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    Effects of Deposits on Film Cooling of a Vane Endwall Along the Pressure Side

    Source: Journal of Turbomachinery:;2008:;volume( 130 ):;issue: 004::page 41006
    Author:
    N. Sundaram
    ,
    M. D. Barringer
    ,
    K. A. Thole
    DOI: 10.1115/1.2812332
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Film cooling is influenced by surface roughness and depositions that occur from contaminants present in the hot gas path, whether that film cooling occurs on the vane itself or on the endwalls associated with the vanes. Secondary flows in the endwall region also affect the film-cooling performance along the endwall. An experimental investigation was conducted to study the effect of surface deposition on film cooling along the pressure side of a first-stage turbine vane endwall. A large-scale wind tunnel with a turbine vane cascade was used to perform the experiments. The vane endwall was cooled by an array of film-cooling holes along the pressure side of the airfoil. Deposits having a semielliptical shape were placed along the pressure side to simulate individual row and multiple row depositions. Results indicated that the deposits lowered the average adiabatic effectiveness levels downstream of the film-cooling rows by deflecting the coolant jets toward the vane endwall junction on the pressure side. Results also indicated that there was a steady decrease in adiabatic effectiveness levels with a sequential increase in the number of rows with the deposits.
    keyword(s): Pressure , Flow (Dynamics) , Cooling AND Coolants ,
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      Effects of Deposits on Film Cooling of a Vane Endwall Along the Pressure Side

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/139455
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    • Journal of Turbomachinery

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    contributor authorN. Sundaram
    contributor authorM. D. Barringer
    contributor authorK. A. Thole
    date accessioned2017-05-09T00:30:44Z
    date available2017-05-09T00:30:44Z
    date copyrightOctober, 2008
    date issued2008
    identifier issn0889-504X
    identifier otherJOTUEI-28750#041006_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/139455
    description abstractFilm cooling is influenced by surface roughness and depositions that occur from contaminants present in the hot gas path, whether that film cooling occurs on the vane itself or on the endwalls associated with the vanes. Secondary flows in the endwall region also affect the film-cooling performance along the endwall. An experimental investigation was conducted to study the effect of surface deposition on film cooling along the pressure side of a first-stage turbine vane endwall. A large-scale wind tunnel with a turbine vane cascade was used to perform the experiments. The vane endwall was cooled by an array of film-cooling holes along the pressure side of the airfoil. Deposits having a semielliptical shape were placed along the pressure side to simulate individual row and multiple row depositions. Results indicated that the deposits lowered the average adiabatic effectiveness levels downstream of the film-cooling rows by deflecting the coolant jets toward the vane endwall junction on the pressure side. Results also indicated that there was a steady decrease in adiabatic effectiveness levels with a sequential increase in the number of rows with the deposits.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleEffects of Deposits on Film Cooling of a Vane Endwall Along the Pressure Side
    typeJournal Paper
    journal volume130
    journal issue4
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.2812332
    journal fristpage41006
    identifier eissn1528-8900
    keywordsPressure
    keywordsFlow (Dynamics)
    keywordsCooling AND Coolants
    treeJournal of Turbomachinery:;2008:;volume( 130 ):;issue: 004
    contenttypeFulltext
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