Airfoil tip pocket with augmentation features
A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge. The airfoil extends to a tip. A tip pocket is formed in the tip and terminates prior to the trailing edge. A heat transfer augmentation device is formed in the tip pocket.
1. A component, comprising:
an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, said airfoil extending to a tip;
a tip pocket formed in said tip and terminating prior to said trailing edge, wherein said tip pocket includes a suction side lip, a pressure side lip, a leading edge lip and a trailing edge lip that extend radially outwardly from a floor;
a heat transfer augmentation device formed in said tip pocket, wherein said heat transfer augmentation device includes a ramp that divides said floor of said tip pocket into radially offset floor portions, said ramp is contoured such that said ramp slants at an angle between said radially offset floor portions, said ramp is formed on said floor of said tip pocket, and said floor portions extend from said suction side lip to said pressure side lip; and
a plurality of cooling holes that fluidly connect said tip pocket to at least one internal cooling cavity formed inside said airfoil.
2. The component as recited in claim 1 , wherein said heat transfer augmentation device extends between said suction side lip and said pressure side lip.
3. The component as recited in claim 1 , wherein said ramp extends between said pressure and suction sidewalls, and said ramp and each of said radially offset floor portions are spaced apart from a radially outermost portion of said tip.
4. A gas turbine engine, comprising:
an airfoil including:
a tip pocket formed at a tip of said airfoil, said tip pocket extending from a position near a leading edge of said airfoil to a position that is upstream from a trailing edge of said airfoil, wherein said tip pocket includes a suction side lip, a pressure side lip, a leading edge lip and a trailing edge lip that extend radially outwardly from a floor; and
at least one heat transfer augmentation device formed in said tip pocket;
wherein said at least one heat transfer augmentation device includes a ramp that divides said floor of said tip pocket into radially offset floor portions, said ramp is contoured such that said ramp slants at an angle between said radially offset floor portions, said ramp is formed on said floor of said tip pocket, said floor portions extend from said suction side lip to said pressure side lip, and said at least one heat transfer augmentation device terminates prior to said tip.
5. The gas turbine engine as recited in claim 4 , wherein said at least one heat transfer augmentation device is formed on a pressure side wall of said tip pocket.
6. The component as recited in claim 4 , comprising a plurality of cooling holes that fluidly connect said tip pocket to at least one internal cooling cavity formed inside said airfoil, wherein said ramp extends between pressure and suction sidewalls of said tip pocket, and said ramp and each of said radially offset floor portions are spaced apart from a radially outermost portion of said tip.
7. A method of cooling a gas turbine engine component, comprising:
communicating a cooling fluid into a tip pocket formed at a tip of an airfoil, wherein said tip pocket includes a suction side lip, a pressure side lip, a leading edge lip and a trailing edge lip that extend radially outwardly from a floor;
temporarily blocking the cooling fluid within the tip pocket with at least one heat transfer augmentation device, wherein said at least one heat transfer augmentation device includes a ramp that divides said floor of said tip pocket into radially offset floor portions, said ramp is contoured between said radially offset floor portions such that said ramp slants at an angle between said radially offset floor portions, said ramp is formed on said floor of said tip pocket, and said floor portions extend from said suction side lip to said pressure side lip; and
expelling the cooling fluid from the tip pocket into a gas stream.
8. The method as recited in claim 7 , comprising communicating fluid from a plurality of cooling holes to said tip pocket, said plurality of cooling holes fluidly connecting said tip pocket to at least one internal cooling cavity formed inside said airfoil, wherein said ramp extends between pressure and suction sidewalls of said tip pocket, and said ramp and each of said radially offset floor portions are spaced apart from a radially outermost portion of said tip.