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    Turbine Blade Platform Film Cooling With Typical Stator-Rotor Purge Flow and Discrete-Hole Film Cooling 

    Source: Journal of Turbomachinery:;2009:;volume( 131 ):;issue: 004:;page 41004
    Author(s): Zhihong Gao; Diganta Narzary; Je-Chin Han
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: This paper is focused on the effect of film-hole configurations on platform film cooling. The platform is cooled by purge flow from a simulated stator-rotor seal combined with discrete-hole ...
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    Effect of a Cutback Squealer and Cavity Depth on Film-Cooling Effectiveness on a Gas Turbine Blade Tip 

    Source: Journal of Turbomachinery:;2008:;volume( 130 ):;issue: 002:;page 21002
    Author(s): Shantanu Mhetras; Diganta Narzary; Zhihong Gao; Je-Chin Han
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Film-cooling effectiveness from shaped holes on the near tip pressure side and cylindrical holes on the squealer cavity floor is investigated. The pressure side squealer rim wall is cut near ...
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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(s): Zhihong Gao; Diganta Narzary; Shantanu Mhetras; Je-Chin Han
    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 ...
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