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    Mitigation of Fretting Fatigue Damage in Blade and Disk Pressure Faces With Low Plasticity Burnishing

    Source: Journal of Engineering for Gas Turbines and Power:;2010:;volume( 132 ):;issue: 008::page 82105
    Author:
    Paul S. Prevéy
    ,
    Ravi A. Ravindranath
    ,
    Michael Shepard
    ,
    N. Jayaraman
    DOI: 10.1115/1.2943154
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Low plasticity burnishing (LPB) is now established as a surface enhancement technology capable of introducing through-thickness compressive residual stresses in the edges of gas turbine engine blades and vanes to mitigate foreign object damage (FOD). The “fatigue design diagram” (FDD) method has been described and demonstrated to determine the depth and magnitude of compression required to achieve the optimum high cycle fatigue strength, and to mitigate a given depth of damage characterized by the fatigue stress concentration factor, kf. LPB surface treatment technology and the FDD method have been combined to successfully mitigate a wide variety of surface damage ranging from FOD to corrosion pits in titanium and steel gas turbine engine compressor and fan components. LPB mitigation of fretting-induced damage in Ti–6Al–4V in laboratory samples has now been extended to fan and compressor components. LPB tooling technology recently developed to allow the processing of the pressure faces of fan and compressor blade dovetails and mating disk slots is described. Fretting-induced microcracks that form at the pressure face edge of bedding on both the blade dovetail and the dovetail disk slots in Ti-6-4 compressor components can now be arrested by the introduction of deep stable compression in conventional computer numerical control (CNC) machine tools during manufacture or overhaul. The compressive residual stress field design method employing the FDD approach developed at Lambda Technologies is described in application to mitigate fretting damage. The depth and magnitude of compression and the fatigue and damage tolerance achieved are presented. It was found that microcracks as deep as 0.030in.(0.75mm) large enough to be readily detected by current nondestructive inspection (NDI) technology can be fully arrested by LPB. The depth of compression achieved could allow NDI screening followed by LPB processing of critical components to reliably restore fatigue performance and extend component life.
    keyword(s): Pressure , Plasticity , Fatigue , Disks , Blades , Compression , Stress , Fatigue design , Fatigue damage , Compressors , Cycles , Microcracks , Stress concentration AND Residual stresses ,
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      Mitigation of Fretting Fatigue Damage in Blade and Disk Pressure Faces With Low Plasticity Burnishing

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    https://yetl.yabesh.ir/yetl1/handle/yetl/143129
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    • Journal of Engineering for Gas Turbines and Power

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    contributor authorPaul S. Prevéy
    contributor authorRavi A. Ravindranath
    contributor authorMichael Shepard
    contributor authorN. Jayaraman
    date accessioned2017-05-09T00:37:34Z
    date available2017-05-09T00:37:34Z
    date copyrightAugust, 2010
    date issued2010
    identifier issn1528-8919
    identifier otherJETPEZ-27125#082105_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/143129
    description abstractLow plasticity burnishing (LPB) is now established as a surface enhancement technology capable of introducing through-thickness compressive residual stresses in the edges of gas turbine engine blades and vanes to mitigate foreign object damage (FOD). The “fatigue design diagram” (FDD) method has been described and demonstrated to determine the depth and magnitude of compression required to achieve the optimum high cycle fatigue strength, and to mitigate a given depth of damage characterized by the fatigue stress concentration factor, kf. LPB surface treatment technology and the FDD method have been combined to successfully mitigate a wide variety of surface damage ranging from FOD to corrosion pits in titanium and steel gas turbine engine compressor and fan components. LPB mitigation of fretting-induced damage in Ti–6Al–4V in laboratory samples has now been extended to fan and compressor components. LPB tooling technology recently developed to allow the processing of the pressure faces of fan and compressor blade dovetails and mating disk slots is described. Fretting-induced microcracks that form at the pressure face edge of bedding on both the blade dovetail and the dovetail disk slots in Ti-6-4 compressor components can now be arrested by the introduction of deep stable compression in conventional computer numerical control (CNC) machine tools during manufacture or overhaul. The compressive residual stress field design method employing the FDD approach developed at Lambda Technologies is described in application to mitigate fretting damage. The depth and magnitude of compression and the fatigue and damage tolerance achieved are presented. It was found that microcracks as deep as 0.030in.(0.75mm) large enough to be readily detected by current nondestructive inspection (NDI) technology can be fully arrested by LPB. The depth of compression achieved could allow NDI screening followed by LPB processing of critical components to reliably restore fatigue performance and extend component life.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleMitigation of Fretting Fatigue Damage in Blade and Disk Pressure Faces With Low Plasticity Burnishing
    typeJournal Paper
    journal volume132
    journal issue8
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.2943154
    journal fristpage82105
    identifier eissn0742-4795
    keywordsPressure
    keywordsPlasticity
    keywordsFatigue
    keywordsDisks
    keywordsBlades
    keywordsCompression
    keywordsStress
    keywordsFatigue design
    keywordsFatigue damage
    keywordsCompressors
    keywordsCycles
    keywordsMicrocracks
    keywordsStress concentration AND Residual stresses
    treeJournal of Engineering for Gas Turbines and Power:;2010:;volume( 132 ):;issue: 008
    contenttypeFulltext
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