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aero-engine Surge Fault Diagnosis Using Deep Neural Network

Computer Systems Science & engineering 2022年第7期42卷 351-360页

作者： Kexin Zhang Bin Lin Jixin Chen Xinlong Wu Chao Lu Desheng Zheng Lulu Tian School of Computer Science Southwest Petroleum UniversityChengdu610500China Sichuan Normal University Chengdu610066China AECC Sichuan Gas Turbine Establishment MianYang621700China Brunel University London UxbridgeMiddlesexUB83PHUnited Kingdom

Deep learning techniques have outstanding performance in feature extraction and modelﬁ*** theﬁeld of aero-engine fault diagnosis,the intro-duction of deep learning technology is of great signiﬁ*** aero-engine is the heart of the aircraft,and its stable operation is the primary guarantee of the *** order to ensure the normal operation of the aircraft,it is necessary to study and diagnose the faults of the *** the many engine fail-ures,the one that occurs more frequently and is more hazardous is the wheeze,which often poses a great threat toﬂight *** the basis of analyzing the mechanism of aero-engine surge,an aero-engine surge fault diagnosis method based on deep learning technology is *** this paper,key sensor data are obtained by analyzing different engine sensor *** aero-engine surge data-set acquisition algorithm(ASDA)is proposed to sample the fault and normal points to generate the training set,validation set and test *** on neural net-work models such as one-dimensional convolutional neural network(1D-CNN),convolutional neural network(RNN),and long-short memory neural network(LSTM),different neural network optimization algorithms are selected to achieve fault diagnosis and classiﬁ*** experimental results show that the deep learning technique has good effect in aero-engine surge fault *** aero-engine surge fault diagnosis network(ASFDN)proposed in this paper achieves better *** training,the network achieves more than 99%classiﬁcation accuracy for the test set.

关键词： aero-engine fault diagnosis surge vibration signal classiﬁcation deep learning

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Airside pressure drop characteristics of three analogous serpentine tube heat exchangers considering heat transfer for aero-engine cooling

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Chinese Journal of aeronautics 2022年第12期35卷 32-46页

作者： Yinlong LIU Guoqiang XU Yanchen FU Jie WEN Shaoshuai QI Lulu LYU Research Institute of aero-engine Beihang UniversityBeijing 100083China National Key Laboratory of Science and Technology on aero-engine aero-thermodynamics Beihang UniversityBeijing 100083China School of Energy and Power engineering Beihang UniversityBeijing 100083China Beihang Hangzhou Innovation Institute Yuhang Hangzhou 310023China China aerospace aerodynamics Technology Research Institute Beijing 100074China AECC Commercial Aircraft engine Co. Ltd.Shanghai 200241China

This study explores the design,analysis,and air pressure drop assessment of three analogous air–fuel heat exchangers consisting of thin serpentine tube bundles intended for use in high Mach number *** high speed flight,the compressor bleed air used to cool high temperature turbine blades and other hot components is too ***,aviation kerosene is applied to precool the compressor bleed air by means of novel air–fuel heat *** light and compact heat exchangers including dozens of in-line thin serpentine tube bundles were designed and manufactured,with little difference existing in aspects of tube pitches and outer diameters among three heat *** fuel flows inside a series of parallel stainless serpentine tubes(outer diameter:2.2,1.8,1.4 mm with 0.2 mm thickness),while the air externally flows normal to tube bundles and countercurrent with *** studies were carried out to investigate the airside pressure drop characteristics on isothermal states with the variation of air mass flow rates and inlet ***-isothermal measurements have also been performed to research the effect of heat transfer on pressure *** experimental results show that inlet temperatures have significant influence on pressure drops,and higher temperatures lead to higher pressure drops at the same mass flow *** hydraulic resistance coefficient decreases quickly with Reynolds number,and the descent rate slows down when Re>6000 for all three heat ***,the pressure drop on heat transfer states is less than that on isothermal states for the same average ***,the pressure drop through heat exchangers is greatly affected by attack angles and transverse pitches,and an asymmetric M-shaped velocity profile is generated in the crosssection of sector channels.

关键词： aero-engine Heat exchanger Heat transfer Pressure drop Serpentine tube

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A novel compilation method of comprehensive mission spectrum of aero-engine maneuvering load based on use-related mission segment

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Chinese Journal of aeronautics 2023年第3期36卷 161-170页

作者： Xuming NIU Qi LU Zhigang SUN Yingdong SONG Jiangsu Province Key Laboratory of aerospace Power System and College of Energy and Power engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016China Laboratory of aero-engine Thermal Environment and Structure Ministry of Industry and Information Technology College of Energy and Power EngineeringNanjing University of Aeronautics and AstronauticsNanjing 210016China College of Energy and Power engineering and State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China

Comprehensive Mission Spectrum(CMS)of an aero-engine can reflect the usage characteristics of the *** can provide load input for engine life prediction and accelerated mission *** this paper,a novel compilation method of CMS of aero-engine maneuvering load based on mission segment is ***,the use-related Typical Mission Segment(TMS)of maneuvering load is divided and identified according to spectral ***,the mathematical model of different kinds of TMS are established based on stochastic process ***,the CMS of maneuvering load is compiled based on *** proposed method can accurately quantify the compilation of *** compiled CMS shows good agreement with the original load *** to damage consistency inspection,the compiled CMS is consistent with the damage caused by the original load spectrum in terms of low cycle fatigue.

关键词： aero-engine Comprehensive mission spectrum Maneuvering load Spectrum compilation Typical mission segment

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An improved nonlinear onboard adaptive model for aero-engine performance control

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Chinese Journal of aeronautics 2023年第10期36卷 317-334页

作者： Qian CHEN Hanlin SHENG Tianhong ZHANG Jiangsu Province Key Laboratory of aerospace Power System College of Energy and Power EngineeringNanjing University of Aeronautics and AstronauticsNanjing 210016China

The onboard adaptive model can achieve the online real-time estimation of performance parameters that are difficult to measure in a real aero-engine,which is the key to realizing modelbased performance *** must possess satisfactory numerical stability and estimation ***,the positive definiteness of the state covariance matrix may be destroyed in filter estimation because of the existence of some uncertain factors,such as the accumulated measurement error,noise,and disturbance in the strongly nonlinear engine system,inevitably causing divergence of estimates of Cholesky decomposition-based Spherical Unscented Kalman Filter(SUKF).Therefore,this paper proposes an improved SUKF algorithm(iSUKF)and applies it to the performance degradation estimation of the *** to SUKF,the iSUKF mainly replaces the Cholesky decomposition with the Singular Value Decomposition(SVD),which is numerically stable without any strict requirement for the state covariance ***,a correction factor is designed to assess the measurement deviation between the real engine and the nonlinear onboard model to correct the state covariance matrix,thus maintaining better numerical stability of parameters estimated by the ***,an offline correction strategy is also proposed to eliminate the influence of the degradation of unestimated health parameters or the filter’s inadequate estimation of the coupled health *** action effectively promotes the onboard adaptive model’s estimation accuracy concerning the degradation of the engine’real health parameters and its performance ***,the simulation results show that the iSUKF can maintain the numerical stability of the filter’s estimation of health *** with the existing methods,the offline correction strategy improves the estimation accuracy of the iSUKF-based nonlinear onboard adaptive model for the performance parameters of the real engine by more than 50%.The proposed met

关键词： aero-engine Onboard adaptive model Spherical unscented Kalman filter Parameter estimation iSUKF

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Optimization of aero-engine pipeline for avoiding vibration based on length adjustment of straight-line segment

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Frontiers of Mechanical engineering 2022年第1期17卷 100-116页

作者： Wenhao JI Wei SUN Donghai WANG Zhonghua LIU School of Mechanical engineering and Automation Northeastern UniversityShenyang 110819China Key Laboratory of Vibration and Control of aero-Propulsion Systems Department of Education of China Northeastern UniversityShenyang 110819China Shenyang Area 2nd Military Representative Room of Air Force Equipment Department Shenyang 110043China

In the design and troubleshooting of aero-engine pipeline,the vibration reduction of the pipeline system is often achieved by adjusting the hoop layout,provided that the shape of pipeline remains ***,in reality,the pipeline system with the best antivibration performance may be obtained only by adjusting the pipeline *** this paper,a typical spatial pipeline is taken as the research object,the length of straight-line segment is taken as the design variable,and an innovative optimization method of avoiding vibration of aero-engine pipeline is *** relationship between straight-line segment length and parameters that determine the geometric characteristics of the pipeline,such as the position of key reference points,bending angle,and hoop position,are derived in *** on this,the parametric finite element model of the pipeline system is *** the maximum first-order natural frequency of pipeline as the optimization objective and introducing process constraints and vibration avoidance constraints,the optimization model of the pipeline system is *** genetic algorithm and the golden section algorithm are selected to solve the optimization model,and the relevant solution procedure is described in ***,two kinds of pipelines with different total lengths are selected to carry out a case *** on the analysis of the influence of straight-line segment length on the vibration characteristics of the pipeline system,the optimization methods developed in this paper are *** show that the developed optimization method can obtain the optimal single value or interval of the straight-line segment length while avoiding the excitation *** addition,the optimization efficiency of the golden section algorithm is remarkably higher than that of the genetic algorithm for length optimization of a single straight-line segment.

关键词： length adjustment spatial pipeline aero-engine vibration avoidance optimization genetic algorithm golden section algorithm

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aero-engine fault diagnosis applying new fast support vector algorithm

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航空动力学报 2012年第7期27卷 1604-1612页

作者： XU Qi-hua GENG Shuai SHI Jun College of Electronic engineering Huaihai Institute of Technology Lianyungang Jiangsu 222005 China No. 365 Institute Northwestern Polytechnical University Xi'an 710072 China

A new fast learning algorithm was presented to solve the large-scale support vector machine ( SVM ) training problem of aero-engine fault *** relative boundary vectors ( RBVs ) instead of all the original training samples were used for the training of the binary SVM fault *** pruning strategy decreased the number of final training sample significantly and can keep classification accuracy almost *** , the training time was shortened to 1 / 20compared with basic SVM *** , owing to the reduction of support vector number , the classification time was also *** sample aliasing existed , the aliasing sample points which were not of the same class were eliminated before the relative boundary vectors were *** , the samples near the relative boundary vectors were selected for SVM training in order to prevent the loss of some key sample points resulted from *** can improve classification accuracy effectively.A simulation example to classify 5classes of combination fault of aero-engine gas path components was finished and the total fault classification accuracy reached 96.1%.Simulation results show that this fast learning algorithm is effective , reliable and easy to be implemented for engineering application.

关键词： aero-engine support vector machines fault diagnosis large-scale training set relative boundary vector sample pruning

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aero-engine Thrust Estimation Based on Ensemble of Improved Wavelet Extreme Learning Machine

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Transactions of Nanjing University of aeronautics and Astronautics 2018年第2期35卷 290-299页

作者： Zhou Jun Zhang Tianhong Jiangsu Province Key Laboratory of aerospace Power Systems College of Energy and Power EngineeringNanjing University of Aeronautics and Astronautics

aero-engine direct thrust control can not only improve the thrust control precision but also save the operating cost by reducing the reserved margin in design and making full use of aircraft engine potential ***,it is a big challenge to estimate engine thrust *** tackle this problem,this paper proposes an ensemble of improved wavelet extreme learning machine(EW-ELM)for aircraft engine thrust *** learning machine(ELM)has been proved as an emerging learning technique with high *** the combination of ELM and wavelet theory has the both excellent properties,wavelet activation functions are used in the hidden nodes to enhance non-linearity dealing ***,as original ELM may result in ill-condition and robustness problems due to the random determination of the parameters for hidden nodes,particle swarm optimization(PSO)algorithm is adopted to select the input weights and hidden ***,the ensemble of the improved wavelet ELM is utilized to construct the relationship between the sensor measurements and *** simulation results verify the effectiveness and efficiency of the developed method and show that aero-engine thrust estimation using EW-ELM can satisfy the requirements of direct thrust control in terms of estimation accuracy and computation time.

关键词： aero-engine thrust estimation wavelet extreme learning machine particle swarm optimization neural network ensemble

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Experimental study of rotating gliding arc discharge plasma-assisted combustion in an aero-engine combustion chamber

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Chinese Journal of aeronautics 2019年第2期32卷 337-346页

作者： Liming HE Yi CHEN Jun DENG Jianping LEI Li FEI Pengfei LIU Science and Technology on Plasma Dynamics Laboratory Aeronautics and Astronautics Engineering CollegeAir Force Engineering University

The combustion chamber is the core component of an aero-engine, and affects its reliability and security operation, even the performance of the aircraft. In this work, a Plasma-Assisted Combustion(PAC) test platform was developed to validate the feasibility of using PAC actuators to enhance annular combustor performance. Two plans of PAC(rotating gliding arc discharge plasma) were designed, Assisted Combustion from Primary Holes(ACPH) and Assisted Combustion from Dilution Holes(ACDH). Comparative experiments and analysis between conventional combustion and PAC were conducted to study the effects of ACPH and ACDH on the performances including average outlet temperature, combustion efficiency, pattern factor under four different excessive air coefficients(0.8, 1, 2, and 4), and lean blowout performance at different inlet airflow velocities. Experimental results show that the combustion efficiency is improved after PAC compared with that in normal conditions, and the combustion efficiency of ACPH increases2.45%, 1.49%, 1.04%, and 0.47%, while it increases 2.75%, 1.67%, 1.36%, and 0.36% under ACDH conditions. The uniformity of the outlet temperature field and the lean blowout performance are improved after PAC. Especially for ACPH, the widening of the lean blowout limit is8.3%, 12.4%, 12.8%, and 25% respectively when the inlet velocity ranges from 60 m/s to120 m/s. These results offer new perspectives for using PAC devices to enhance aero-engine combustors' performances.

关键词： aero-engine Assisted combustion actuator Combustion chambers Plasma-Assisted Combustion Rotating gliding arc discharge

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Bifurcation analysis of aero-engine's rotor system under constant maneuver load

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Applied Mathematics and Mechanics(English Edition) 2015年第11期36卷 1417-1426页

作者： Lei HOU Yushu CHEN School of Astronautics Harbin Institute of Technology

When an aircraft is hovering or doing a dive-hike flight at a fixed speed, a constant additional inertial force will be induced to the rotor system of the aero-engine, which can be called a constant maneuver load. Take hovering as an example. A Jeffcott rotor system with a biased rotor and several nonlinear elastic supports is modeled, and the vibration characteristics of the rotor system under a constant maneuver load are analytically studied. By using the multiple-scale method, the differential equations of the system are solved, and the bifurcation equations are obtained. Then, the bifurcations of the system are analyzed by using the singularity theory for the two variables. In the EG-plane, where E refers to the eccentricity of the rotor and G represents the constant maneuver load, two hysteresis point sets and one double limit point set are obtained. The bifurcation diagrams are also plotted. It is indicated that the resonance regions of the two variables will shift to the right when the aircraft is maneuvering. Furthermore, the movement along the horizontal direction is faster than that along the vertical direction. Thus, the different overlapping modes of the two resonance regions will bring about different bifurcation modes due to the nonlinear coupling effects. This result lays a theoretical foundation for controlling the stability of the aero-engine＇s rotor system under a maneuver load.

关键词： constant maneuver load aero-engine Jeffcott rotor system two-variablesingularity bifurcation

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Application of multi-outputs LSSVR by PSO to the aero-engine model

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Journal of Systems engineering and Electronics 2009年第5期20卷 1153-1158页

作者： Lu Feng Huang Jinquan Qiu Xiaojie Coll. of Energy and Power engineering Nanjing Univ. of Aeronautics and Astronautics Nanjing 210016 P. R. China

Considering the modeling errors of on-board self-tuning model in the fault diagnosis of aero-engine, a new mechanism for compensating the model outputs is proposed. A discrete series predictor based on multi-outputs least square support vector regression （LSSVR） is applied to the compensation of on-board self-tuning model of aero-engine, and particle swarm optimization （PSO） is used to the kernels selection of multi-outputs LSSVR. The method need not reconstruct the model of aero-engine because of the differences in the individuals of the same type engines and engine degradation after use. The concrete steps for the application of the method are given, and the simulation results show the effectiveness of the algorithm.

关键词： aero-engine on-board self-tuning model multi-outputs least square support vector regression particle swarm optimization.

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