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    Thermal-Mechanical Life Prediction System for Anisotropic Turbine Components

    Source: Journal of Turbomachinery:;2006:;volume( 128 ):;issue: 002::page 240
    Author:
    F. J. Cunha
    ,
    M. K. Chyu
    ,
    M. T. Dahmer
    DOI: 10.1115/1.2137740
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Modern gas turbine engines provide large amounts of thrust and withstand severe thermal-mechanical conditions during the load and mission operations characterized by cyclic transients and long dwell times. All these operational factors can be detrimental to the service life of turbine components and need careful consideration. Engine components subject to the harshest environments are turbine high-pressure vanes and rotating blades. Therefore, it is necessary to develop a turbine component three-dimensional life prediction system, which accounts for mission transients, anisotropic material properties, and multi-axial, thermal-mechanical, strain, and stress fields. This paper presents a complete life prediction approach for either commercial missions or more complex military missions, which includes evaluation of component transient metal temperatures, resolved maximum shear stresses and strains, and subsequent component life capability for fatigue and creep damage. The procedure is based on considering all of the time steps in the mission profile by developing a series of extreme points that envelop every point in the mission. Creep damage is factored into the component capability by debiting thermal-mechanical accumulated cycles using the traditional Miner’s rule for accumulated fatigue and creep damage. Application of this methodology is illustrated to the design of the NASA Energy Efficient Engine (E3) high pressure turbine blade with operational load shakedown leading to stress relaxation on the external hot surfaces and potential state of overstress in the inner cold rib regions of the airfoil.
    keyword(s): Creep , Fatigue , Temperature , Stress , Shear (Mechanics) , Design , Turbine components , Blades , Cycles , Airfoils , Metals , Equations AND Crystals ,
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      Thermal-Mechanical Life Prediction System for Anisotropic Turbine Components

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    http://yetl.yabesh.ir/yetl1/handle/yetl/134841
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    contributor authorF. J. Cunha
    contributor authorM. K. Chyu
    contributor authorM. T. Dahmer
    date accessioned2017-05-09T00:21:58Z
    date available2017-05-09T00:21:58Z
    date copyrightApril, 2006
    date issued2006
    identifier issn0889-504X
    identifier otherJOTUEI-28728#240_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/134841
    description abstractModern gas turbine engines provide large amounts of thrust and withstand severe thermal-mechanical conditions during the load and mission operations characterized by cyclic transients and long dwell times. All these operational factors can be detrimental to the service life of turbine components and need careful consideration. Engine components subject to the harshest environments are turbine high-pressure vanes and rotating blades. Therefore, it is necessary to develop a turbine component three-dimensional life prediction system, which accounts for mission transients, anisotropic material properties, and multi-axial, thermal-mechanical, strain, and stress fields. This paper presents a complete life prediction approach for either commercial missions or more complex military missions, which includes evaluation of component transient metal temperatures, resolved maximum shear stresses and strains, and subsequent component life capability for fatigue and creep damage. The procedure is based on considering all of the time steps in the mission profile by developing a series of extreme points that envelop every point in the mission. Creep damage is factored into the component capability by debiting thermal-mechanical accumulated cycles using the traditional Miner’s rule for accumulated fatigue and creep damage. Application of this methodology is illustrated to the design of the NASA Energy Efficient Engine (E3) high pressure turbine blade with operational load shakedown leading to stress relaxation on the external hot surfaces and potential state of overstress in the inner cold rib regions of the airfoil.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleThermal-Mechanical Life Prediction System for Anisotropic Turbine Components
    typeJournal Paper
    journal volume128
    journal issue2
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.2137740
    journal fristpage240
    journal lastpage250
    identifier eissn1528-8900
    keywordsCreep
    keywordsFatigue
    keywordsTemperature
    keywordsStress
    keywordsShear (Mechanics)
    keywordsDesign
    keywordsTurbine components
    keywordsBlades
    keywordsCycles
    keywordsAirfoils
    keywordsMetals
    keywordsEquations AND Crystals
    treeJournal of Turbomachinery:;2006:;volume( 128 ):;issue: 002
    contenttypeFulltext
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    DSpace software copyright © 2002-2015  DuraSpace
    نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
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