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    Effect of Inlet Flow Angle on Gas Turbine Blade Tip Film Cooling

    Source: Journal of Turbomachinery:;2009:;volume( 131 ):;issue: 003::page 31005
    Author:
    Zhihong Gao
    ,
    Diganta Narzary
    ,
    Shantanu Mhetras
    ,
    Je-Chin Han
    DOI: 10.1115/1.2987235
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The influence of incidence angle on film-cooling effectiveness is studied for a cutback squealer blade tip. Three incidence angles are investigated −0 deg at design condition and ±5 deg at off-design conditions. Based on mass transfer analogy, the film-cooling effectiveness is measured with pressure sensitive paint techniques. The film-cooling effectiveness distribution on the pressure side near tip region, squealer cavity floor, and squealer rim tip is presented for the three incidence angles at varying blowing ratios. The average blowing ratio is controlled to be 0.5, 1.0, 1.5, and 2.0. One row of shaped holes is provided along the pressure side just below the tip; two rows of cylindrical film-cooling holes are arranged on the blade tip in such a way that one row is offset to the suction side profile and the other row is along the camber line. The pressure side squealer rim wall is cut near the trailing edge to allow the accumulated coolant in the cavity to escape and cool the tip trailing edge. The internal coolant-supply passages of the squealer tipped blade are modeled similar to those in the GE-E3 rotor blade. Test is done in a five-blade linear cascade in a blow-down facility with a tip gap clearance of 1.5% of the blade span. The Mach number and turbulence intensity level at the cascade inlet were 0.23 and 9.7%, respectively. It is observed that the incidence angle affects the coolant jet direction on the pressure side near tip region and the blade tip. The film-cooling effectiveness distribution is also altered. The peak of laterally averaged effectiveness is shifted upstream or downstream depending on the off-design incidence angle. The film cooling effectiveness inside the tip cavity can increase by 25% with the positive incidence angle. However, in general, the overall area-averaged film-cooling effectiveness is not significantly changed by the incidence angles in the range of study.
    keyword(s): Pressure , Flow (Dynamics) , Cooling , Coolants , Blades , Cavities , Design , Suction AND Gas turbines ,
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      Effect of Inlet Flow Angle on Gas Turbine Blade Tip Film Cooling

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    http://yetl.yabesh.ir/yetl1/handle/yetl/142159
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    • Journal of Turbomachinery

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    contributor authorZhihong Gao
    contributor authorDiganta Narzary
    contributor authorShantanu Mhetras
    contributor authorJe-Chin Han
    date accessioned2017-05-09T00:35:47Z
    date available2017-05-09T00:35:47Z
    date copyrightJuly, 2009
    date issued2009
    identifier issn0889-504X
    identifier otherJOTUEI-28755#031005_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/142159
    description abstractThe influence of incidence angle on film-cooling effectiveness is studied for a cutback squealer blade tip. Three incidence angles are investigated −0 deg at design condition and ±5 deg at off-design conditions. Based on mass transfer analogy, the film-cooling effectiveness is measured with pressure sensitive paint techniques. The film-cooling effectiveness distribution on the pressure side near tip region, squealer cavity floor, and squealer rim tip is presented for the three incidence angles at varying blowing ratios. The average blowing ratio is controlled to be 0.5, 1.0, 1.5, and 2.0. One row of shaped holes is provided along the pressure side just below the tip; two rows of cylindrical film-cooling holes are arranged on the blade tip in such a way that one row is offset to the suction side profile and the other row is along the camber line. The pressure side squealer rim wall is cut near the trailing edge to allow the accumulated coolant in the cavity to escape and cool the tip trailing edge. The internal coolant-supply passages of the squealer tipped blade are modeled similar to those in the GE-E3 rotor blade. Test is done in a five-blade linear cascade in a blow-down facility with a tip gap clearance of 1.5% of the blade span. The Mach number and turbulence intensity level at the cascade inlet were 0.23 and 9.7%, respectively. It is observed that the incidence angle affects the coolant jet direction on the pressure side near tip region and the blade tip. The film-cooling effectiveness distribution is also altered. The peak of laterally averaged effectiveness is shifted upstream or downstream depending on the off-design incidence angle. The film cooling effectiveness inside the tip cavity can increase by 25% with the positive incidence angle. However, in general, the overall area-averaged film-cooling effectiveness is not significantly changed by the incidence angles in the range of study.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleEffect of Inlet Flow Angle on Gas Turbine Blade Tip Film Cooling
    typeJournal Paper
    journal volume131
    journal issue3
    journal titleJournal of Turbomachinery
    identifier doi10.1115/1.2987235
    journal fristpage31005
    identifier eissn1528-8900
    keywordsPressure
    keywordsFlow (Dynamics)
    keywordsCooling
    keywordsCoolants
    keywordsBlades
    keywordsCavities
    keywordsDesign
    keywordsSuction AND Gas turbines
    treeJournal of Turbomachinery:;2009:;volume( 131 ):;issue: 003
    contenttypeFulltext
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