Resupply hole of cooling air into gas turbine blade serpentine passage
AssigneeUnited Technologies Corporation
InventorsChristopher Whitfield, Carey Clum, Mark Borja
Life of this patent
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Abstract
An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges and extending in a radial direction. A serpentine cooling passage is provided between the pressure and suction side walls. A passageway adjoins a passage wall and is fluidly interconnected to an upstream turn that has radially spaced apart innermost and outermost contours. The innermost contour is provided at the wall. A resupply hole is configured to exit downstream from the innermost contour.
Claims19
An airfoil for a gas turbine engine comprising:
- pressure and suction side walls joined to one another at leading and trailing edges and extending in a radial direction, a serpentine cooling passage provided between the pressure and suction side walls, the serpentine cooling passage includes first, second and third passageways, the first and second passageways separated by a first wall and fluidly interconnected to one another by a first turn, the second and third passageways separated by a second wall and fluidly interconnected to one another by a second turn, the first and second walls bridging the pressure and suction side walls in a thickness direction of the airfoil, the second turn has radially spaced apart innermost and outermost contours, the innermost contour provided at the second wall, and a resupply hole fluidly interconnecting the first and third passageways through the first and second walls, the resupply hole configured to exit downstream from the innermost contour.
A gas turbine engine comprising:
- a compressor section;
- a combustor fluidly connected to the compressor section;
- a turbine section fluidly connected to the combustor, the turbine section includes:
- an array of turbine blades, each turbine blade includes an airfoil having pressure and suction side walls joined to one another at leading and trailing edges and extending in a radial direction, a serpentine cooling passage provided between the pressure and suction side walls, the serpentine cooling passage includes first, second and third passageways, the first and second passageways separated by a first wall and fluidly interconnected to one another by a first turn, the second and third passageways separated by a second wall and fluidly interconnected to one another by a second turn, the first and second walls bridging the pressure and suction side walls in a thickness direction of the airfoil, the second turn has radially spaced apart innermost and outermost contours, the innermost contour provided at the second wall, and a resupply hole fluidly interconnecting the first and third passageways through the first and second walls, the resupply hole configured to exit downstream from the innermost contour.
Dependencies are inferred from the claim text.