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US 2016/0102561 A1Published application
Gas turbine engine turbine blade tip cooling
AssigneeUnited Technologies Corporation
InventorsBrandon W. Spangler, Laurie L. Burstynski
Life of this patent
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Abstract
An airfoil for a gas turbine engine includes pressure and suction walls that are spaced apart from one another and joined at leading and trailing edges to provide an airfoil that has an exterior surface that extends in a radial direction to a tip. A film cooling hole is provided in the tip and extends at an angle relative to the radial direction. The film cooling hole includes a diffuser.
Claims20
An airfoil for a gas turbine engine comprising:
- pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip;
- and
- a film cooling hole provided in the tip extending at an angle relative to the radial direction, the film cooling hole includes a diffuser.
An airfoil for a gas turbine engine comprising:
- pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip;
- and
- a shelf provided in at least one of the pressure and suction side walls at the tip, and a film cooling hole is provided in the shelf and extends at an angle relative to the radial direction, the film cooling hole includes a diffuser.
Dependencies are inferred from the claim text.