Method for producing a metal reinforcement for a turbomachine blade

Patent metadata

Field	Value
Publication number	US-9321100-B2
Application number	US-201113877985-A
Country	US
Kind code	B2
Filing date	Oct 5, 2011
Priority date	Oct 5, 2010
Publication date	Apr 26, 2016
Grant date	Apr 26, 2016

Abstract

A method for producing a metal reinforcement for the leading edge or trailing edge of a turbomachine blade, the method including cutting a plurality of metal foils from a flexible metal sheet, corresponding substantially to the developed length of the leading or trailing edge metal reinforcement; producing a plurality of metal pockets, each pocket being produced from two of the metal foils obtained during the cutting; stacking the metal pockets one inside the other, such as to form a preform of the leading or trailing edge metal reinforcement; and hot isostatic pressing the preform, causing the metal pockets to bond to one another, so as to produce the leading or trailing edge metal reinforcement.

First claim

The invention claimed is:

1. A method of production of a metal reinforcement of a leading edge or a trailing edge of a turbomachine blade comprising:
cutting, in at least one flexible metal sheet, a plurality of metal foils corresponding to the evolute of said leading edge or trailing edge metal reinforcement;
producing a plurality of metal pockets, each metal pocket being produced by attaching two metal foils together cut during the cutting;
stacking said metal pockets one inside the other, in such a way as to form a preform of said leading or trailing edge metal reinforcement, and
after said stacking, hot isostatic pressing said preform, causing said metal pockets to bond to one another, in such a way as to obtain said leading or trailing edge metal reinforcement.

2. The method of production of a metal reinforcement of the leading edge or trailing edge of a turbomachine blade according to claim 1 , wherein said producing is carried out by superposition of two separate metal foils, and by joining at least one edge of said two metal foils by bonding.

3. The method of production of a metal reinforcement of the leading edge or trailing edge of a turbomachine blade according to claim 1 , wherein said producing is carried out by bending a junction zone between two metal foils, and by joining at least one edge of said two metal foils by bonding.

4. The method of production of a metal reinforcement of the leading edge or trailing edge of a turbomachine blade according to claim 2 , wherein said bonding is performed by gluing and/or welding.

5. The method of production of a metal reinforcement of the leading edge or trailing edge of a turbomachine blade according to claim 4 , wherein said welding is performed by spot welding.

6. The method of production of a metal reinforcement of the leading edge or trailing edge of a turbomachine blade according to claim 1 , wherein said cutting is carried out in at least one metal sheet having a thickness between 0.05 mm and 0.3 mm.

7. The method of production of a metal reinforcement of the leading edge or trailing edge of a turbomachine blade according to claim 1 , wherein said stacking comprises incorporating an insert between two successive metal pockets.

8. The method of production of a metal reinforcement of the leading edge or trailing edge of a turbomachine blade according to claim 7 , wherein said incorporating includes inserting a solid or woven metal insert or a temporary insert capable of being dissolved by chemical attack.

9. The method of production of a metal reinforcement of the leading edge or trailing edge of a turbomachine blade according to claim 1 , wherein said stacking is carried out by stacking said metal pockets using a shaping template.

10. The method of production of a metal reinforcement of the leading edge or trailing edge of a turbomachine blade according to claim 1 , wherein said stacking is carried out by stacking said metal pockets in a mould or on a counter-mould of a hot isostatic pressing tool.

Assignees

• Dambrine Bruno Jacques Gérard
• Godon Thierry
• Perroux Alain Robert Yves
• Snecma

Inventors

• Dambrine Bruno Jacques Gérard
• Godon Thierry
• Perroux Alain Robert Yves

Classifications

• F05D2240/303

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

• B29C66/301

  Three-dimensional joints, i.e. the joined area being substantially non-flat (B29C66/5223, B29C66/5224, B29C66/5225 take precedence) · CPC title

• B21D53/78 Primary

  propeller blades; turbine blades · CPC title

• B29C65/48

  using adhesives {, i.e. using supplementary joining material; solvent bonding} · 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