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    Heat Transfer and Flow on the First-Stage Blade Tip of a Power Generation Gas Turbine: Part 1—Experimental Results

    Source: Journal of Turbomachinery:;2000:;volume( 122 ):;issue: 002::page 263
    Author:
    Ronald S. Bunker
    ,
    Ali A. Ameri
    ,
    Jeremy C. Bailey
    DOI: 10.1115/1.555443
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: A combined experimental and computational study has been performed to investigate the detailed distribution of convective heat transfer coefficients on the first-stage blade tip surface for a geometry typical of large power generation turbines (>100 MW). This paper is concerned with the design and execution of the experimental portion of the study, which represents the first reported investigation to obtain nearly full surface information on heat transfer coefficients within an environment that develops an appropriate pressure distribution about an airfoil blade tip and shroud model. A stationary blade cascade experiment has been run consisting of three airfoils, the center airfoil having a variable tip gap clearance. The airfoil models the aerodynamic tip section of a high-pressure turbine blade with inlet Mach number of 0.30, exit Mach number of 0.75, pressure ratio of 1.45, exit Reynolds number based on axial chord of 2.57×106, and total turning of about 110 deg. A hue detection based liquid crystal method is used to obtain the detailed heat transfer coefficient distribution on the blade tip surface for flat, smooth tip surfaces with both sharp and rounded edges. The cascade inlet turbulence intensity level took on values of either 5 or 9 percent. The cascade also models the casing recess in the shroud surface ahead of the blade. Experimental results are shown for the pressure distribution measurements on the airfoil near the tip gap, on the blade tip surface, and on the opposite shroud surface. Tip surface heat transfer coefficient distributions are shown for sharp edge and rounded edge tip geometries at each of the inlet turbulence intensity levels. [S0889-504X(00)01902-4]
    keyword(s): Pressure , Flow (Dynamics) , Heat transfer , Clearances (Engineering) , Blades , Airfoils , Cascades (Fluid dynamics) , Heat transfer coefficients , Electric power generation , Energy generation , Turbines AND Turbulence ,
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      Heat Transfer and Flow on the First-Stage Blade Tip of a Power Generation Gas Turbine: Part 1—Experimental Results

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    http://yetl.yabesh.ir/yetl1/handle/yetl/124486
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    • Journal of Turbomachinery

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    contributor authorRonald S. Bunker
    contributor authorAli A. Ameri
    contributor authorJeremy C. Bailey
    date accessioned2017-05-09T00:03:39Z
    date available2017-05-09T00:03:39Z
    date copyrightApril, 2000
    date issued2000
    identifier issn0889-504X
    identifier otherJOTUEI-28676#263_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/124486
    description abstractA combined experimental and computational study has been performed to investigate the detailed distribution of convective heat transfer coefficients on the first-stage blade tip surface for a geometry typical of large power generation turbines (>100 MW). This paper is concerned with the design and execution of the experimental portion of the study, which represents the first reported investigation to obtain nearly full surface information on heat transfer coefficients within an environment that develops an appropriate pressure distribution about an airfoil blade tip and shroud model. A stationary blade cascade experiment has been run consisting of three airfoils, the center airfoil having a variable tip gap clearance. The airfoil models the aerodynamic tip section of a high-pressure turbine blade with inlet Mach number of 0.30, exit Mach number of 0.75, pressure ratio of 1.45, exit Reynolds number based on axial chord of 2.57×106, and total turning of about 110 deg. A hue detection based liquid crystal method is used to obtain the detailed heat transfer coefficient distribution on the blade tip surface for flat, smooth tip surfaces with both sharp and rounded edges. The cascade inlet turbulence intensity level took on values of either 5 or 9 percent. The cascade also models the casing recess in the shroud surface ahead of the blade. Experimental results are shown for the pressure distribution measurements on the airfoil near the tip gap, on the blade tip surface, and on the opposite shroud surface. Tip surface heat transfer coefficient distributions are shown for sharp edge and rounded edge tip geometries at each of the inlet turbulence intensity levels. [S0889-504X(00)01902-4]
    publisherThe American Society of Mechanical Engineers (ASME)
    titleHeat Transfer and Flow on the First-Stage Blade Tip of a Power Generation Gas Turbine: Part 1—Experimental Results
    typeJournal Paper
    journal volume122
    journal issue2
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.555443
    journal fristpage263
    journal lastpage271
    identifier eissn1528-8900
    keywordsPressure
    keywordsFlow (Dynamics)
    keywordsHeat transfer
    keywordsClearances (Engineering)
    keywordsBlades
    keywordsAirfoils
    keywordsCascades (Fluid dynamics)
    keywordsHeat transfer coefficients
    keywordsElectric power generation
    keywordsEnergy generation
    keywordsTurbines AND Turbulence
    treeJournal of Turbomachinery:;2000:;volume( 122 ):;issue: 002
    contenttypeFulltext
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    DSpace software copyright © 2002-2015  DuraSpace
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