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2024 3rd International Conference on Energy and Power Engineering, EPE-AEIC 2024

作者： Hou, Liang Zhang, Benben Zhao, Hao Tang, Zhili College of Aerospace Engineering Nanjing University of Aeronautics and Astronautics Jiangsu Nanjing210016 China Science and Technology on Altitude Simulation Laboratory Sichuan Gas Turbine Establishment Aero Engine Corporation of China Sichuan Mianyang621000 China

Numerical simulation of a high-altitude chamber is a preliminary step for ground testing of a high-altitude chamber. In this paper, the three-dimensional simulation model is established based on the real structure of a high-altitude chamber and aero-engine with an irregular stern, and then the three-dimensional numerical simulation is carried out to obtain the flow field characteristics in the chamber and the engine performance data under different working conditions. The calculation results show that the irregular stern structure can effectively reduce the backflow area inside the chamber, but it will lead to an increase in the unevenness of pressure and temperature distribution inside the chamber. The irregular stern structure can also cause a loss of 1.138% to 1.925% in engine thrust. © Published under licence by IOP Publishing Ltd.

关键词： Engines

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Effect of showerhead jet deflection on full-surface film cooling effectiveness of turbine blade

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Applied Thermal Engineering 2025年 274卷

作者： Tianliang, Zhou Lin, Ye Haonan, Yan Weijiang, Xu Fan, Zhang Cunliang, Liu School of Power and Energy Northwestern Polytechnical University Shaanxi Xi'an710129 China Science and Technology on Altitude Simulation Laboratory Sichuan Mianyang621000 China Science and Technology on Space Physics Laboratory China Academy of Launch Vehicle Technology Beijing100076 China

This study investigates film cooling effectiveness (η) on a turbine blade featuring seven rows of cylindrical holes using Pressure-Sensitive Paint (PSP) and numerical simulations. The influences of mass flow ratio (MFR = 1.29 %∼5.29 %), density ratio (DR = 1.0, 1.5, 2.8), and turbulence intensity (Tu = 8 %, 12 %, 16 %) are systematically explored. Results indicate that increasing DR notably improves η, especially at the leading edge, by enhancing coolant adherence. Meanwhile, raising MFR enhances downstream film coverage but can induce film blow-off, primarily on the suction side. The influence of Tu on η is noticeable within a limited range (Tu ≤ 12 %), beyond which further increases show diminishing effects. A modified SST k–ω turbulence model (MIX model) was used, providing predictions consistent with experimental measurements. The findings clarify how leading-edge coolant jets influence downstream cooling through momentum interactions, guiding practical cooling design improvements. © 2025

关键词： Turbine components

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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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Active disturbance rejection intake pressure control of aeropropulsion systems test facility with adaptive parameter b0

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Aerospace science and technology 2025年 163卷

作者： Xu, Zhuang Zhang, Hehong Zhai, Chao Xiao, Gaoxi Qian, Qiumeng Huang, Feng College of Computer and Data Science Fuzhou University Fuzhou350108 China Wuhan430074 China School of Electrical and Electronic Engineering Nanyang Technological University Singapore639798 Singapore Science and Technology on Altitude Simulation Laboratory AECC Sichuan Gas Turbine Establishment Mianyang621703 China School of Mechanical Engineering and Automation Fuzhou University Fuzhou350108 China

Establishing a precise intake pressure environment in the aeropropulsion systems test facility (ASTF) is critical for evaluating aeroengines' flight characteristics. The model-partial and robust active disturbance rejection control (ADRC), that is extended state observer (ESO)-based controller, has become a favorable solution to the complex intake pressure control system. The parameter b0, as the estimated value of the closed-loop system control gain b under the ADRC paradigm, significantly influences ADRC performances, evidenced by extensive flight tests. In this work, an enhanced ADRC with an adaptive parameter b0 is proposed to improve the control quality of the intake pressure. In particular, the simplified model of b is utilized to dynamically adjust b0. Meanwhile, the differential signals obtained from a tracking differentiator (TD) are applied to further improve the responsiveness of b0. The stable region of b0 is theoretically analyzed by using the time delay estimation technique, and the quantitative relationship between b0 and disturbance observation ability of ESO is given. Experimental results demonstrate that the proposed controller can effectively suppress the valve swing amplitude in steady state and reduce the maximum pressure error in transitional state, with improvement rates of 50% and 62%, respectively. © 2025 Elsevier Masson SAS

关键词： Disturbance rejection

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Two freedom linear parameter varying μ synthesis control for flight environment testbed

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Chinese Journal of Aeronautics 2019年第5期32卷 1204-1214页

作者： Meiyin ZHU Xi WANG Zhihong DAN Song ZHANG Xitong PEI School of Energy and Power Engineering Beihang University Collaborative Innovation Center for Advanced Aero-Engine Science and Technology on Altitude Simulation Laboratory

To solve the problem of robust servo performance of Flight Environment Testbed(FET)of altitude Ground Test Facilities(AGTF) over the whole operational envelope, a two-degree-offreedom μ synthesis method based on Linear Parameter Varying(LPV) schematic is proposed, and meanwhile a new structure frame of μ synthesis control on two degrees of freedom with double integral and weighting functions is presented, which constitutes a core support part of the paper. Aimed at the problem of reference command's rapid change, one freedom feed forward is adopted, while another freedom output feedback is used to meet good servo tracking as well as disturbance and noise rejection; furthermore, to overcome the overshoot problem and acquire dynamic tuning,the integral is introduced in inner loop, and another integral controller is used in outer loop in order to guarantee steady errors; additionally, two performance weighting functions are designed to achieve robust specialty and control energy limit considering the uncertainties in system. As the schedule parameters change over large flight envelope, the stability of closed-loop LPV system is proved using Lyapunov inequalities. The simulation results show that the relative tracking errors of temperature and pressure are less than 0.5% with LPV μ synthesis controller. Meanwhile, compared with non-LPV μ synthesis controller in large uncertainty range, the proposed approach in this research can ensure robust servo performance of FET over the whole operational envelope.

关键词： altitude ground test facilities Flight environment testbed Linear parameter varying Robust control Two-degree-of-freedom μ Synthesis

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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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Multi-dimensional simulations for extensive off-design conditions of gas turbines by iterative-coupled methods using different characteristic maps of coaxial compressor and turbine

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Case Studies in Thermal Engineering 2025年 72卷

作者： Weimin Deng Guangming Ren Linyuan Jia Zuojun Wei Yuchun Chen Xiaohua Gan School of Power and Energy Northwestern Polytechnical University Xi'an 710072 China Department of Mechanics and Aerospace Engineering Southern University of Science and Technology Shenzhen 518055 China Science and Technology on Altitude Simulation Laboratory Mianyang 621000 China Shenzhen Key Laboratory of Wide-Speed-Range and Variable-Density Continuous Wind Tunnel Southern University of Science and Technology Shenzhen 518000 China National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine Xi'an 710129 China

Multi-dimensional simulations offer a complementary numerical platform to gas turbine experimentation, generating supportive data for training adaptation and artificial intelligence models. However, the application of iterative-coupled simulations to extensive off-design conditions depends significantly on the accuracy of generic characteristic maps, particularly near choke and stall regions. In this study, multi-dimensional simulation based on iterative-coupled models using three different sets of maps was developed. Based on experimental speed characteristics data, the standard deviation of performance parameters simulated from the three iterative-coupled models was found to be less than 10 −3 . Further analysis reveals the convergence consistent traits that the different characteristic maps used in the iterative-coupled simulations only affect convergence speed and scope and do not impact the final convergence results. To apply iterative-coupled simulations to extensive off-design conditions, a self-moving strategy based on the convergence consistent traits of different characteristic maps was developed. The iterative-coupled simulations using the self-moving strategy have an extensive convergence scope, including adjustable-nozzle-area conditions (0.0013–0.008 m 2 , 78 %–479 %) and adjustable-power-extraction conditions (0–16 kW, 0 %–80 %). This demonstrates that the self-moving strategy for inexact generic characteristic maps can apply iterative-coupled simulations to extensive off-design, compared to the CLM with exact specific characteristic maps.

关键词： Iterative-coupled simulations Component-level model Adaptation method Gas turbine Thermodynamics Computational fluid dynamics

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Blade Self-excited Vibration with Identification of Fan Using Microphone Array 3

Blade Self-excited Vibration with Identification of Fan Usin...

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3rd International Conference on Sensing, Measurement and Data Analytics in the Era of Artificial Intelligence, ICSMD 2022

作者： Wen, Bi Qiao, Baijie Wang, Yanan Li, Zhendong Chen, Xuefeng Science and Technology on Altitude Simulation Laboratory Mianyang China School of Mechanical Engineering Xi'An Jiaotong University Xi'an China

ISBN: (纸本)9781665492812

The identification of blade self-excited vibration on a fan is attached to great importance for aero-engine operation safety. A non-contact method based on acoustic measurement is proposed to identify blade self-excited vibration via the run-up test, where a circular microphone array is arranged in the inlet section of a three-stage fan. The test results at 6880r/min present that the asynchronous aerodynamic excitation frequency has a connection with the asynchronous blade vibration frequency. In order to reveal the connection between sound pressure fluctuations and blade vibration in asynchronous vibration phenomena, the acoustic mode decomposition are carried out. The experimental results shows that the fan blade exists asynchronous vibration when the dominant acoustic mode order decomposed at the asynchronous aerodynamic excitation frequency is the same as the nodal diameter. A brief formula is provided to reveal the connection of sound signals to identify asynchronous vibrations. © 2022 IEEE.

关键词： Acoustic boundary Fan Microphone array Self-excited vibration Traveling wave

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Framework Design and Key Technologies of Intelligent Management and Control Platform for altitude simulation Test Facility 12

Framework Design and Key Technologies of Intelligent Managem...

引用

12th Asia Conference on Mechanical and Aerospace Engineering, ACMAE 2021

作者： Qiao, Yanping Zhao, Wanli Li, Kai Zhang, Cong Guo, Yingqing School of Power and Energy Northwestern Polytechnical University Xi'an710072 China Science and Technology on Altitude Simulation Laboratory Mianyang621700 China

In this paper, based on the technologies such as intelligent operation and maintenance, data mining, etc., a design framework for the intelligent management and control platform of aero-engine altitude simulation test facility was proposed. Aiming at the problems of low data utilization rate of aero-engine altitude simulation test facility and insufficient level of intelligent control of the test process, with the current advanced experience in large-scale equipment management and control, an intelligent management and control platform for altitude simulation test facility can be constructed to effectively ensure the safety of test equipment. Improve test efficiency. The key technologies such as baseline modelling and database construction involved in the platform are summarized in order to realize the intelligent management of altitude simulation test facility, test data, software resources and the coordinated operation of test equipment, and promote the intelligent development of aero-engine altitude simulation test. © Published under licence by IOP Publishing Ltd.

关键词： Data mining

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Evaluation of Equipment Performance for altitude Test Facility Flight Environment simulation System 12

Evaluation of Equipment Performance for Altitude Test Facili...

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2022 12th International Workshop on Computer science and Engineering, WCSE 2022

作者： Li, Kai Zhao, Wanli Qiao, Yanping Guo, Yingqing Zhou, Qifan School of Power and Energy Northwestern Polytechnical University Xi'an710072 China Science and Technology on Altitude Simulation Laboratory Mianyang621700 China

ISBN: (纸本)9789811839597

Based on the predictive maintenance requirements of aero-engine altitude Test Facility (ATF) equipment, a test equipment performance evaluation method (PCA-SPR) combining principal component analysis (PCA) and statistical pattern recognition (SPR) is proposed. It uses the PCA method to reduce the dimensionality of the equipment features, and recognizes the equipment status based on SPR. Then it defines the equipment health indicators based on the sample similarity theory, and achieves the quantitative evaluation of the equipment status. This paper takes the special control valve of ATF as the research object. Based on the simulation platform of the ATF flight environment simulation system, the valve performance degradation mode is studied and the valve degradation simulation is performed. The proposed PCA-SPR algorithm is applied to the valve performance evaluation to verify the applicability of the algorithm. © 2022 WCSE. All Rights Reserved.

关键词： Principal component analysis

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