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    Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade With Single or Double Squealer

    Source: Journal of Turbomachinery:;2003:;volume( 125 ):;issue: 004::page 778
    Author:
    C. Pang Lee
    ,
    Ronald S. Bunker
    ,
    Robert Boyle
    ,
    Jae Su Kwak
    ,
    Jaeyong Ahn
    ,
    Raymond Gaugler
    ,
    Je-Chin Han
    DOI: 10.1115/1.1626684
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid-crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the camber line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the camber line and the pressure side, and (f) the camber line and the suction side, respectively. Tests were performed on a five-bladed linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1×106 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5%, and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.
    keyword(s): Pressure , Suction , Blades , Heat transfer coefficients , Gas turbines , Heat transfer AND Liquid crystals ,
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      Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade With Single or Double Squealer

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/129232
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    • Journal of Turbomachinery

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    contributor authorC. Pang Lee
    contributor authorRonald S. Bunker
    contributor authorRobert Boyle
    contributor authorJae Su Kwak
    contributor authorJaeyong Ahn
    contributor authorRaymond Gaugler
    contributor authorJe-Chin Han
    date accessioned2017-05-09T00:11:38Z
    date available2017-05-09T00:11:38Z
    date copyrightOctober, 2003
    date issued2003
    identifier issn0889-504X
    identifier otherJOTUEI-28706#778_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/129232
    description abstractDetailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid-crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the camber line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the camber line and the pressure side, and (f) the camber line and the suction side, respectively. Tests were performed on a five-bladed linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1×106 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5%, and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleHeat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade With Single or Double Squealer
    typeJournal Paper
    journal volume125
    journal issue4
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.1626684
    journal fristpage778
    journal lastpage787
    identifier eissn1528-8900
    keywordsPressure
    keywordsSuction
    keywordsBlades
    keywordsHeat transfer coefficients
    keywordsGas turbines
    keywordsHeat transfer AND Liquid crystals
    treeJournal of Turbomachinery:;2003:;volume( 125 ):;issue: 004
    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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