Airfoil and method of cooling

Profil d'aube et procédé de refroidissement

Schaufelprofil und kühlverfahren

Abstract

An airfoil (21) for use in a gas turbine engine (10) is provided. The airfoil having: a pressure surface (52) and a suction surface (54) each extending axially from a leading edge (44) to a trailing edge (46) of the airfoil, at least one of the pressure surface, the suction surface, the leading edge and the trailing edge terminating at an edge (65; 80; 88; 96) of a tip section of the airfoil; a plurality of internal cooling conduits (60) located within the airfoil; and at least one cooling hole (62; 76; 86; 92) in fluid communication with at least one of the plurality of internal cooling channels, wherein the at least one cooling hole is aligned with an opening or diffuser (70; 78; 90; 94) that extends directly from the at least one cooling hole and wherein the opening or diffuser is formed in and extends through the edge of the tip section of the airfoil.

Claims

Description

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Patent Citations (3)

    Publication numberPublication dateAssigneeTitle
    US-2014030102-A1January 30, 2014General Electric CompanyTurbine bucket with notched squealer tip
    US-5192192-AMarch 09, 1993The United States Of America As Represented By The Secretary Of The Air ForceTurbine engine foil cap
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NO-Patent Citations (1)

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Cited By (0)

    Publication numberPublication dateAssigneeTitle