Shield

Patent metadata

Field	Value
Publication number	US-10309237-B2
Application number	US-201514924006-A
Country	US
Kind code	B2
Filing date	Oct 27, 2015
Priority date	Nov 19, 2014
Publication date	Jun 4, 2019
Grant date	Jun 4, 2019

Abstract

The present invention provides a method of making a metallic shield for shielding an edge of a component e.g. an aerofoil component such as a gas turbine blade or vane. The method comprises:
providing a mandrel with a mandrel edge having a shape conforming to the shape of the component edge, wherein the mandrel edge comprises a surface having a width, W 1; providing a metal wire having a substantially triangular radial cross-section with a base surface of width W 2 , wherein W 2 equals W 1; aligning and affixing the base surface of the wire on the surface of the mandrel edge; electro-depositing metal onto the mandrel and metal wire to form the metallic shield comprising the deposited metal and the metal wire; and removing the metallic shield from the mandrel.

First claim

The invention claimed is:

1. A method of making a metallic shield for shielding an edge of a component, the method comprising:
providing a mandrel with a mandrel edge having a shape conforming to the shape of the component edge, wherein the mandrel edge comprises a surface having a width, W 1 ;
providing a metal wire having a substantially triangular radial cross-section with a base surface of width W 2 , wherein W 2 equals W 1 ;
aligning and affixing the base surface of the wire on the surface of the mandrel edge;
electro-depositing metal onto the mandrel and metal wire to form the metallic shield comprising the deposited metal and the metal wire; and
removing the metallic shield from the mandrel,

wherein the metallic shield comprises an electroplated shield comprising opposing walls, each wall having an inside surface for abutment with the component and an outside surface, wherein the outside surfaces of the opposing walls meet at and define a shield edge, and
the electroplated shield covers all surfaces of the wire except an internal abutment surface of the wire that is configured for direct abutment with the edge of the component.

2. A method according to claim 1 wherein the metal wire has a radial cross-section with a linear or concave base edge and/or two linear or convex side edges.

3. A method according to claim 1 wherein the surface of the mandrel edge has a length, L 1 and the metal wire has a length L 2 , wherein L 2 is equal to or greater than L 1 .

4. A method according to claim 1 wherein the metal wire comprises an outer surface with a conductive coating.

5. A method according to claim 1 wherein the metal wire or the conductive coating is formed of nickel or nickel/cobalt alloy.

6. A method according to claim 5 wherein the deposited metal is nickel.

7. A method of forming an aerofoil component, the method comprising forming a metallic shield using the method according to claim 1 and affixing the metallic shield to the edge of the aerofoil component.

8. A metallic shield for shielding an edge of a component, the metallic shield comprising:
an electroplated shield comprising opposing walls, each wall having an inside surface for abutment with the component and an outside surface, wherein the outside surfaces of the opposing walls meet at and define a shield edge; and
wherein the electroplated shield covers all surfaces of a wire except an internal abutment surface of the wire that is configured for direct abutment with the edge of the component.

9. The metallic shield according to claim 8 wherein the base surface of the shield is a planar surface.

10. An aerofoil component comprising the metallic shield according to claim 8 at the leading edge of the aerofoil component with the opposing walls at least partly covering pressure and suction surfaces of the aerofoil component.

11. An aerofoil component having a pressure surface, a suction surface, and an edge surface, the edge surface extending between the pressure and suction surfaces, wherein the aerofoil component further comprises a unitary metallic shield comprising:
an electroformed shield having opposing walls, each opposing wall having (1) an inside surface in abutment with one of the pressure or suction surfaces and (2) an outside surface, the outside surfaces of the opposing walls of the unitary metallic shield directly contacting each other and defining a shield edge; and
wherein surfaces abutting the opposing walls and longitudinal ends of a wire are covered by the electroformed shield, the wire comprising an internal abutment surface which is configured to abut the edge surface of the aerofoil component.

12. A gas turbine engine comprising the aerofoil component according to claim 10 .

13. A gas turbine engine comprising the aerofoil component according to claim 11 .

14. The metallic shield according to claim 8 wherein the wire has a triangular radial cross-section.

15. The aerofoil component according to claim 11 ,
wherein the wire has a triangular radial cross-section.

16. A metallic shield for shielding an edge of a component, the metallic shield comprising:
a wire comprising two end surfaces positioned at opposing ends of a longitudinal length of the wire and a base surface; and
an electroformed covering subsuming the wire such that the two end surfaces of the wire are completely covered by the electroformed covering while the base surface is not covered by the electroformed portion, each wall having an inside surface for abutment with the component and an outside surface, wherein the opposing walls have a constant thickness from one end of the metallic shield to a point where the opposing walls meet at and define a shield edge, wherein
the inside surfaces of the opposing walls are separated at the shield edge by the wire, and
the base surface being configured for abutment with the edge of the component.

17. The metallic shield according to claim 16 wherein each of the opposing walls have a curvature from the shield edge to the one end of the metallic shield.

Assignees

• Rolls Royce Plc

Inventors

• Norton Giles Daniel

Classifications

• F05D2240/121

  related to the leading edge of a stator vane · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F04D29/324

  Blades · CPC title

• F05D2230/30

  with deposition of material · CPC title

• F01D9/02 Primary

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title