# US 2014/0193271 A1 · Method of making protective reinforcement for the leading edge of a blade

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- Number: US 2014/0193271 A1
- Document ID: US20140193271A1
- Status: Published application
- Kind: A1
- Application number: 14/237,995
- Filed: 2012-08-09
- Published: 2014-07-10
- Earliest claimed: 2011-08-10
- Assignees: Snecma
- Inventors: Laurent Paul Dudon; Antonio Cremildo Arantes
- Web page: https://patentgrep.com/patent/US20140193271A1

## CPC

- F04D 29/38: Blades {(for axial flow compressors F04D29/324)}
- B23P 15/04: turbine or like blades from several pieces
- B64C 11/205: {for protecting blades, e.g. coating}
- C23C 4/01: Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
- C23C 4/02: Pretreatment of the material to be coated, e.g. for coating on selected surface areas
- C23C 4/067: containing free particles of non-metal elements, e.g. carbon, silicon, boron, phosphorus or arsenic
- C23C 4/08: containing only metal elements (C23C4/073 takes precedence)
- C23C 24/04: Impact or kinetic deposition of particles
- F01D 5/147: {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)}
- F01D 5/288: {Protective coatings for blades}
- F04D 29/023: {especially adapted for elastic fluid pumps}
- F04D 29/324: {Blades}
- F05D 2220/36: specially adapted for the fan of turbofan engines
- F05D 2230/90: Coating; Surface treatment
- F05D 2240/303: related to the leading edge of a rotor blade
- F05D 2300/10: Metals, alloys or intermetallic compounds
- F05D 2300/611: Coating
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q)
- B64C: AEROPLANES; HELICOPTERS
- C23C: COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL (making metal-coated products by extrusion B21C23/22; covering with metal by connecting pre-existing layers to articles, see the relevant places, e.g. B21D39/00, B23K; metallising of glass C03C; metallising mortars, concrete, artificial stone, ceramics or natural stone C04B41/00; enamelling of, or applying a vitreous layer to, metals C23D; treating metal surfaces or coating of metals by electrolysis or electrophoresis C25D; single-crystal film growth C30B; by metallising textiles D06M11/83; decorating textiles by locally metallising D06Q1/04)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A method of making a reinforcement for reinforcing a leading edge of a blade, the method including depositing a metal coating on the leading edge by thermal spraying in compression. A blade, for example a blade for a turbine engine, a helicopter, or a propeller, can have the leading edge protected by such a reinforcement.

## Claims

### Claim at position 1

1-12. (canceled)

### Claim 13

A method of making a reinforcement for protecting a leading edge of a blade, the method comprising:
depositing a metal coating on the leading edge by thermal spraying in compression.

### Claim 14 (depends on 13)

A method according to claim 13, further comprising, prior to the thermal spraying in compression, forming at least one longitudinal groove in the blade on either side of the leading edge, with the metal coating being deposited in the grooves.

### Claim 15 (depends on 13)

A method according to claim 13, wherein the metal coating is made of Ni, Al, or Ti, or of an alloy based on Ni, Co, Al, or Ti, or of cermet.

### Claim 16 (depends on 13)

A method according to claim 13, wherein the reinforcement has a thickness in a range of 0.5 mm to 20 mm.

### Claim 17 (depends on 13)

A method according to claim 13, further comprising depositing a bonding underlayer on the leading edge prior to depositing the metal coating.

### Claim 18 (depends on 13)

A method according to claim 13, further comprising fastening a metal foil onto the leading edge prior to depositing the metal coating.

### Claim 19

A blade comprising:
a leading edge, the leading edge being protected by a reinforcement formed by a metal coating deposited on the leading edge by thermal spraying in compression.

### Claim 20 (depends on 19)

A blade according to claim 19, the blade being made of organic matrix composite material.

### Claim 21 (depends on 20)

A blade according to claim 20, the blade being a blade of a turbine engine, a helicopter, or a propeller.

### Claim 22 (depends on 19)

A blade according to claim 19, further comprising at least one longitudinal groove on either side of the leading edge, the grooves being filled with the metal coating.

### Claim 23 (depends on 19)

A blade according to claim 19, wherein the metal coating is made of Ni, Al, or Ti, or of an alloy based on Ni, Co, Al, or Ti, or of cermet.

### Claim 24 (depends on 19)

A blade according to claim 19, wherein the reinforcement has a thickness in a range of 0.5 mm to 20 mm.