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    Heat Transfer Augmentation Downstream of Rows of Various Dimple Geometries on the Suction Side of a Gas Turbine Airfoil

    Source: Journal of Turbomachinery:;2010:;volume( 132 ):;issue: 003::page 31010
    Author:
    Jason E. Dees
    ,
    Ronald S. Bunker
    ,
    David G. Bogard
    DOI: 10.1115/1.3149284
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Heat transfer coefficients were measured downstream of a row of shaped film cooling holes, as well as elliptical, diffuser, and teardrop shaped dimples, simulating depressions due to film coolant holes of different shapes. These features were placed on the suction side of a simulated gas turbine vane. The dimples were used as approximations to film cooling holes after the heat transfer levels downstream of active fan shaped film cooling holes was found to be independent of film cooling. The effects of the dimples were tested with varying approach boundary layers, freestream turbulence intensity, and Reynolds numbers. For the case of an untripped (transitional) approach boundary layer, all dimple shapes caused approximately a factor of 2 increase in heat transfer coefficient relative to the smooth baseline condition due to the dimples effectively causing boundary layer transition downstream. The exact augmentation varied depending on the dimple geometry: diffuser shapes causing the largest augmentation and teardrop shapes causing the lowest augmentation. For tripped (turbulent boundary layer) approach conditions, the dimple shapes all caused the same 20% augmentation relative to the smooth tripped baseline. The already turbulent nature of the tripped approach flow reduces the effect that the dimples have on the downstream heat transfer coefficient.
    keyword(s): Flow (Dynamics) , Heat transfer , Cooling , Turbulence , Suction , Boundary layers , Gas turbines , Shapes , Heat transfer coefficients , Diffusers , Airfoils , Reynolds number , Boundary layer turbulence AND Geometry ,
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      Heat Transfer Augmentation Downstream of Rows of Various Dimple Geometries on the Suction Side of a Gas Turbine Airfoil

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    http://yetl.yabesh.ir/yetl1/handle/yetl/144991
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    contributor authorJason E. Dees
    contributor authorRonald S. Bunker
    contributor authorDavid G. Bogard
    date accessioned2017-05-09T00:41:32Z
    date available2017-05-09T00:41:32Z
    date copyrightJuly, 2010
    date issued2010
    identifier issn0889-504X
    identifier otherJOTUEI-28764#031010_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/144991
    description abstractHeat transfer coefficients were measured downstream of a row of shaped film cooling holes, as well as elliptical, diffuser, and teardrop shaped dimples, simulating depressions due to film coolant holes of different shapes. These features were placed on the suction side of a simulated gas turbine vane. The dimples were used as approximations to film cooling holes after the heat transfer levels downstream of active fan shaped film cooling holes was found to be independent of film cooling. The effects of the dimples were tested with varying approach boundary layers, freestream turbulence intensity, and Reynolds numbers. For the case of an untripped (transitional) approach boundary layer, all dimple shapes caused approximately a factor of 2 increase in heat transfer coefficient relative to the smooth baseline condition due to the dimples effectively causing boundary layer transition downstream. The exact augmentation varied depending on the dimple geometry: diffuser shapes causing the largest augmentation and teardrop shapes causing the lowest augmentation. For tripped (turbulent boundary layer) approach conditions, the dimple shapes all caused the same 20% augmentation relative to the smooth tripped baseline. The already turbulent nature of the tripped approach flow reduces the effect that the dimples have on the downstream heat transfer coefficient.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleHeat Transfer Augmentation Downstream of Rows of Various Dimple Geometries on the Suction Side of a Gas Turbine Airfoil
    typeJournal Paper
    journal volume132
    journal issue3
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.3149284
    journal fristpage31010
    identifier eissn1528-8900
    keywordsFlow (Dynamics)
    keywordsHeat transfer
    keywordsCooling
    keywordsTurbulence
    keywordsSuction
    keywordsBoundary layers
    keywordsGas turbines
    keywordsShapes
    keywordsHeat transfer coefficients
    keywordsDiffusers
    keywordsAirfoils
    keywordsReynolds number
    keywordsBoundary layer turbulence AND Geometry
    treeJournal of Turbomachinery:;2010:;volume( 132 ):;issue: 003
    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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