Gas turbine engine airfoil squealer pocket cooling hole configuration

Patent metadata

Field	Value
Publication number	US-10053992-B2
Application number	US-201514790231-A
Country	US
Kind code	B2
Filing date	Jul 2, 2015
Priority date	Jul 2, 2015
Publication date	Aug 21, 2018
Grant date	Aug 21, 2018

Abstract

A gas turbine engine airfoil includes a body that provides an exterior airfoil surface that extends in a radial direction to a tip. The exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction. The tip includes a squealer pocket that has a recess surface. A cooling passage is arranged in the body. Each of the cooling holes extends from an inlet at the cooling passage to an outlet at the recessed surface. The inlet and outlet are arranged at an angle in an angular direction relative to the recessed surface. The angular direction is toward at least one of the forward and aft directions.

First claim

What is claimed is:

1. A gas turbine engine airfoil comprising:
a body that provides an exterior airfoil surface that extends in a radial direction to a tip, the exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction, the exterior airfoil surface includes pressure and suction sides joined at the leading and trailing edges, the tip includes a squealer pocket that has a recessed surface, a cooling passage is arranged in the body, and cooling holes, each of the cooling holes extends from a respective inlet at the cooling passage to a respective outlet at the recessed surface, the cooling holes including first and second sets of cooling holes, the first set of cooling holes comprising all of the cooling holes nearest the pressure side and the second set of cooling holes comprising all of the cooling holes nearest the suction side, the respective inlet and outlet of each cooling hole are arranged at an angle in an angular direction relative to the recessed surface, the angular direction is toward at least one of the forward and aft directions, wherein the angular directions of all of the first set of cooling holes are arranged only toward the aft direction, and the angular direction of all of the second set of cooling holes are arranged only toward the forward direction.

2. The airfoil according to claim 1 , wherein the angle is a first angle in a range of between 10° and 90°.

3. The airfoil according to claim 1 , wherein the tip is configured to receive a flow path fluid in a flow direction, and the cooling holes extend in a longitudinal direction that is at a second angle of 90°+/−60° with respect to the flow direction.

4. The airfoil according to claim 1 , wherein the body is a turbine blade.

5. The airfoil according to claim 1 , wherein the tip includes multiple squealer pockets.

6. The airfoil according to claim 1 , wherein the tip includes a partial tip shelf.

7. The airfoil according to claim 1 , wherein the tip includes a full tip shelf.

8. A gas turbine engine airfoil comprising:
a body that provides an exterior airfoil surface that extends in a radial direction to a tip, the exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction, the exterior airfoil surface includes pressure and suction sides joined at the leading and trailing edges, the tip includes a squealer pocket that has a recessed surface, a cooling passage is arranged in the body, and cooling holes, each of the cooling holes extends from a respective inlet at the cooling passage to a respective outlet at the recessed surface, the cooling holes including first and second sets of cooling holes, the first set of cooling holes comprising all of the cooling holes nearest the pressure side and the second set of cooling holes comprising all of the cooling holes nearest the suction side, the respective inlet and outlet of each cooling hole are arranged at an angle in an angular direction relative to the recessed surface, the angular direction is toward at least one of the forward and aft directions, wherein the angular directions of all of the first set of cooling holes are arranged only toward one of the forward and aft directions, and the angular direction of all of the second set of cooling holes are arranged only toward the other of the forward and aft directions, wherein the cooling holes are arranged in an arc, and the angular direction of each of the cooling holes is arranged toward an adjacent cooling hole.

9. The airfoil according to claim 8 , wherein the angle is a first angle in a range of between 10° and 90°.

10. The airfoil according to claim 8 , wherein the tip is configured to receive a flow path fluid in a flow direction, and the cooling holes extend in a longitudinal direction that is at a second angle of 90°+/−60° with respect to the flow direction.

11. The airfoil according to claim 8 , wherein the body is a turbine blade.

12. The airfoil according to claim 8 , wherein the tip includes multiple squealer pockets.

13. The airfoil according to claim 8 , wherein the tip includes a partial tip shelf.

14. The airfoil according to claim 8 , wherein the tip includes a full tip shelf.

Assignees

• United Technologies Corp

Inventors

• Quach San
• Lewis Scott D
• Gautschi Steven Bruce
• King Christopher
• Corcoran Christopher
• Chapdelaine David Donald

Classifications

• F05D2260/202

  by film cooling · CPC title

• F01D5/20 Primary

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title