Turbine airfoil tip shelf and squealer pocket cooling

Patent metadata

Field	Value
Publication number	US-9284845-B2
Application number	US-201414250166-A
Country	US
Kind code	B2
Filing date	Apr 10, 2014
Priority date	Apr 5, 2012
Publication date	Mar 15, 2016
Grant date	Mar 15, 2016

Abstract

An airfoil comprises pressure and suction surfaces extending from a root section to a tip section of the airfoil. The airfoil also comprises a leading edge and trailing edge defining a chord length therebetween. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall, the tip shelf wall being 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 less than 85% of the chord length measured from the trailing edge.

First claim

The invention claimed is:

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;
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 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 less than 85% of the chord length measured from the trailing edge.

2. The airfoil of claim 1 , wherein the squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate between 25% and 80% of the chord length measured from the trailing edge.

3. The airfoil of claim 1 , wherein the squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate between 45% and 60% of the chord length measured from the trailing edge.

4. The airfoil of claim 1 , wherein the squealer pocket extends for more than 15% of the chord length and less than 75% of the chord length.

5. The airfoil of claim 1 , wherein the squealer pocket extends from a location within 5% of the chord length measured from the leading edge of the airfoil to a location within 50% of the chord length measured from the trailing edge of the airfoil.

6. 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, wherein the tip shelf wall is spaced between the suction surface and the pressure surface, wherein the open perimeter recess extends from the leading edge of the airfoil to 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 25% and 80% of the chord length measured from the trailing edge of the airfoil.

7. The blade of claim 6 , wherein the closed perimeter recess defined by the squealer pocket extends along the tip section of the airfoil for more than 20% of the chord length and less than 75% of the chord length.

8. The blade of claim 6 , 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.

9. The blade of claim 8 , wherein each of the plurality of cooling holes formed in the tip shelf includes a transition opening that tapers inward into the tip shelf to diffuse the cooling fluid as it exits the plurality of cooling holes formed in the tip shelf.

10. The blade of claim 8 , 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.

11. An airfoil for a gas turbine engine, the airfoil comprising:
pressure and suction surfaces extending from a root section to a tip section;
leading and trailing edges defining a chord length therebetween;
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 at a location less than 85% of the chord length measured from the trailing edge; 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.

12. The airfoil of claim 11 , further comprising a squealer discharge flow channel extending from the squealer tip cavity to the trailing edge of the airfoil.

13. The gas turbine engine of claim 12 , wherein cooling fluid flow from the tip shelf and squealer pocket merge at the discharge flow channel.

Assignees

• United Technologies Corp

Inventors

• Lewis Scott D
• Mongillo Jr Dominic J
• Gautschi Steven Bruce
• Corcoran Christopher

Classifications

• F05D2260/202

  by film cooling · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• F01D5/20 Primary

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

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title