Turbine airfoil tip shelf and squealer pocket cooling

Patent metadata

Field	Value
Publication number	US-9228442-B2
Application number	US-201213440297-A
Country	US
Kind code	B2
Filing date	Apr 5, 2012
Priority date	Apr 5, 2012
Publication date	Jan 5, 2016
Grant date	Jan 5, 2016

Abstract

An airfoil comprises leading and trailing edges with pressure and suction surfaces defining a chord length therebetween. The pressure and suction surfaces extend from a root section of the airfoil to a tip section. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall spaced between the pressure surface and the suction surface. A squealer pocket is formed along the tip section between the tip shelf wall and a squealer tip wall extending from the suction surface. The tip shelf extends from within 10% of the cord length measured from the leading edge to within 10% of the chord length measured from the trailing edge. The squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate between 10% and 25% of the chord length measured from the trailing edge.

First claim

The invention claimed is:

1. An airfoil comprising:
a leading edge, a trailing edge and pressure and suction surfaces defining a chord length therebetween, the pressure and suction surfaces extending from a root section of the airfoil to a tip section of the airfoil;
a tip shelf formed along the tip section of the airfoil between the pressure surface and a tip shelf wall spaced between the pressure surface and the suction surface, wherein the tip shelf extends from the leading edge to an intersection of the pressure surface and the suction surface at the trailing edge such that the tip shelf communicates with both the pressure surface and the suction surface proximate to the trailing edge,
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; and
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, wherein the squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate within 10% and 25% of the chord length measured from the trailing edge.

2. The airfoil of claim 1 , wherein the squealer pocket extends for more than 75% of the chord length and less than 90% of the chord length.

3. The airfoil of claim 2 , wherein the squealer pocket extends from a location within 5% of the chord length measured from the leading edge of the airfoil.

4. The airfoil of claim 1 , further comprising a squealer discharge flow channel extending from the squealer pocket to the trailing edge of the airfoil.

5. The airfoil of claim 1 , further comprising a plurality of cooling holes formed in the tip shelf to generate cooling fluid flow along pressure surface of the airfoil.

6. The airfoil of claim 5 , further comprising a plurality of cooling holes formed in the squealer pocket to generate cooling fluid flow along the tip section of the airfoil.

7. A turbine engine comprising the airfoil of claim 1 .

8. The turbine engine of claim 7 , wherein the squealer pocket and tip shelf are configured to match transient response rates of the tip section with the pressure and suction surfaces adjacent the tip section based on removal of metal volume from the tip section of the airfoil, reducing transient thermal strains as compared to an airfoil without the squealer pocket and tip shelf.

9. A gas turbine engine blade comprising:
an airfoil comprising suction and pressure 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;
a tip shelf defining an open perimeter recess between the pressure surface and a tip shelf wall spaced between the suction surface and the pressure surface, wherein the open perimeter recess extends from the leading edge of the airfoil the trailing edge of the airfoil,
wherein the tip shelf extends to an intersection of the pressure surface and the suction surface at the trailing edge such that the tip shelf communicates with both the pressure surface and the suction surface proximate to the trailing edge, and
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; and
a squealer pocket defining a closed perimeter recess between the tip shelf wall and a squealer tip wall extending congruently from the suction 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 10% and 25% of the chord length measured from the trailing edge of the airfoil.

10. The blade of claim 9 , wherein the closed perimeter recess defined by the squealer pocket extends along the tip section of the airfoil for more than 75% of the chord length and less than 90% of the chord length.

11. The blade of claim 9 , further comprising a plurality of cooling holes formed in the tip shelf to maintain a pocket of cooling fluid along the tip section of the airfoil between the tip shelf wall and the pressure surface.

12. The blade of claim 11 , further comprising a plurality of cooling holes formed in the squealer pocket to maintain a pocket of cooling fluid along the tip section of the airfoil between the tip shelf wall and the squealer tip wall.

13. An airfoil for a gas turbine engine, the airfoil comprising:
leading and trailing edges extending from a root section to a tip section;
pressure and suction surfaces defining a chord length between the leading and trailing edges;
a squealer tip cavity extending along the tip section of the airfoil, the squealer tip cavity defined between a squealer tip wall extending congruently from the suction surface and a tip shelf wall extending between the squealer tip wall and the pressure surface, wherein the squealer tip cavity extends from a location within 10% of the chord length measured from the leading edge of the airfoil and terminates in a region between 10% and 25% of the chord length measured from the trailing edge of the airfoil; and
a tip shelf recess formed between the tip shelf wall and the pressure surface of the airfoil, the tip shelf recess extending from the leading edge of the airfoil,
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, and
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.

14. The airfoil of claim 13 , further comprising a plurality of cooling holes formed along the squealer tip cavity and a plurality of cooling holes formed along the tip shelf recess.

15. The airfoil of claim 13 , further comprising a squealer discharge flow channel extending from the squealer tip cavity to the trailing edge of the airfoil.

16. A rotor blade comprising the airfoil of claim 15 .

17. A gas turbine engine comprising the rotor blade of claim 16 .

18. The gas turbine engine of claim 17 , wherein the squealer discharge flow channel is configured to reduce tip leakage vortex flow by axially aligning squealer discharge flow at the trailing edge of the airfoil.

19. The gas turbine engine of claim 17 , wherein cooling fluid flow from the tip shelf and squealer pocket merge at the discharge flow channel.

20. The gas turbine engine of claim 19 , wherein the squealer discharge channel is configured to reduce penetration of leakage flow over the blade tip by discharging cooling fluid flow from the tip shelf and the squealer pocket in an axial direction aligned with suction side streamlines adjacent the tip section of the airfoil at the trailing edge.

Assignees

• Mongillo Jr Dominic J
• Gautschi Steven Bruce
• Quach San
• United Technologies Corp

Inventors

• Mongillo Jr Dominic J
• Gautschi Steven Bruce
• Quach San

Classifications

• 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

• Y02T50/60

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