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    Molten Particulate Impact on Tailored Thermal Barrier Coatings for Gas Turbine Engine

    Source: Journal of Engineering for Gas Turbines and Power:;2018:;volume( 140 ):;issue: 002::page 22601
    Author:
    Ghoshal, Anindya
    ,
    Murugan, Muthuvel
    ,
    Walock, Michael J.
    ,
    Nieto, Andy
    ,
    Barnett, Blake D.
    ,
    Pepi, Marc S.
    ,
    Swab, Jeffrey J.
    ,
    Zhu, Dongming
    ,
    Kerner, Kevin A.
    ,
    Rowe, Christopher R.
    ,
    Shiao, Chi-Yu (Michael)
    ,
    Hopkins, David A.
    ,
    Gazonas, George A.
    DOI: 10.1115/1.4037599
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Commercial/military fixed-wing aircraft and rotorcraft engines often have to operate in significantly degraded environments consisting of sand, dust, ash, and other particulates. Marine gas turbine engines are subjected to salt spray, while the coal-burning industrial power generation turbines are subjected to fly ash. The presence of solid particles in the working fluid medium has an adverse effect on the durability of these engines as well as performance. Typical turbine blade damages include blade coating wear, sand glazing, calcia–magnesia–alumina–silicate (CMAS) attack, oxidation, and plugged cooling holes, all of which can cause rapid performance deterioration including loss of aircraft. This research represents the complex thermochemomechanical fluid structure interaction problem of semimolten particulate impingement and infiltration onto ceramic thermal barrier coatings (TBCs) into its canonical forms. The objective of this research work is to understand the underpinning interface science of interspersed graded ceramic/metal and ceramic/ceramic composites at the grain structure level for robust coatings and bulk material components for vehicle propulsion systems. This research enhances our understanding of the fundamental relationship between interface properties and the thermomechanical behavior in dissimilar materials for materials by design systems, and creates the ability to develop and fabricate materials with targeted macroscale properties as a function of their interfacial behavior. This project creates a framework to enable the engineered design of solid–solid and liquid–solid interfaces in dissimilar functionalized materials to establish a paradigm shift toward science from the traditional empiricism in engineering TBCs and high temperature highly loaded bulk materials. An integrated approach of modeling and simulation, characterization, fabrication, and validation to solve the fundamental questions of interface mechanisms which affect the properties of novel materials will be validated to guide component material solutions to visionary 2040+ military vehicle propulsion systems.
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      Molten Particulate Impact on Tailored Thermal Barrier Coatings for Gas Turbine Engine

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    contributor authorGhoshal, Anindya
    contributor authorMurugan, Muthuvel
    contributor authorWalock, Michael J.
    contributor authorNieto, Andy
    contributor authorBarnett, Blake D.
    contributor authorPepi, Marc S.
    contributor authorSwab, Jeffrey J.
    contributor authorZhu, Dongming
    contributor authorKerner, Kevin A.
    contributor authorRowe, Christopher R.
    contributor authorShiao, Chi-Yu (Michael)
    contributor authorHopkins, David A.
    contributor authorGazonas, George A.
    date accessioned2019-02-28T10:57:21Z
    date available2019-02-28T10:57:21Z
    date copyright10/3/2017 12:00:00 AM
    date issued2018
    identifier issn0742-4795
    identifier othergtp_140_02_022601.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4251139
    description abstractCommercial/military fixed-wing aircraft and rotorcraft engines often have to operate in significantly degraded environments consisting of sand, dust, ash, and other particulates. Marine gas turbine engines are subjected to salt spray, while the coal-burning industrial power generation turbines are subjected to fly ash. The presence of solid particles in the working fluid medium has an adverse effect on the durability of these engines as well as performance. Typical turbine blade damages include blade coating wear, sand glazing, calcia–magnesia–alumina–silicate (CMAS) attack, oxidation, and plugged cooling holes, all of which can cause rapid performance deterioration including loss of aircraft. This research represents the complex thermochemomechanical fluid structure interaction problem of semimolten particulate impingement and infiltration onto ceramic thermal barrier coatings (TBCs) into its canonical forms. The objective of this research work is to understand the underpinning interface science of interspersed graded ceramic/metal and ceramic/ceramic composites at the grain structure level for robust coatings and bulk material components for vehicle propulsion systems. This research enhances our understanding of the fundamental relationship between interface properties and the thermomechanical behavior in dissimilar materials for materials by design systems, and creates the ability to develop and fabricate materials with targeted macroscale properties as a function of their interfacial behavior. This project creates a framework to enable the engineered design of solid–solid and liquid–solid interfaces in dissimilar functionalized materials to establish a paradigm shift toward science from the traditional empiricism in engineering TBCs and high temperature highly loaded bulk materials. An integrated approach of modeling and simulation, characterization, fabrication, and validation to solve the fundamental questions of interface mechanisms which affect the properties of novel materials will be validated to guide component material solutions to visionary 2040+ military vehicle propulsion systems.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleMolten Particulate Impact on Tailored Thermal Barrier Coatings for Gas Turbine Engine
    typeJournal Paper
    journal volume140
    journal issue2
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.4037599
    journal fristpage22601
    journal lastpage022601-10
    treeJournal of Engineering for Gas Turbines and Power:;2018:;volume( 140 ):;issue: 002
    contenttypeFulltext
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