Gas turbine engine airfoil baffle

Patent metadata

Field	Value
Publication number	US-9353631-B2
Application number	US-201113214429-A
Country	US
Kind code	B2
Filing date	Aug 22, 2011
Priority date	Aug 22, 2011
Publication date	May 31, 2016
Grant date	May 31, 2016

Abstract

An airfoil includes an airfoil wall having an exterior airfoil surface and an interior surface. The interior surface provides an airfoil cavity. A baffle is arranged in the airfoil cavity and provides a baffle wall having first and second portions spaced from one another on first and second sides. A tube interconnects the first and second portions and is configured to convey fluid through the tube between the first and second sides. The airfoil is cooled by supplying cooling fluid to a baffle arranged within an airfoil. The cooling fluid is passed through baffle cooling holes to a gap between the baffle and airfoil to cool an interior surface of the airfoil. A portion of cooling fluid is conveyed from one gap location to another gap through a tube in the baffle. Another portion of the cooling fluid is passed through film cooling holes in the airfoil.

First claim

What is claimed is:

1. An airfoil comprising:
an airfoil wall providing an exterior airfoil surface and an interior surface, the interior surface providing an airfoil cavity with concave and convex surfaces respectively corresponding to pressure and suction sides;
a baffle arranged in the airfoil cavity and providing a baffle wall having first and second portions spaced from one another on first and second sides that are respectively concave and convex to define a gap therebetween;
a plurality of standoffs arranged between the interior surface and baffle wall to isolate a first gap portion and a second gap portion;
baffle cooling holes are arranged in the first portion to convey a fluid between the baffle and the first gap portion;
a tube interconnecting the first and second portions; and
wherein the tube is configured to convey fluid between first and second gap portions, the first gap portion is arranged between the concave surface and the first side, the second gap portion is arranged between the convex surface and the second side.

2. The airfoil according to claim 1 , wherein the plurality of stand-offs are arranged between the interior surface and the baffle wall to provide the gap.

3. The airfoil according to claim 2 , wherein the airfoil wall includes film cooling holes, the airfoil is configured to convey cooling fluid through the baffle and out the baffle cooling holes to the film cooling holes, and the plurality of standoffs isolate pressure and suction sides of the gap from one another.

4. The airfoil according to claim 2 , wherein the plurality of stand offs extend radially along the airfoil.

5. The airfoil according to claim 1 , wherein the first and second portions include bypass holes, and the tube interconnects the bypass holes.

6. The airfoil according to claim 5 , wherein the tube is flush with an exterior baffle surface provided by the baffle wall.

7. The airfoil according to claim 5 , wherein a weld secures the tube to the exterior baffle surface at least one of the bypass holes.

8. The airfoil according to claim 5 , wherein the tube is secured to the baffle by riveting.

9. The airfoil according to claim 1 , wherein the tube is arranged substantially perpendicularly relative to the first and second portions.

10. The airfoil according to claim 1 , wherein the tube is an imperforate conduit configured to convey a bypass flow from the first gap portion to the second gap portion.

11. The airfoil according to claim 1 , wherein the tube is cylindrical.

12. The airfoil according to claim 1 , wherein the first and second gap portions are defined respectively by the first and second portions and the concave and convex surfaces.

13. A method of cooling an airfoil comprising the steps of:
supplying cooling fluid to a baffle arranged within an airfoil;
passing the cooling fluid through baffle cooling holes to a first gap portion between the baffle and airfoil to cool an interior surface of the airfoil;
conveying a portion of cooling fluid from the first gap portion to a second gap portion remote from the first gap portion through a tube in the baffle;
passing another portion of the cooling fluid through film cooling holes in the airfoil; and
wherein the first gap portion and the second gap portion are respectively adjacent to suction and pressure sides provided by an exterior surface of said airfoil, the first and second gap portions fluidly isolated from one another by standoffs arranged between the interior surface and the baffle.

Assignees

• Spangler Brandon W
• United Technologies Corp

Inventors

• Spangler Brandon W

Classifications

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2260/202

  by film cooling · CPC title

• F01D5/186 Primary

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

• F01D5/189

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title