Airfoil tip pocket with augmentation features
A component for a gas turbine engine 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 extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.
1. A component for a gas turbine engine comprising:
an airfoil extending in a chordwise direction between a leading edge and a trailing edge and in a thickness direction between a pressure sidewall and a suction sidewall that meet together at both the leading edge and the trailing edge, the airfoil extending in a radial direction from a platform to a tip;
a tip pocket formed in the tip and terminating prior to the trailing edge;
wherein the tip pocket includes a suction side lip, a pressure side lip, a leading edge lip and a trailing edge lip that each extend outwardly in the radial direction from a floor to the tip;
one or more heat transfer augmentation devices formed in the tip pocket, the one or more heat transfer augmentation devices including at least one rib along the floor extending in a circumferential direction between the suction side lip and the pressure side lip such that the at least one rib is spaced apart from the tip at the pressure and suction side lips, and the at least one rib extending from at least one of the suction side lip and the pressure side lip; and
a plurality of cooling holes defined in the floor that fluidly connect the tip pocket to at least one internal cooling cavity formed inside the airfoil.
2. The component as recited in claim 1 , wherein the airfoil is a rotatable turbine blade.
3. The component as recited in claim 2 , wherein the at least one rib includes a plurality of ribs distributed along the floor.
4. The component as recited in claim 3 , wherein the plurality of cooling holes includes a first cooling hole defined in the floor at a position between the leading edge lip and a forwardmost one of the plurality of ribs.
5. The component as recited in claim 3 , wherein each rib of the plurality of ribs is a chevron pointing towards the leading edge lip or the trailing edge lip.
6. The component as recited in claim 3 , wherein each rib of the plurality of ribs is dimensioned to taper towards a central axis of the tip pocket to establish a valley.
7. The component as recited in claim 6 , wherein the plurality of cooling holes are distributed along the central axis.
8. A component for a gas turbine engine comprising:
an airfoil extending in a chordwise direction between a leading edge and a trailing edge and in a thickness direction between a pressure sidewall and a suction sidewall that meet together at both the leading edge and the trailing edge, the airfoil extending in a radial direction from a platform to a tip;
a tip pocket formed in the tip and terminating prior to the trailing edge;
wherein the tip pocket includes a suction side lip, a pressure side lip, a leading edge lip and a trailing edge lip that each extend outwardly in the radial direction from a floor to the tip;
one or more heat transfer augmentation devices formed in the tip pocket, the one or more heat transfer augmentation devices including at least one rib along the floor extending in a circumferential direction between the suction side lip and the pressure side lip such that the at least one rib is spaced apart from the tip at the pressure and suction side lips;
a plurality of cooling holes defined in the floor that fluidly connect the tip pocket to at least one internal cooling cavity formed inside the airfoil; and
wherein the at least one rib includes a plurality of ribs distributed along the floor, and each rib of the plurality of ribs spans an entire distance between the suction side lip and the pressure side lip.
9. The component as recited in claim 8 , wherein the plurality of cooling holes includes a first cooling hole defined in the floor at a position between the leading edge lip and a forwardmost one of the plurality of ribs.
10. The component as recited in claim 9 , wherein the first cooling hole is angled relative to the floor.
11. The component as recited in claim 8 , wherein each rib of the plurality of ribs is a trip strip.
12. The component as recited in claim 8 , wherein each rib of the plurality of ribs is a chevron pointing towards the leading edge lip or the trailing edge lip.
13. The component as recited in claim 12 , wherein the chevron points towards the leading edge lip.
14. The component as recited in claim 12 , wherein the chevron points towards the trailing edge lip.
15. The component as recited in claim 8 , wherein the airfoil is a rotatable turbine blade.
16. The component as recited in claim 8 , wherein each rib of the plurality of ribs is dimensioned to taper towards a central axis of the tip pocket to establish a valley.
17. The component as recited in claim 16 , wherein the plurality of cooling holes are distributed along the central axis.
18. The component as recited in claim 16 , wherein the valley is aligned with the central axis relative to the circumferential direction.
19. A component for a gas turbine engine comprising:
an airfoil extending in a chordwise direction between a leading edge and a trailing edge and in a thickness direction between a pressure sidewall and a suction sidewall that meet together at both the leading edge and the trailing edge, the airfoil extending in a radial direction from a platform to a tip;
a tip pocket formed in the tip and terminating prior to the trailing edge;
wherein the tip pocket includes a suction side lip, a pressure side lip, a leading edge lip and a trailing edge lip that each extend outwardly in the radial direction from a floor to the tip;
one or more heat transfer augmentation devices formed in the tip pocket, the one or more heat transfer augmentation devices including at least one rib along the floor extending in a circumferential direction between the suction side lip and the pressure side lip such that the at least one rib is spaced apart from the tip at the pressure and suction side lips;
a plurality of cooling holes defined in the floor that fluidly connect the tip pocket to at least one internal cooling cavity formed inside the airfoil; and
wherein the one or more heat transfer augmentation devices includes a first heat transfer augmentation device and a second heat transfer augmentation device interconnected by the at least one rib, and the first and second heat transfer augmentation devices extend in the radial direction from the at least one rib to respective ones of the suction side lip and the pressure side lip.
20. The component as recited in claim 19 , wherein the airfoil is a rotatable turbine blade.