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    Effect of Unheated Starting Lengths on Film Cooling Experiments

    Source: Journal of Turbomachinery:;2006:;volume( 128 ):;issue: 003::page 579
    Author:
    Sarah M. Coulthard
    ,
    Ralph J. Volino
    ,
    Karen A. Flack
    DOI: 10.1115/1.2184355
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The effect of an unheated starting length upstream of a row of film cooling holes was studied experimentally to determine its effect on heat transfer coefficients downstream of the holes. Cases with a single row of cylindrical film cooling holes inclined at 35deg to the surface of a flat plate were considered at blowing ratios of 0.25, 0.5, 1.0, and 1.5. For each case, experiments were conducted to determine the film-cooling effectiveness and the Stanton number distributions in cases with the surface upstream of the holes heated and unheated. Measurements were made using an infrared camera, thermocouples, and hot and cold-wire anemometry. Ratios were computed of the Stanton number with film cooling (Stf) to corresponding Stanton numbers in cases without film cooling (Sto), but the same surface heating conditions. Contours of these ratios were qualitatively the same regardless of the upstream heating conditions, but the ratios were larger for the cases with a heating starting length. Differences were most pronounced just downstream of the holes and for the lower blowing rate cases. Even 12 diameters downstream of the holes, the Stanton number ratios were 10–15% higher with a heated starting length. At higher blowing rates the differences between the heated and unheated starting length cases were not significant. The differences in Stanton number distributions are related to jet flow structures, which vary with blowing rate.
    keyword(s): Cooling AND Jets ,
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      Effect of Unheated Starting Lengths on Film Cooling Experiments

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    contributor authorSarah M. Coulthard
    contributor authorRalph J. Volino
    contributor authorKaren A. Flack
    date accessioned2017-05-09T00:21:57Z
    date available2017-05-09T00:21:57Z
    date copyrightJuly, 2006
    date issued2006
    identifier issn0889-504X
    identifier otherJOTUEI-28730#579_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/134837
    description abstractThe effect of an unheated starting length upstream of a row of film cooling holes was studied experimentally to determine its effect on heat transfer coefficients downstream of the holes. Cases with a single row of cylindrical film cooling holes inclined at 35deg to the surface of a flat plate were considered at blowing ratios of 0.25, 0.5, 1.0, and 1.5. For each case, experiments were conducted to determine the film-cooling effectiveness and the Stanton number distributions in cases with the surface upstream of the holes heated and unheated. Measurements were made using an infrared camera, thermocouples, and hot and cold-wire anemometry. Ratios were computed of the Stanton number with film cooling (Stf) to corresponding Stanton numbers in cases without film cooling (Sto), but the same surface heating conditions. Contours of these ratios were qualitatively the same regardless of the upstream heating conditions, but the ratios were larger for the cases with a heating starting length. Differences were most pronounced just downstream of the holes and for the lower blowing rate cases. Even 12 diameters downstream of the holes, the Stanton number ratios were 10–15% higher with a heated starting length. At higher blowing rates the differences between the heated and unheated starting length cases were not significant. The differences in Stanton number distributions are related to jet flow structures, which vary with blowing rate.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleEffect of Unheated Starting Lengths on Film Cooling Experiments
    typeJournal Paper
    journal volume128
    journal issue3
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.2184355
    journal fristpage579
    journal lastpage588
    identifier eissn1528-8900
    keywordsCooling AND Jets
    treeJournal of Turbomachinery:;2006:;volume( 128 ):;issue: 003
    contenttypeFulltext
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