Method of fabricating a blade platform out of composite material with integrated gaskets for a turbine engine fan

Patent metadata

Field	Value
Publication number	US-10293530-B2
Application number	US-201515126982-A
Country	US
Kind code	B2
Filing date	Mar 5, 2015
Priority date	Mar 17, 2014
Publication date	May 21, 2019
Grant date	May 21, 2019

Abstract

There is provided a method of fabricating a blade platform out of composite material with integrated gaskets for a turbine engine fan, the platform including a base and a stiffener, the method including using three-dimensional weaving to make a single-piece fiber blank with a plurality of longitudinal yarn layers extending in a direction corresponding to a longitudinal direction of the base of the platform; shaping the fiber blank to form a fiber preform having a first portion forming a base preform and a second portion forming a stiffener preform; positioning platform gaskets at side margins of the first portion of the fiber preform forming a base preform; placing the fiber preform with the gaskets in an injection mold; injecting resin into the injection mold; compacting the assembly; heating the injection mold to solidify the resin; and unmolding the resulting platform.

First claim

The invention claimed is:

1. A method of fabricating a blade platform out of composite material with integrated gaskets for a turbine engine fan, the platform comprising a base extending along a longitudinal direction and presenting two opposite faces and a stiffener that extends from one of the faces of the base, the method comprising:
using three-dimensional weaving to make a single-piece fiber blank with a plurality of longitudinal yarn layers extending in a direction corresponding to a longitudinal direction of the base of the platform and interlinked by yarns of a plurality of transverse yarn layers, while leaving between the longitudinal yarn layers two main zones of non-interlinking that are open, each extending from a side edge of the fiber blank for the purpose of forming a stiffener preform;
shaping the fiber blank to form a fiber preform having a first portion forming a base preform and a second portion forming a stiffener preform;
positioning platform gaskets at side margins of the first portion of the fiber preform forming a base preform;
placing the fiber preform with the gaskets in an injection mold;
injecting resin into the injection mold;
compacting the assembly;
heating the injection mold to solidify the resin; and
unmolding the resulting platform,
wherein the step of using three-dimensional weaving to make the fiber blank further comprises making closed secondary zones of non-interlinking in the side margins of a portion of the fiber blank that is to form the base preform, the secondary zones of non-interlinking being opened and the gaskets being inserted therein prior to the step of placing the fiber preform in the injection mold.

2. The method according to claim 1 , wherein an opening of each secondary zone of non-interlinking comprises cutting the portion of the fiber blank that is to form a base preform in a cutting plane leading to insides of said secondary zones of non-interlinking.

3. The method according to claim 2 , wherein the cutting plane is previously identified on the fiber blank.

4. The method according to claim 1 , wherein each gasket has an attachment portion that is inserted longitudinally inside a secondary zone of non-interlinking, once opened.

5. A method of fabricating a blade platform out of composite material with integrated gaskets for a turbine engine fan, the platform comprising a base extending along a longitudinal direction and presenting two opposite faces and a stiffener that extends from one of the faces of the base, the method comprising:
using three-dimensional weaving to make a single-piece fiber blank with a plurality of longitudinal yarn layers extending in a direction corresponding to a longitudinal direction of the base of the platform and interlinked by yarns of a plurality of transverse yarn layers, while leaving between the longitudinal yarn layers two main zones of non-interlinking that are open, each extending from a side edge of the fiber blank for the purpose of forming a stiffener preform;
shaping the fiber blank to form a fiber preform having a first portion forming a base preform and a second portion forming a stiffener preform;
positioning platform gaskets at side margins of the first portion of the fiber preform forming a base preform;
placing the fiber preform with the gaskets in an injection mold;
injecting resin into the injection mold;
compacting the assembly;
heating the injection mold to solidify the resin; and
unmolding the resulting platform,
wherein the gaskets are assembled to the side margins of the first portion of the fiber preform forming a base preform by stitching prior to the step of placing the fiber preform in the injection mold.

6. The method according to claim 5 , wherein carbon yarns are used for assembling the gaskets to the side edges of the first portion of the fiber preform forming a base preform.

7. A method of fabricating a blade platform out of composite material with integrated gaskets for a turbine engine fan, the platform comprising a base extending along a longitudinal direction and presenting two opposite faces and a stiffener that extends from one of the faces of the base, the method comprising:
using three-dimensional weaving to make a single-piece fiber blank with a plurality of longitudinal yarn layers extending in a direction corresponding to a longitudinal direction of the base of the platform and interlinked by yarns of a plurality of transverse yarn layers, while leaving between the longitudinal yarn layers two main zones of non-interlinking that are open, each extending from a side edge of the fiber blank for the purpose of forming a stiffener preform;
shaping the fiber blank to form a fiber preform having a first portion forming a base preform and a second portion forming a stiffener preform;
positioning platform gaskets at side margins of the first portion of the fiber preform forming a base preform;
placing the fiber preform with the gaskets in an injection mold;
injecting resin into the injection mold;
compacting the assembly;
heating the injection mold to solidify the resin; and
unmolding the resulting platform,
wherein the gaskets are placed in the injection mold against the side margins of the first portion of the fiber preform forming the base preform without being mechanically connected thereto, and
wherein each longitudinal end of the base of the platform is folded inward so as to present a step, and the gaskets extend between the steps in the longitudinal direction.

8. The method according to claim 1 , wherein the gaskets are made of elastomer.

9. The method according to claim 1 , wherein the stiffener of the preform comprises two legs.

10. The method according to claim 9 , wherein the stiffener of the platform further includes a stiffener wall connecting together free ends of the legs.

11. The method according to claim 1 , wherein each gasket includes an attachment portion which is attached to the platform, and a flexible portion configured to abut against a blade.

Assignees

• Safran Aircraft Engines

Inventors

• Marchal Yann Didier Simon
• Dambrine Bruno Jacques Gerard

Classifications

• B29C49/071

  Preforms or parisons characterised by their configuration, e.g. geometry, dimensions or physical properties · CPC title

• B29C2949/0715

  the preform having one end closed · CPC title

• B29C70/24

  oriented in at least three directions forming a three-dimensional [3D] structure · CPC title

• B29L2031/082

  Blades, e.g. for helicopters · CPC title

• B29C2045/14237

  the inserts being deformed or preformed outside the mould or mould cavity · CPC title