades were identified, thereby establishing a comprehensive data-driven optimization methodology framework that supports thermal protection design in aero-engine. © 2025 Institute of Physics Publishing. All rights reserved.

关键词： Heat conduction

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Research on the Loosening Mechanism of the Rotor with Curvic Couplings in Aircraft engines 7th

Research on the Loosening Mechanism of the Rotor with Curvic...

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7th China aeronautical science and technology Conference, CASTC 2024

作者： Jing, Xiaoming Zha, Hong Liu, Zhenchen Mei, Shun Wang, Fang China AECC Hunan Aviation Powerplant Research Institute Zhuzhou412002 China Hunan Key Laboratory of Turbo Machinery on Small and Medium Aero-Engine Zhuzhou412002 China National Defense Key Discipline Laboratory of Light Alloy Processing Science and Technology Nanchang Hangkong University Nanchang330063 China

ISBN: (纸本)9789819797738

Understanding the mechanism of rotor looseness in aircraft engines and the characterization of the corresponding rotating mechanical parameters play an important role in quickly diagnosing technical problems about rotor looseness and improving the stability design of the rotor. Taking a certain rotor with curvic couplings as the research object, this paper analyzed the mechanism of the influence of preload and loosening changes on the stability of the rotor structure by applying the validation methods of numerical simulation and modal test. The results showed that the changing trends in simulation calculation and modal test were the same. When the preload of the rotor decreased, the stiffness of curvic couplings sharply decreased, and the critical bending speed of the rotor decreased significantly. Therefore, when the rotor with curvic couplings became loose, its operating characteristics indicated a typical resonance instability phenomenon. In rotor dynamic property design, the stiffness of the rotor with curvic couplings should be designed according to the minimum preload during the operating process. Before installation tests, modal tests should be conducted on rotors with different preload states to obtain the minimum allowable preload value during operation and verify whether the design meets the application requirement. © Chinese Society of aeronautics and Astronautics 2025.

关键词： Modal analysis

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Film cooling effectiveness in the presence of internal hole random roughness: A comprehensive analysis

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International Communications in Heat and Mass Transfer 2025年 165卷

作者： Wang, Xinyu Ye, Lin Li, Wei Zheng, Tianyi Liang, Xiyuan Liu, Cunliang School of Power and Energy Northwestern Polytechnical University Shaanxi Xi'an710129 China State Key Laboratory for Strength and Vibration of Mechanical Structures Xi'an Jiaotong University Shaanxi Xi'an710049 China Science and Technology on Altitude Simulation Laboratory Sichuan Mianyang621000 China Hunan Aviation Powerplant Research Institute Aero Engine Corporation of China Hunan Zhuzhou412002 China

Film cooling, with its excellent cooling performance, is widely applied in the active thermal protection design of aerospace propulsion systems. However, during manufacturing and service, film holes are affected by drilling processes and particle deposition, leading to significant deviations between the actual cooling structures and the original design. These deviations primarily manifest as hole blockage and increased surface roughness, which may cause cooling degradation. Therefore, it is essential to investigate the film cooling performance under structural damage and the jet-mainstream mixing mechanisms of damaged holes. This study focuses on internal roughness as a form of structural damage by investigating three levels of hole roughness—Ra = 3.1 μm (Film hole I), Ra = 35.9 μm (Film hole II), and Ra = 64.9 μm (Film hole III). The selected roughness levels and blowing ratios correspond to the practical range encountered in turbine cooling. The film cooling effectiveness distribution is measured using pressure-sensitive paint technology, and numerical simulations are conducted to analyze the flow field and support the experimental results. The results indicate that cooling degradation caused by internal roughness is mainly reflected in the reduction of high cooling effectiveness areas and the deterioration of cooling performance near the film hole exit. However, increased roughness also leads to an expansion of the film coverage in the spanwise, enhancing cooling performance downstream. Flow field analysis reveals that internal roughness increases the inhomogeneity of coolant velocity distribution inside the hole, strengthening the counter-rotating vortex pair and causing jet lift-off, which reduces the high cooling effectiveness area. Additionally, roughness-induced disturbances enhance turbulence intensity, promoting jet-mainstream mixing and increasing the overall film coverage. © 2025

关键词： Solar sails

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Design and implementation of rigid-flexible coupling for a half-flexible single jack nozzle

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Chinese Journal of aeronautics 2016年第6期29卷 1477-1483页

作者： Chen Pengfei Wu Feng Xu Jinglei Feng Xudong Yang Qiao Aviation Key Laboratory of Science and Technology on Aero-Engine Altitude Simulation China Gas Turbine Establishment Aviation Engine Corporation of China Department of Power Engineering Nanjing University of Aeronautics and Astronautics

The aerodynamic design of a rigid-flexible coupling profile is the decisive factor for the flow-field quality of a supersonic free jet wind tunnel nozzle, and its mechanic dynamic features are the key for engineering implementation of continuous Mach number regulations. To fulfill the requirements of a free jet inlet/engine compatibility test within a wide simulation envelop, both uniform flow-fields of continuous acceleration and deceleration are necessary. In this paper, the aerodynamic design methods of an expansion wall and machinery implementation plan for the halfflexible single jack nozzle were researched. The profile control in nozzle flexible plate design was studied with a rigid-flexible coupling method. Design and calculations were performed with the help of numerical simulation. The technique of axial free stretching of the flexible plate was used to improve the matching performance between the designed elasticity profile and the theoretical one, and the rigid-flexible coupling structure was calibrated by wind tunnel tests. Results indicate that the flexible plate aerodynamic design method used here is effective and feasible. Via rigidflexible coupling design, the flexible plate agrees with the rigid body very well, and continuous Mach number changes can be achieved during the tests. The nozzle’s exit flow-field uniformity meets the requirements of China Military Standard(GJB).

关键词： aerodynamic profile Flow-field quality Free jet Nozzle Rigid-flexible coupling Variable Mach number Wind tunnel

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Experimental Studies on Droplet-Size Distribution in a Reverse-Flow Combustor of a Two-Staged Fuel Injector

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Journal of aerospace engineering 2025年第4期38卷

作者： Jin, Yi Huang, Yakun Ding, Guoyu Yao, Kanghong Zhang, Kai Wang, Yunbiao College of Energy and Power Engineering Nanjing Univ. of Aeronautics and Astronautics Jiangsu Nanjing210016 China National Key Laboratory of Transient Physics Nanjing Univ. of Science and Technology Nanjing210094 China Aero Engine Corporation of China Hunan Aviation Power Plant Research Institute Zhuzhou412002 China

The ultracompact combustion chamber is a promising propulsion system for low-altitude, miniaturized aircraft, with fuel injection characteristics directly influencing the flame stability limit, a critical factor for optimizing combustion performance. This study innovatively measured the fuel droplet distribution characteristics under flame stability critical conditions for a two-stage injector in a closed, reverse-flow combustion chamber and explored the impact of fuel atomization on the stability limit. The experiment was conducted at standard temperature and pressure using a laser particle size analyzer to measure droplet distribution at three points downstream of the nozzle, with the nozzle supply pressure drop corresponding to the ignition and lean blowout limits. Results showed that as the inlet velocity ranged from 9.4 m/s to 42.1 m/s, the average sauter mean diameter (SMD) of fuel droplets near the spark plug was between 23.34 and 63.86 μm. As the inlet velocity increased, the fuel supply pressure difference at the flameout limit also increased. The fuel particle size distribution near the ignition electrode expanded from 20-50 μm to 29-144 μm, and then decreased to 16-95 μm. The main fuel particle diameter first increased from 34 μm to 87 μm, then decreased to 51 μm. When the inlet velocity exceeded 28.9 m/s, the droplet size near the spark plug became smaller and more uniform, suggesting that fuel atomization was not the primary cause of the increased pressure drop at the flameout limit. These findings provide valuable insights for extending the flame stability limit by adjusting fuel droplet distribution. © 2025 American Society of Civil engineers.

关键词： Combustion chambers

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μ-Synthesis control with reference model for aeropropulsion system test facility under dynamic coupling and uncertainty

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Chinese Journal of aeronautics 2023年第10期36卷 246-261页

作者： Jiashuai LIU Xi WANG Xi LIU Meiyin ZHU Xitong PEI Song ZHANG Zhihong DAN School of Energy and Power Engineering Beihang UniversityBeijing 100191China Zhongfa Aviation Institute Beihang UniversityHangzhou 311115China Research Institute of Aero-Engine Beihang UniversityBeijing 100191China Science and Technology on Altitude Simulation Laboratory AECC(Aero Engine Corporation of China)Sichuan Gas Turbine EstablishmentMianyang 621703China

Due to the dynamic coupling and multi-source uncertainties,it is difficult to accurately control the pressure and temperature of the aeropropulsion System Test Facility(ASTF)in the presence of rapid command and large *** paper presents the design ofμ-synthesis control to solve the *** incorporating the pressure ratio into the linear equation of the control valve,the modeling error of ASTF in the low frequency range is effectively ***,an uncertain model is established by considering various factors,including parameter variations,modeling error in the low frequency range,unmodeled dynamics,and changes in the working *** address the dynamic coupling,a diagonal reference model with desired performance is incorporated intoμ-***,all weighting functions are designed according to the performance ***,theμ-controller is obtained by using the standardμ-synthesis *** results indicate that theμ-controller decouples the pressure and temperature dynamics of *** with the multivariable PI controller,integral-μcontroller,and double integral-μcontroller,the proposedμ-controller can achieve higher transient accuracy and better disturbance ***,the robustness of theμ-controller is demonstrated by Monte Carlo simulations.

关键词： aeropropulsion System Test Facility(ASTF) Decoupling Robustness μ-Synthesis Uncertainty

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A novel multi-fidelity coupled simulation method for flow systems

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Chinese Journal of aeronautics 2013年第4期26卷 868-875页

作者： Wang Peng Zheng Yun Zou Zhengping Qi Lei Zhou Zhixiang National Key Laboratory of Science & Technology on Aero-Engine Aero-thermodynamics School of Energy and Power Engineering Beihang University Aeroengine Numerical Simulation Research Center School of Energy and Power Engineering Beihang University Chinese Aviation Powerplant Research Institute

For the numerical simulation of flow systems with various complex components, the traditional one-dimensional （1D） network method has its comparative advantage in time consuming and the CFD method has its absolute advantage in the detailed flow capturing. The proper coupling of the advantages of different dimensional methods can strike balance well between time cost and accuracy and then significantly decrease the whole design cycle for the flow systems in modern machines. A novel multi-fidelity coupled simulation method with numerical zooming is developed for flow systems. This method focuses on the integration of one-, two-and three-dimensional codes for various components. Coupled iterative process for the different dimensional simulation cycles of sub-systems is performed until the concerned flow variables of the whole system achieve convergence. Numerical zooming is employed to update boundary data of components with different dimen-sionalities. Based on this method, a highly automatic, multi-discipline computing environment with integrated zooming is developed. The numerical results of Y-Junction and the air system of a jet engine are presented to verify the solution method. They indicate that this type of multi-fidelity simulationmethod can greatly improve the prediction capability for the flow systems.

关键词： Complex flow system Coupling Jet engine Multi-fidelity Zooming

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Lubrication condition monitoring of journal bearings in diesel engine based on thermoelectricity

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Friction 2024年第11期12卷 2532-2547页

作者： Yuhao LV Hao LIU Zhigang CHEN Weijie CHANG Hui ZHANG Hulin LI Shanghai Jiao Tong University Shanghai 200240China National Key Laboratory of Marine Engine Science and Technology Shanghai 201108China Shanghai Marine Diesel Engine Research Institute Shanghai 201108China Hunan Aviation Powerplant Research Institute Aero Engine Corporation of ChinaHunan 412002China

There is still a lack of effective lubrication condition monitoring methods in the field of diesel *** paper proposes a novel thermoelectric approach to divide the lubrication state of ***,the generation mechanism of thermoelectric potential on bearings is ***,both experimental and simulation studies are done,and a strong correlation between lubrication and thermoelectric potential is *** film thickness and temperature are further confirmed as significant factors influencing thermoelectric ***,the thermoelectric potential increases with ***,a small film thickness ratio(when the film thickness ratio is less than 4)will suppress the thermoelectric *** typical lubrication states of bearings are distinguished through thermoelectric potential and supported by the Stribeck curve ***,the significant influence of lubrication on the bearing is confirmed through the analysis of surface morphology and composition.

关键词： journal bearing lubrication state,thermoelectric potential condition monitoring

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A review of modeling,simulation,and control technologies of altitude ground test facilities for control application

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Chinese Journal of aeronautics 2023年第9期36卷 38-62页

作者： Xitong PEI Xi WANG Jiashuai LIU Meiyin ZHU Zhihong DAN Ai HE Keqiang MIAO Louyue ZHANG Zheng XU Research Institute of Aero-Engine Beihang UniversityBeijing 100191China Science and Technology on Altitude Simulation Laboratory AECC Sichuan Gas Turbine EstablishmentMianyang 621703China School of Energy and Power Engineering Beihang UniversityBeijing 100191China Beihang Hangzhou Innovation Institute Yuhang Hangzhou 310023China Institute for Aero Engine Tsinghua UniversityBeijing 100084China Institute of Engineering Thermophysics Chinese Academy of SciencesBeijing 100190China

As the pivotal test equipment of aero-engines design,finalization,improvement,modification,etc.,the altitude Ground Test Facilities(AGTF)plays an important role in the research and development of the *** the rapid development of advanced high-performance aeroengine,the increasing demand of high-altitude simulation test is driving AGTF to improve its test ability and level of automation and *** modeling method,simulation tool,and control technology are the key factors to support the improvement of the AGTF control *** main purpose of this paper is to provide an overview of modeling methods,simulation tools,and control technologies in AGTF control system for future ***,it reviews the evolution of AGTF in the world,from the early formative stage to integration ***,the mathematical modeling method of AGTF for control application is ***,the simulation tools used in the AGTF control system are overviewed from numerical simulation to hardware-in-loop simulation and further to semi-physical ***,the control technologies used in the AGTF control system are summarized from single-variable control to multivariable integrated control,and from classical control theory to modern control ***,recommendations for future research are ***,this review article provides extensive literature information for the modeling,simulation,and control design of AGTF for control application.

关键词： altitude ground test facilities Control system Modeling and simulation Robust control Temperature and pressure control

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Impact of Stagger Angle Nonuniformity on Turbine aerodynamic Performance

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Journal of Thermal science 2010年第5期19卷 465-472页

作者： Weihao Zhang Zhengping Zou Shangneng Pan Huoxing Liu Huoxing Liu Wei Li National Key Laboratory of Science and Technology on Aero-Engines School of Jet Propulsion Beihang University Beijing 100191 China Aeroengine Numerical Simulation Research Center B eihang University Beijing 100191 China Chinese Aviation Powerplant Research Institute Zhuzhou 412002 China

The assembling error may lead to variation in stagger angles,which would affect the aerodynamic performance of the *** investigate this underlying effect,two parallel numerical experiments on two turbines with the same profile,but uniform and nonuniform vane stagger angle respectively,were conducted in both steady and unsteady *** results indicate that certain changes in the detailed flow field of the turbine occur when the stagger angles are nonuniform,further,the blade loading distribution of the vane and rotor become markedly different from that in uniform vane stagger angle *** these consequences caused by nonuniformity mentioned above enhance the unsteadiness of the flow,finally,the aerodynamic performance changes *** also shows that,compared with steady simulation,the unsteady numerical simulation is necessary in this investigation.

关键词： assembling error stagger angle nonuniformity turbine aerodynamic performance

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