TURBINE AIRFOIL TIP SHELF AND SQUEALER POCKET COOLING

• US 20150292334A1
• Filed: 06/24/2015
• Published: 10/15/2015
• Est. Priority Date: 04/05/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Mongillo, Dominic J. Jr., Gautschi, Steven Bruce, Quach, San
• Granted Patent: US 9,429,027 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An airfoil includes a pressure surface and a suction surface extending from a root section of the airfoil to a tip section of the airfoil. The airfoil also includes a leading edge and a trailing edge defining a chord length of the airfoil therebetween. The airfoil further includes a tip shelf formed along the tip section of the airfoil between the pressure surface and a tip shelf wall. The tip shelf wall is spaced between the pressure surface and the suction surface and the tip shelf extends from within 10% of the chord length measured from the leading edge to within 10% of the chord length measured from the trailing edge.

Claims

1. An airfoil comprising:

a pressure surface and a suction surface extending from a root section of the airfoil to a tip section of the airfoil;

a leading edge and a trailing edge defining a chord length of the airfoil therebetween; and

a tip shelf formed along the tip section of the airfoil between the pressure surface and a tip shelf wall, wherein the tip shelf wall is spaced between the pressure surface and the suction surface, wherein the tip shelf extends from within 10% of the chord length measured from the leading edge to within 10% of the chord length measured from the trailing edge.

2. The airfoil of claim 1, wherein the airfoil further comprises:

a squealer pocket formed along the tip section of the airfoil between the tip shelf wall and a squealer tip wall extending from the suction surface.

3. The airfoil of claim 1, wherein the tip shelf extends around the leading edge and onto the suction surface to terminate on the suction surface between the leading edge and the trailing edge of the airfoil.

4. The airfoil of claim 3, wherein the leading edge further comprises an indentation formed on the leading edge, the indentation extending along the leading edge between the root section of the airfoil and the tip section of the airfoil, and wherein the indentation intersects the tip shelf at the leading edge.

5. The airfoil of claim 4, further comprising a plurality of cooling holes formed in the indentation formed on the leading edge of the airfoil.

6. The airfoil of claim 5, wherein at least one of the plurality of cooling holes formed in the indentation extends partially in a radial direction.

7. The airfoil of claim 5, wherein at least one of the plurality of cooling holes formed in the indentation includes a transition opening that tapers inward into the leading edge of the airfoil.

8. The airfoil of claim 1, wherein the tip shelf extends to the trailing edge of the airfoil to terminate at a downstream intersection of the pressure and suction surfaces such that the tip shelf communicates with both the pressure surface and the suction surface proximate to the trailing edge.

9. The airfoil of claim 1, further comprising a plurality of cooling holes formed in the tip shelf proximate the pressure surface of the airfoil.

10. The airfoil of claim 9, wherein the plurality of cooling holes are arranged in at least two rows on the tip shelf for a first portion of the chord length and the plurality of cooling holes are arranged in a single row for a second portion of the chord length.

11. The airfoil of claim 1, further comprising a plurality of cooling holes formed in the tip shelf proximate the leading edge of the airfoil.

12. The airfoil of claim 11, wherein at least one of the plurality of cooling holes formed in the tip shelf proximate the leading edge of the airfoil includes a transition opening that tapers inward into the tip shelf.

13. The airfoil of claim 11, wherein at least one of the plurality of cooling holes formed in the tip shelf proximate the leading edge of the airfoil includes an oval cross-sectional profile.

14. The airfoil of claim 11, wherein at least one of the plurality of cooling holes formed in the tip shelf extends at least partially in a radial direction.

15. A gas turbine engine blade comprising:

an airfoil comprising convex and concave surfaces extending from a root section to a tip section and from a leading edge to a trailing edge, the leading and trailing edges defining a chord length therebetween; and

a tip shelf defining an open perimeter recess between the concave surface and a tip shelf wall, wherein the tip shelf wall is spaced between the convex surface and the concave surface, wherein the open perimeter recess extends from a region within 5% of the chord length measured from the leading edge of the airfoil to a region within 5% of the chord length measured from the trailing edge of the airfoil.

16. The blade of claim 15, further comprising:

a squealer pocket defining a closed perimeter recess between the tip shelf wall and a squealer tip wall extending congruently from the convex surface, wherein the closed perimeter recess extends from a region within 5% of the chord length measured from the leading edge of the airfoil to terminate in a region between 25% and 80% of the chord length measured from the trailing edge of the airfoil.

17. The blade of claim 15, wherein the open perimeter recess defined by the tip shelf extends from an intersection of the convex and concave surfaces at the trailing edge and around the leading edge of the airfoil onto the convex surface, the open perimeter recess and the tip shelf terminating on the convex surface proximate the leading edge.

18. The blade of claim 17, further comprising a plurality of cooling holes formed in the tip shelf at the leading edge and proximate to the concave surface.

19. The blade of claim 18, wherein each of the plurality of cooling holes formed in the tip shelf includes a transition opening that tapers inward into the tip shelf.

20. The blade of claim 17, wherein the tip shelf comprises a step disposed between 55% and 25% of the chord length measured from the trailing edge of the airfoil, wherein the step shifts a portion of the tip shelf generally radially outward toward the tip section.