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Asbestos Exposure during Gasket Removal from aircraft engine

Occupational Diseases and Environmental Medicine 2024年第2期12卷 59-67页

作者： Charles L. Blake Kevin M. Guth Raymond D. Harbison Apex Companies Marietta USA Center for Environmental and Occupational Risk Analysis and Management College of Public Health University of South Florida Tampa USA

We have previously evaluated asbestos exposure associated with various maintenance procedures on light aircraft. The purpose of this study was to evaluate asbestos exposure during engine maintenance on light aircraft. This test was designed to evaluate the potential for asbestos exposure to mechanics and others who remove asbestos-containing engine gaskets from reciprocating style aircraft engines. Utilized in this test was an air cooled, horizontally opposed, aviation gasoline burning engine, assembled during 1986 and operated intermittently up into 2015, having accumulated 1680 hours run time. Nearly 75% of the asbestos-containing gaskets installed during 1986 were still in place at the time of testing. Chrysotile asbestos contents of such gaskets ranged from 55% to 60% by area, for those of sheet style and 5% by area, for the spiral wound metal/asbestos style. Despite the levels of effort required to effect gasket removals, the professional aircraft mechanic was not exposed to airborne asbestos fibers at the lower limits of sampling and analytical detection achieved;all of which were substantially less than the current Occupational Safety and Health Administration Permissible Exposure Limits for asbestos. The results of this testing indicate an absence of gasket related asbestos exposure risk to mechanics who work with light aircraft engines, including those having asbestos-containing gaskets. These results are consistent with the findings of Mlyarek and Van Orden who studied the asbestos exposure risk occasioned during overhaul of larger radial style reciprocating aircraft engines [1].

关键词： Asbestos Exposure Gaskets aircraft engine Friction Materials

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Fault diagnosis and isolation of the componentand sensor for aircraft engine

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航空动力学报 2012年第6期27卷 1432-1440页

作者： QIU Xiao-jie HUANG Jin-quan LU Feng LIU Nan College of Energy and Power engineering Nanjing University of Aeronautics and Astronautics Nanjing 210016 China

aircraft engine component and sensor fault detection and isolation approach was proposed,which included fault type detection module and component-sensor simultaneous fault isolation *** approach can not only distinguish among sensor fault,component fault and component-sensor simultaneous fault,but also isolate and locate sensor fault and the type of engine component fault when the engine component fault and the sensor faults occur *** double-threshold mechanism has been proposed,in which the fault diagnostic threshold changed with the sensor type and the engine condition,and it greatly improved the accuracy and robustness of sensor fault diagnosis *** results show that the approach proposed can diagnose and isolate the sensor and engine component fault with improved *** effectively improves the fault diagnosis ability of aircraft engine.

关键词： aircraft engine sensor fault engine component fault simultaneous fault diagnosis isolation double-threshold mechanism

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Approximate Nonlinear Modeling of aircraft engine Surge Margin Based on Equilibrium Manifold Expansion

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Chinese Journal of Aeronautics 2012年第5期25卷 663-674页

作者： LIU Xiaofeng ZHAO Lei School of Transportation Science and engineering Beihang UniversityBeijing 100191China

Stable operation of aircraft engine compressions is constrained by rotating surge. In this paper, an approximate nonlinear surge margin model of aircraft engine compression system by using equilibrium manifold is presented. Firstly, this paper gives an overview of the current state of modeling aerodynamic flow instabilities in engine compressors. Secondly, the expansion form of equilibrium manifold is introduced, and the choosing scheduling variable method is discussed. Then, this paper also gives the identification procedure of modeling the approximate nonlinear model. Finally, the modeling and simulations with high pressure （liP） compressor surge margin of the aircraft engine show that this real-time model has the same accuracy with the thermody- namic model, but has simpler structure and shorter computation time.

关键词： aircraft engine surge margin system identification equilibrium manifold scheduling variable perpendicular expan-sion

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3D modeling of transformation of gaseous pollutants in the high-pressure turbine of an aircraft engine

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Propulsion and Power Research 2020年第1期9卷 1-14页

作者： Trung Hieu Nguyen Phuong Nguyen-Tri Francois Garnier Department of Mechanical engineering École de Technologie Supérieure(ETS)MontrealQuebecH3C 1K3Canada Institute of Research and Development Duy Tan UniversityDa Nang550000Viet Nam Department of Chemistry Biochemistry and PhysicsUniversitédu QuébecàTrois-RivièresUniversity of QuebecTrois-Rivières(Québec)G9A 5H7Canada

aircraft emissions contribute to global climate change and regional air pollution near *** the formation and the transformation of emissions in the aircraft engine is essential to properly quantify the environmental impact and air ***,precise investigation of chemical process in the turbine is challenging because of the complexity of the transformation process in the complex flow relating to the moving blade at high temperature and high *** present here,the first published model study of 3D chemical formations inside a high-pressure turbine and first time to compare three numerical solutions(1D,2D and 3D calculations)of transformation of trace species inside an aircraft *** model has simulated the evolution of principal precursor pollutant gases(NOx and SOx)and other species(hydrogen,oxygen species and carbon oxides).Our results also indicated strong dissimilarities in chemical transformations of 3D *** comparing the three solutions,the results obtained showed that the difference of mole fractions of species can be under predicted by 75%between 1D and 2D calculations and in the comparison of 2D and 3D calculation,the under predicted difference may be 90%.

关键词： Gaseous pollutants High-pressure turbine aircraft engine 3D modeling

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Prediction of aircraft engine Health Condition Parameters Based on Ensemble ELM

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Journal of Harbin Institute of Technology(New Series) 2013年第3期20卷 7-11页

作者： Da Lei Shi-Sheng Zhong School of Mechatronics engineering Harbin Institute of Technology

In view of aircraft engine health condition parameters prediction,an ensemble ELM based prediction approach is proposed in this paper. In the approach,the AdaBoost. RT algorithm is improved to adjust its threshold adaptively,and is utilized as the basic framework to establish the ensemble learning model using ELM as weak learners. The proposed approach is evaluated through the prediction of the actual engine fuel flow deviation time series,and the results demonstrate that this approach is feasible for the prediction of aircraft engine health condition parameters. The performance of the proposed approach is compared with single ELM, single process neural network ( PNN) ,and a similar ensemble ELM based approach using AdaBoost. RT as basic framework. The results show that,the proposed approach is more accurate than single ELM and single PNN,and no worse than the ensemble prediction approach for contrast,furthermore,the given approach is more convenient for practical application. Therefore,the proposed approach is better suited to the prediction of aircraft engine health parameters.

关键词： ensemble learning AdaBoost. RT ELM aircraft engine condition parameter prediction

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A Data-Driven Anomaly Detection Approach for Acquiring Baseline of aircraft engine Measurement Data

A Data-Driven Anomaly Detection Approach for Acquiring Basel...

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第36届中国控制会议

作者： Hao Sun Ying-Qing Guo School of Power and Energy Northwestern Polytechnical University

ISBN: (纸本)9781538629185

This paper presents a data-driven anomaly detection architecture designed for acquiring baseline of aircraft engine measurement *** auto-regressive（AR） models are established to analyzing measurement data utilizing U-C algorithm to calculate model parameters,when the aircraft engine operating in *** nominal engine measurement data is extracted to update the previously obtained baseline and the established AR *** updated baseline reflect the current working condition of the engine and can be used in fault diagnosis *** to the oil system of a civil high bypass ratio engine,the simulation result shows that abnormal measurement data can be detected in time and the latest steady-state baseline information of the current measurement data is obtained.

关键词： aircraft engine Data-Driven Anomaly Detection Baseline Auto-Regressive

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GRADE-LIFE PROGNOSTIC MODEL OF aircraft engine BEARING

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Transactions of Nanjing University of Aeronautics and Astronautics 2012年第2期29卷 171-178页

作者：苗学问牛枞杨云韩磊洪杰空军装备研究院北京理工大学信息与电子学院北京航空航天大学能源与动力工程学院

Research on practical and verifiable prediction methods for the service life of bearings plays a critical role in improving the reliability and safety of aircraft engines. The concept of grade-life （GL） is introduced to de- scribe the service life of bearings. A GL prognostic model for aircraft engine bearings is proposed based on sup- port vector machine （SVM） and fuzzy logic inference. Firstly, the mathematical model is discussed to predict the physics-based GL （PGL）. Then, the diagnostic estimation model based on SVM is presented in detail to predict the empirical GL （EPL）. Thirdly, a fuzzy logic inference is adopted to fuse two GL predicted results. Finally, the GL prognostic model is verified by the run-to-failure data acquired from an accelerated life test of an aircraft bearing. The results show that the model provides a more practical and reliable prediction for the service life of bearings.

关键词： aircraft engine bearing grade-life fuzzy logic inference SVM

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Neural Networks Adaptive Control of aircraft engine Based on Genetic Algorithm

Neural Networks Adaptive Control of Aircraft Engine Based on...

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第26届中国控制与决策会议

作者： Hongmei Zhang Ziyun Dong Guangyan Xu Aerospace Faculty Shenyang Aerospace University Automation Department Shenyang Aerospace University

ISBN: (纸本)9781479937097

In this paper, a method of neural network adaptive control was proposed based on genetic algorithm（GA）. At first, genetic algorithm is applied to determine initial weights of neural networks（NNs）, and then NNs identifier is applied to real-time identify the model of engine. Moreover, the sensitivity information of the system is fed back to the NNs controller, which ensures the accuracy of the controller for the controlled object. For an aircraft turbojet engine, the control system is designed on the selected design point. The simulation results show that the control system not only has good quickness and less overshoot but also has strong anti-interference ability.

关键词： aircraft engine Genetic Algorithm Neural Networks Self-adaptation Control

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Design of Simulation Platform for Control System in aircraft engine

Design of Simulation Platform for Control System in Aircraft...

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第37届中国控制会议

作者： Linfeng Gou Zhidan Liu Aixia Liang Lulu Wang Zihan Zhou Northwestern Poly-Technical University School of Power and Energy

For the dilemma of lacking a convenient and generic Simulation Platform for aircraft engine Control System, A possible solution to design such a platform based on Simulink is proposed for purpose of modeling, controller design, visual programming and software development. First of all, the overall structure of the platform is put forward, followed by a piecewise linearization module to do the linearization;After that a set of linearized model is employed to represent nonlinearty of the real engine. Based on the model above, this platform is elevated to built controller with SUMT and simplex optimization method. The whole system is developed based on MATLAB/Simulink, as well as the simulations. The simulated results show the system behaves properly in modelling and controller design, and the platform is generic, flexible and easy to be expanded for further research.

关键词： aircraft engine Control system self-tuning design Simulation platform Piecewise linear model

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Study of Flow and Heat Transfer in an Ejector-Driven Swirl Anti-Icing Chamber

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Fluid Dynamics & Materials Processing 2024年第5期20卷 989-1014页

作者： Yi Tu Yuan Wu Yu Zeng Hunan University of Arts and Sciences Hunan Key Laboratory of Distributed Electric Propulsion Vehicle Control TechnologyChangde415000China Liaoning Provincial Key Laboratory of aircraft Ice Protection AVIC Aerodynamics Research InstituteShenyang110034China School of Aeronautic Science and engineering Beihang UniversityBeijing100191China

The formation of ice on the leading edge of aircraft engines is a serious issue,as it can have catastrophic *** Swirl Anti-Icing(SAI)system,driven by ejection,circulates hot fluid within a 360°annular chamber to heat the engine inlet lip surface and prevent *** study employs a validated Computational Fluid Dynamics(CFD)approach to study the impact of key geometric parameters of this system on flow and heat transfer characteristics within the anti-icing ***,the entropy generation rate and exergy efficiency are analyzed to assess the energy utilization in the *** research findings indicate that,within the considered flow range,reducing the nozzle specific areaφfrom 0.03061 to 0.01083 can enhance the ejection coefficient by over 60.7%.This enhancement increases the air circulating rate,thereby intensifying convective heat transfer within the SAI ***,the reduction inφalso leads to a significant increase in the required bleed air pressure and a higher entropy generation rate,indicating lower exergy *** nozzle angleθnotably affects the distribution of hot and cold spots on the lip surface of the SAI ***θfrom 0°to 20°reduces the maximum temperature difference on the anti-icing chamber surface by 60 K.

关键词： Swirl anti-icing heat transfer exergy efficiency hot and cold spot aircraft engine

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