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    Effect of Midpassage Gap, Endwall Misalignment, and Roughness on Endwall Film-Cooling

    Source: Journal of Turbomachinery:;2006:;volume( 128 ):;issue: 001::page 62
    Author:
    N. D. Cardwell
    ,
    N. Sundaram
    ,
    K. A. Thole
    DOI: 10.1115/1.2098791
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: To maintain acceptable turbine airfoil temperatures, film cooling is typically used whereby coolant, extracted from the compressor, is injected through component surfaces. In manufacturing a turbine, the first stage vanes are cast in either single airfoils or double airfoils. As the engine is assembled, these singlets or doublets are placed in a turbine disk in which there are inherent gaps between the airfoils. The turbine is designed to allow outflow of high-pressure coolant rather than hot gas ingestion. Moreover, it is quite possible that the singlets or doublets become misaligned during engine operation. It has also become of interest to the turbine community as to the effect of corrosion and deposition of particles on component heat transfer. This study uses a large-scale turbine vane in which the following two effects are investigated: the effect of a midpassage gap on endwall film cooling and the effect of roughness on endwall film cooling. The results indicate that the midpassage gap was found to have a significant effect on the coolant exiting from the combustor-turbine interface slot. When the gap is misaligned, the results indicate a severe reduction in the film-cooling effectiveness in the case where the pressure side endwall is below the endwall associated with the suction side of the adjacent vane.
    keyword(s): Pressure , Flow (Dynamics) , Cooling , Surface roughness , Coolants , Turbines , Suction AND Combustion chambers ,
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      Effect of Midpassage Gap, Endwall Misalignment, and Roughness on Endwall Film-Cooling

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    contributor authorN. D. Cardwell
    contributor authorN. Sundaram
    contributor authorK. A. Thole
    date accessioned2017-05-09T00:22:01Z
    date available2017-05-09T00:22:01Z
    date copyrightJanuary, 2006
    date issued2006
    identifier issn0889-504X
    identifier otherJOTUEI-28726#62_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/134869
    description abstractTo maintain acceptable turbine airfoil temperatures, film cooling is typically used whereby coolant, extracted from the compressor, is injected through component surfaces. In manufacturing a turbine, the first stage vanes are cast in either single airfoils or double airfoils. As the engine is assembled, these singlets or doublets are placed in a turbine disk in which there are inherent gaps between the airfoils. The turbine is designed to allow outflow of high-pressure coolant rather than hot gas ingestion. Moreover, it is quite possible that the singlets or doublets become misaligned during engine operation. It has also become of interest to the turbine community as to the effect of corrosion and deposition of particles on component heat transfer. This study uses a large-scale turbine vane in which the following two effects are investigated: the effect of a midpassage gap on endwall film cooling and the effect of roughness on endwall film cooling. The results indicate that the midpassage gap was found to have a significant effect on the coolant exiting from the combustor-turbine interface slot. When the gap is misaligned, the results indicate a severe reduction in the film-cooling effectiveness in the case where the pressure side endwall is below the endwall associated with the suction side of the adjacent vane.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleEffect of Midpassage Gap, Endwall Misalignment, and Roughness on Endwall Film-Cooling
    typeJournal Paper
    journal volume128
    journal issue1
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.2098791
    journal fristpage62
    journal lastpage70
    identifier eissn1528-8900
    keywordsPressure
    keywordsFlow (Dynamics)
    keywordsCooling
    keywordsSurface roughness
    keywordsCoolants
    keywordsTurbines
    keywordsSuction AND Combustion chambers
    treeJournal of Turbomachinery:;2006:;volume( 128 ):;issue: 001
    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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