Method for manufacturing a metal part

Patent metadata

Field	Value
Publication number	US-9486870-B2
Application number	US-201514609726-A
Country	US
Kind code	B2
Filing date	Jan 30, 2015
Priority date	Aug 2, 2012
Publication date	Nov 8, 2016
Grant date	Nov 8, 2016

Abstract

A manufacturing method for a metal part uses a tooling assembly. The tooling assembly includes a counter-form and a deformable core which includes inner and outer skins, a honeycomb structure positioned between the inner and outer skins, and a brazing material interposed between the honeycomb structure and the inner and outer skins. In particular, the core is closed by a lid equipped with ducts through which a gas is introduced. The manufacturing method includes the following steps: positioning the tooling assembly in a vacuum furnace; introducing a pressurized gas directly inside an inner skin of the core of the tooling assembly; purging the pressurized gas from an inner portion of the inner skin of the tooling assembly; and dismounting the tooling assembly so as to extract a metal part manufactured.

First claim

What is claimed is:

1. A manufacturing method for a metal part comprising:
positioning a tooling assembly without a central cask in a vacuum furnace, the tooling assembly comprising:
at least one counter-form with a shape substantially similar to a shape of said metal part to be manufactured; and
at least one core deformable at least partially; wherein said at least one core comprises:
at least one inner skin and at least one outer skin, said inner and outer skins constituting corresponding inner skin and outer skins of said metal part to be manufactured;
at least one honeycomb structure positioned between said at least one inner and outer skins; and
at least one brazing element interposed between said at least one honeycomb structure and said at least one inner skin, and between said honeycomb structure and said at least one outer skin, said at least one core being closed at ends by at least one lid comprising means for introducing a gas within said core, at least one of said lids being fixed to said at least one inner skin by welding,

introducing a pressurized gas through the at least one lid and directly inside said at least one inner skin of said at least one core of the tooling assembly;
heating the tooling assembly so as to cause successively: the plating of said at least one core against said at least one counter-form by expansion of said pressurized gas; and brazing said at least one honeycomb structure and said at least one inner and outer skins;
purging said pressurized gas from an inner portion of said at least one inner skin;
dismounting the tooling assembly so as to extract said metal part manufactured; and
removing the at least one lid from the at least one inner skin.

2. The manufacturing method according to claim 1 , wherein said metal part to be manufactured is a front portion of an ejection cone of hot gases discharged by an aircraft turbojet engine.

3. The manufacturing method according to claim 2 , said at least one inner and outer skins are made of austenitic nickel-chromium based superalloys.

4. The manufacturing method according to claim 2 , wherein said at least one inner skin is formed by hydro-forming.

5. The manufacturing method according to claim 2 , wherein said at least one inner skin is substantially cylindrical in shape.

6. The manufacturing method according to claim 2 , wherein said at least one outer skin is preformed.

7. The manufacturing method according to claim 2 , wherein said at least one outer skin is substantially cylindrical in shape.

8. The manufacturing method according to claim 1 , wherein said at least one outer skin is an acoustic skin.

9. The manufacturing method according to claim 1 , wherein said metal part to be manufactured is an inner fixed structure of a turbojet engine nacelle whose inner and outer skins are made of titanium.

10. The manufacturing method according to claim 8 , wherein the tooling assembly is made by a manufacturing method comprising the following steps:
manufacturing a first substantially barrel-shaped shroud defining at least partially the inner skin of the inner fixed structure;
manufacturing a second substantially barrel-shaped shroud defining at least partially the outer skin of the inner fixed structure;
manufacturing blocks by hot forming, said blocks defining at least partially the inner and outer skins of the inner fixed structure;
piercing the first and second barrel-shaped shrouds and said blocks of the outer skin of the inner fixed structure;
cutting each of the first and second barrel-shaped shrouds in the longitudinal direction so as to define:
a half-shroud defining at least partially an upper outer skin;
a half-shroud defining at least partially a lower outer skin;
a half-shroud defining at least partially an upper inner skin;
a half-shroud defining at least partially a lower inner skin;
welding the blocks to ends of each of the half-shrouds so as to define:
an upper outer skin;
a lower outer skin;
an upper inner skin;
a lower inner skin,
assembling the blocks of the upper inner skin with the blocks of the lower inner skin so as to define the inner skin of the inner fixed structure;
depositing a brazing element on an outer wall of the lower and upper inner skins;
positioning the lower outer skin on a lower counter-form;
depositing a brazing element on an inner wall of the lower outer skin;
depositing a lower preformed honeycomb structure on the brazing element of the inner wall of the lower outer skin;
depositing the lower and upper inner skins on the lower preformed honeycomb structure; and
depositing an upper preformed honeycomb structure on the brazing element previously deposited on the outer wall of the upper inner skin;
depositing a brazing element on the upper preformed honeycomb structure or on the inner wall of said upper outer skin;
depositing the upper outer skin on the brazing element of the upper honeycomb structure; and
positioning an upper counter-form on the upper outer skin.

Assignees

• Aircelle Sa

Inventors

• Bienvenu Philippe
• Rivoal Jean-Claude
• Poulet Flavien
• Caneque Francisco

Classifications

• B23K1/20

  Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating · CPC title

• B23K1/0018 Primary

  Brazing of turbine parts · CPC title

• B23K1/008

  Soldering within a furnace (B23K1/012 takes precedence) · CPC title

• B23K1/0008

  specially adapted for particular articles or work · CPC title

• F01D25/005

  Selecting particular materials · CPC title