YaBeSH Engineering and Technology Library

    • Journals
    • PaperQuest
    • YSE Standards
    • YaBeSH
    • Login
    View Item 
    •   YE&T Library
    • ASME
    • Journal of Turbomachinery
    • View Item
    •   YE&T Library
    • ASME
    • Journal of Turbomachinery
    • View Item
    • All Fields
    • Source Title
    • Year
    • Publisher
    • Title
    • Subject
    • Author
    • DOI
    • ISBN
    Advanced Search
    JavaScript is disabled for your browser. Some features of this site may not work without it.

    Archive

    Experimental Study on Film Cooling Effectiveness of Blade With Chevron-Shaped Holes Under Wake Influence

    Source: Journal of Turbomachinery:;2021:;volume( 143 ):;issue: 008::page 081014-1
    Author:
    Li, Ji-Chen
    ,
    Zhu, Hui-Ren
    ,
    Liu, Cun-Liang
    ,
    Ye, Lin
    ,
    Zhou, Dao-En
    DOI: 10.1115/1.4050449
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Gas turbines have been widely used. With the continuous improvement of the performance of gas turbines, the turbine inlet temperature has greatly exceeded the heat-resistance limit of the turbine blade material, so advanced cooling technology is required. The film cooling effectiveness distribution over the blade under the effect of wake was obtained by the pressure-sensitive paint (PSP) technique. The test blade has five rows of chevron film holes on the pressure side, three rows of cylindrical film holes on the leading edge, and three rows of chevron film holes on the suction side. The mainstream Reynolds number is 130,000 based on the blade chord length, and the mainstream turbulence intensity is 2.7%. The upstream wake was simulated by the spoken-wheel type wake generator. The film cooling effectiveness was measured at three wake Strouhal numbers (0, 0.12, and 0.36) and three mass flux ratios (MFR1, MFR2, and MFR3). The results show that the increase of mass flux ratio leads to a decrease of the film cooling effectiveness on the suction surface. In the wake condition, the effect of mass flux ratio is weakened. Wake leads to a marked decrease of the film cooling effectiveness over most blade surface except for the surface near leading edge on the pressure surface. In the high mass flux ratio condition, the effect of wake on the film cooling effectiveness is weakened on the suction surface and strengthened on the pressure surface.
    • Download: (754.0Kb)
    • Show Full MetaData Hide Full MetaData
    • Get RIS
    • Item Order
    • Go To Publisher
    • Price: 5000 Rial
    • Statistics

      Experimental Study on Film Cooling Effectiveness of Blade With Chevron-Shaped Holes Under Wake Influence

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/4278993
    Collections
    • Journal of Turbomachinery

    Show full item record

    contributor authorLi, Ji-Chen
    contributor authorZhu, Hui-Ren
    contributor authorLiu, Cun-Liang
    contributor authorYe, Lin
    contributor authorZhou, Dao-En
    date accessioned2022-02-06T05:53:34Z
    date available2022-02-06T05:53:34Z
    date copyright5/3/2021 12:00:00 AM
    date issued2021
    identifier issn0889-504X
    identifier otherturbo_143_8_081014.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4278993
    description abstractGas turbines have been widely used. With the continuous improvement of the performance of gas turbines, the turbine inlet temperature has greatly exceeded the heat-resistance limit of the turbine blade material, so advanced cooling technology is required. The film cooling effectiveness distribution over the blade under the effect of wake was obtained by the pressure-sensitive paint (PSP) technique. The test blade has five rows of chevron film holes on the pressure side, three rows of cylindrical film holes on the leading edge, and three rows of chevron film holes on the suction side. The mainstream Reynolds number is 130,000 based on the blade chord length, and the mainstream turbulence intensity is 2.7%. The upstream wake was simulated by the spoken-wheel type wake generator. The film cooling effectiveness was measured at three wake Strouhal numbers (0, 0.12, and 0.36) and three mass flux ratios (MFR1, MFR2, and MFR3). The results show that the increase of mass flux ratio leads to a decrease of the film cooling effectiveness on the suction surface. In the wake condition, the effect of mass flux ratio is weakened. Wake leads to a marked decrease of the film cooling effectiveness over most blade surface except for the surface near leading edge on the pressure surface. In the high mass flux ratio condition, the effect of wake on the film cooling effectiveness is weakened on the suction surface and strengthened on the pressure surface.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleExperimental Study on Film Cooling Effectiveness of Blade With Chevron-Shaped Holes Under Wake Influence
    typeJournal Paper
    journal volume143
    journal issue8
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.4050449
    journal fristpage081014-1
    journal lastpage081014-8
    page8
    treeJournal of Turbomachinery:;2021:;volume( 143 ):;issue: 008
    contenttypeFulltext
    DSpace software copyright © 2002-2015  DuraSpace
    نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
    yabeshDSpacePersian
     
    DSpace software copyright © 2002-2015  DuraSpace
    نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
    yabeshDSpacePersian