Method for creating a metal reinforcement with insert for protecting a leading edge made of composite

Patent metadata

Field	Value
Publication number	US-9963971-B2
Application number	US-201314394366-A
Country	US
Kind code	B2
Filing date	Apr 11, 2013
Priority date	Apr 19, 2012
Publication date	May 8, 2018
Grant date	May 8, 2018

Abstract

A method for producing a metal reinforcement for protecting a leading edge of a compressor blade of composite, including: creating a core that has a shape of an internal cavity of the reinforcement; creating an insert made of an alloy of a hardness greater than that of the reinforcement; shaping sheet metal by stamping with the creation, upstream of the core, a cavity between the metal sheets, which cavity is configured to accept the insert, positioning the sheets around the core with the insert placed in the cavity and securing the assembly together; creating a vacuum and closing the assembly by welding; consolidation by hot isostatic pressing; cutting the assembly to extract the core and separate the reinforcement; creating an external profile of the reinforcement by a final machining operation that reveals a material of the insert.

First claim

The invention claimed is:

1. A method for producing a metal reinforcement for protecting a leading edge or a trailing edge of an aeronautical engine blade made of composite material, the method comprising:
producing a core that has a shape of an internal cavity of the metal reinforcement to be produced, a first face of the core corresponding to an internal shape of a suction face of the reinforcement and a second face of the core corresponding to an internal shape of a pressure face of the reinforcement;
producing an insert made of an alloy of a hardness greater than that of the reinforcement, the insert being made of a titanium-based alloy;
initial shaping metal sheets by stamping to bring metal sheets closer to the shape of the suction face and pressure face of the reinforcement, by leaving a residual space between the metal sheets, and forming, upstream or downstream of the core, a cavity between the metal sheets that is configured to receive the insert, the cavity being positioned beyond the residual space, in a position further upstream or further downstream than the core towards the leading edge or the trailing edge, a width of the cavity increasing from a first end of the cavity to a second end of the cavity, the second end of the cavity being closer to the core than the first end of the cavity;
positioning the metal sheets around the core with the insert being placed in the cavity to form an assembly;
placing the assembly under vacuum and closing the assembly by welding;
joining the assembly by hot isostatic pressing so as to diffusion-weld the metal sheets and the insert to each other;
producing an external profile of the reinforcement by a final machining operation that reveals the material of the insert at an end of the reinforcement by removing a portion of the metal sheets and the insert that are diffusion-welded to each other, the insert constituting a portion of the suction face of the reinforcement and a portion of the pressure face of the reinforcement; and
cutting the assembly to extract the core and separate the reinforcement, the core and the insert being two distinct parts.

2. A method according to claim 1 , wherein an elastic limit for cold working of the alloy used for the insert is greater than that of the material used for the reinforcement.

3. A method according to claim 1 , wherein the metal sheets are made of titanium alloy and wherein the insert is made of a titanium alloy selected from Ti5553, Ti10-2-3, or Ti17.

4. A method according to claim 1 , wherein the metal sheets are made of titanium alloy and wherein the insert is made of an intermetallic titanium alloy.

5. A method according to claim 4 , wherein the intermetallic alloy is a titanium-aluminium alloy.

6. A method according to claim 1 , wherein the metal sheets are made of titanium alloy and wherein the insert is made of an orthorhombic alloy.

7. A method according to claim 6 , wherein the orthorhombic alloy is a titanium-aluminium-niobium alloy.

8. A method according to claim 1 , wherein during the joining of the assembly by hot isostatic pressing, the residual space is eliminated and the insert is surrounded in a front part of the reinforcement.

9. A method for producing a metal reinforcement for protecting a leading edge or a trailing edge of an aeronautical engine blade made of composite material, the method comprising:
producing a core that has a shape of an internal cavity of the metal reinforcement to be produced, a first face of the core corresponding to an internal shape of a suction face of the reinforcement and a second face of the core corresponding to an internal shape of a pressure face of the reinforcement;
producing an insert made of an alloy of a hardness greater than that of the reinforcement, the insert being made of a titanium-based alloy;
initial shaping metal sheets by stamping to bring metal sheets closer to the shape of the suction face and pressure face of the reinforcement, by leaving a residual space between the metal sheets, and forming, upstream or downstream of the core, a cavity between the metal sheets that is configured to receive the insert, the cavity being positioned beyond the residual space, in a position further upstream or further downstream than the core towards the leading edge or the trailing edge;
positioning the metal sheets around the core with the insert being placed in the cavity to form an assembly;
placing the assembly under vacuum and closing the assembly by welding;
joining the assembly by hot isostatic pressing so as to diffusion-weld the metal sheets and the insert to each other;
producing an external profile of the reinforcement by a final machining operation that reveals the material of the insert at an end of the reinforcement by removing a portion of the metal sheets and the insert that are diffusion-welded to each other, the insert constituting a portion of the suction face of the reinforcement and a portion of the pressure face of the reinforcement; and
cutting the assembly to extract the core and separate the reinforcement, the core and the insert being two distinct parts,
wherein during the joining of the assembly by hot isostatic pressing, the residual space is eliminated and the insert is surrounded upstream or downstream of the reinforcement.

Assignees

• Snecma

Inventors

• Franchet Jean-Michel Patrick Maurice
• Klein Gilles Charles Casimir
• Leconte Gilbert Michel Marin
• Magnaudeix Dominique

Classifications

• B23P15/04

  turbine or like blades from several pieces · CPC title

• B23K2101/001

  Turbines · CPC title

• F04D29/023

  especially adapted for elastic fluid pumps · 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

• F05D2230/20

  essentially without removing material · CPC title