Airfoil with leading edge reinforcement

Patent metadata

Field	Value
Publication number	US-9470097-B2
Application number	US-201314094313-A
Country	US
Kind code	B2
Filing date	Dec 2, 2013
Priority date	Mar 14, 2013
Publication date	Oct 18, 2016
Grant date	Oct 18, 2016

Abstract

A leading edge member for a composite vane of a gas turbine engine. The leading edge member includes a first leg and a second leg. The first leg includes a proximal end joined to a proximal end of the second leg.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine comprising
a core body having a leading edge, a trailing edge, a first surface extending between the leading edge and the trailing edge, and a second surface extending between the leading edge and the trailing edge;
a leading edge member having a tip, a first leg extending from a first proximal end at the tip to a first distal end, a second leg extending from a second proximal end at the tip to a second distal end, the first distal end of the first leg being joined to the first surface of the core body, the second distal end of the second leg being joined to the second surface of the core body, and an interior cavity located between the first leg and the second leg at the tip of the leading edge member; and
a reinforcement member located within the interior cavity of the leading edge member, the reinforcement member being joined to the proximal end of the first leg of the leading edge member and joined to the proximal end of the second leg of the leading edge member.

2. The airfoil of claim 1 , wherein said leading edge member is formed from sheet metal.

3. The airfoil of claim 1 , wherein the reinforcement member comprises a braze alloy material.

4. The airfoil of claim 1 , wherein the reinforcement member includes a meniscus extending between the first leg and the second leg of the leading edge member.

5. The airfoil of claim 4 , wherein the meniscus of the reinforcement member forms a generally V-shaped notch.

6. The airfoil of claim 1 , wherein the first leg of the leading edge member has a generally constant thickness, and the second leg of the leading edge member has a generally constant thickness that is generally equal to the thickness of the first leg member.

7. The airfoil of claim 1 , wherein the reinforcement member fills a portion of the interior cavity of the leading edge member at the tip of the leading edge member and between the first proximal end of the first leg and the second proximal end of the second leg.

8. A leading edge member for an airfoil included in a gas turbine engine, the leading edge member comprising
a first leg extending from a first proximal end to a first distal end;
a second leg extending from a second proximal end to a second distal end, the first distal end of the first leg being joined to the first distal end of the second leg, the first leg and the second leg forming an interior cavity between the first leg and the second leg; and
a reinforcement member located within the interior cavity and extending between the first leg and the second leg, the reinforcement member being joined to the proximal end of the first leg and to the proximal end of the second leg.

9. The leading edge member of claim 8 , wherein the reinforcement member comprises a braze alloy material.

10. The leading edge member claim 8 , including a tip formed by the proximal end of the first leg and the proximal end of the second leg, wherein the reinforcement member fills a portion of the interior cavity at the tip between the first proximal end of the first leg and the second proximal end of the second leg.

11. The leading edge member of claim 8 , wherein the reinforcement member includes a meniscus extending between the first leg and the second leg.

12. A method of manufacturing an airfoil comprising the steps of
forming a strip of metal into a V-shape having a first and a second leg,
applying a braze alloy to an internal cavity defined by the strip of metal, and
melting the braze alloy so that a meniscus of braze alloy is formed at the intersection of first and the second leg of the V-shaped strip of metal.

13. The method of claim 12 , wherein the forming step is performed by one of a mandrel, an extrusion process, a deposition process, and a plating process.

14. The method of claim 12 , further comprising the step of coupling the strip of metal to an airfoil.

15. The method of claim 14 , wherein the airfoil includes a composite material.

16. The method of claim 14 , wherein the strip of metal is arranged to extend over a leading edge of the airfoil.

17. The method of claim 14 , wherein the braze alloy is arranged to extend along a leading edge of the airfoil.

18. The method of claim 12 , wherein the braze alloy includes silver.

19. The method of claim 12 , wherein the strip of metal is sheet metal.

20. The method of claim 12 , wherein the strip of metal includes at least one of stainless steel, electroformed nickel alloy, and stainless steel mesh.

Assignees

• Rolls Royce Corp

Inventors

• Hodgson Benedict N
• Rivers Jonathan M

Classifications

• F01D5/282 Primary

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F01D5/146

  of blades with tandem configuration, split blades or slotted blades · CPC title

• F01D5/288

  Protective coatings for blades · CPC title