METHOD OF MANUFACTURING A GAS TURBINE CASING OUT OF COMPOSITE MATERIAL, AND A CASING AS OBTAINED THEREBY

• US 20080206048A1
• Filed: 02/19/2008
• Published: 08/28/2008
• Est. Priority Date: 02/23/2007
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Molinari, Olivier Michael, Marlin, Francois Marie Paul, Coupe, Dominique, Verseux, Philippe, Phelippeau, Antoine, Dambrine, Bruno Jacques Gerard
• Granted Patent: US 8,322,971 B2
• Time in Patent Office: Days
• US Class Current: 415/200
• CPC Class Codes: B29B 11/16 comprising fillers or reinforcement non-woven fabrics per se D04H1/00, D04H3/00
• CPC Class Codes: B29C 70/24 oriented in at least three directions forming a three dimensional structure
• CPC Class Codes: B29C 70/32 on a rotating mould, former or core
• CPC Class Codes: B29C 70/443 and impregnating by vacuum or injection
• CPC Class Codes: B29L 2031/7504 Turbines
• CPC Class Codes: F01D 21/045 special arrangements in stators or in rotors dealing with breaking-off of part of rotor
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.

Claims

1. A method of manufacturing a composite material casing of varying thickness for a gas turbine, the method comprising forming fiber reinforcement as superposed layers of a fiber texture and densifying the fiber reinforcement with a matrix, and wherein the fiber texture is made by three-dimensional weaving with varying thickness, which texture is wound as a plurality of superposed layers on a mandrel of profile corresponding to the profile of the casing that is to be made, so as to obtain a fiber preform of varying thickness and of shape corresponding to the shape of the casing to be made.

2. A method according to claim 1, wherein the fiber texture is woven with its warp being taken up on a drum having a profile that is determined as a function of the profile of the casing to be made.

3. A method according to claim 1, for manufacturing a casing having at least one fastening or connection flange, wherein the preform is made as a single part with a preform portion corresponding to the flange of the casing.

4. A method according to claim 1, wherein the fiber texture is woven with thickness that increases progressively from its longitudinal ends in zones that are adjacent to the longitudinal ends.

5. A method according to claim 1, wherein the preform is formed by three-dimensional weaving with an interlock weave.

6. A fan retention casing for a gas turbine, the casing being of varying thickness and being made of a composite material with fiber reinforcement densified by a matrix, wherein the fiber reinforcement comprises a texture of varying thickness formed by three-dimensional weaving and wound into superposed layers.

7. A casing according to claim 6, including at least one flange, wherein the fiber reinforcement is made as a single part including a flange-reinforcing portion.

8. A gas turbine aeroengine including a fan retention casing according to claim 6 or claim 7.