Method for manufacturing a composite blade for a turbine engine, the blade comprising a reinforcing shield for balancing the blade

Patent metadata

Field	Value
Publication number	US-12502858-B2
Application number	US-202218571057-A
Country	US
Kind code	B2
Filing date	Jun 16, 2022
Priority date	Jun 21, 2021
Publication date	Dec 23, 2025
Grant date	Dec 23, 2025

Abstract

A method for manufacturing a blade made of a composite material for a turbine engine, in particular a turbine engine of an aircraft, wherein a reinforcing shield is attached to one edge of an airfoil, the shield having a generally elongated shape along an elongation axis of the airfoil. The shield includes at least one excess dimension so as to be able to adjust the moment weight of the blade along the axis according to the position of the shield on the edge of the axis, and the method includes a step for removing a surplus portion of the shield so s to balance the blade.

First claim

The invention claimed is:

1 . A method for manufacturing a vane made of composite material for a turbine engine comprising the steps of:
preparing a blade based on fibres embedded in a resin, the blade comprising a suction side and a pressure side extending between a leading edge and a trailing edge, attaching a reinforcing shield to an edge of the blade, said shield having an elongate shape along an axis of elongation of the blade, wherein the shield attached in the step of attaching the reinforced shield to the edge of the blade comprises at least one excess dimension so as to be able to adjust the moment weight of the vane along said axis according to the position of the shield on the edge along said axis, and in that the method comprises a subsequent step of removing a surplus portion of the shield.

2 . The method according to claim 1 , wherein the step of preparing the blade comprises the following steps:
weaving of fibres in three dimensions to obtain a fibrous preform, and mounting of the fibrous preform in a mould and injecting resin into the mould so as to obtain the blade.

3 . The method according to claim 1 , wherein the step of preparing the blade comprises stacking of fibre plies or mats, which are previously or subsequently impregnated with a resin.

4 . The method according to claim 1 , wherein said excess dimension is an extra length of the shield.

5 . The method according to claim 4 , wherein the surplus portion is located at a lower or radially internal end of the blade, or at an upper or radially external end of the blade.

6 . The method according to claim 1 , wherein said surplus portion is a longitudinal surplus portion of the shield.

7 . The method according to claim 1 , comprising a preliminary step of studying the impact of the position of the shield on the edge of the blade, along said axis, on the moment weight of the vane along this axis.

8 . The method according to claim 1 , wherein said surplus portion is removed by machining the shield.

9 . A method of assembling a turbine engine module comprising the steps of:
manufacturing a plurality of vanes made of composite material, the manufacturing of the vanes comprising:
preparing blades based on fibres embedded in a resin, each blade comprising a suction side and a pressure side extending between a leading edge and a trailing edge,
attaching a reinforcing shield to an edge of each blade, said shield having an elongate shape along an axis of elongation of the blade, wherein the shield attached in the step of attaching the reinforced shield to the edge of the blade comprises at least one excess dimension so as to be able to adjust the moment weight of the vane along said axis according to the position of the shield on the edge along said axis,
removing a surplus portion of the shield,
the method of assembling further comprising the step of:
mounting the vanes on a rotor disc.

10 . The method according to claim 9 , wherein the turbine engine module is a fan module.

Assignees

• Safran Aircraft Engines

Inventors

• Mourot Maxime Mathieu
• Lauwick Lucas Antoine Christophe
• Trebaol Julien

Classifications

• B29C65/70

  by moulding (using a particular moulding technique, see the relevant technique {, e.g. by injection B29C45/14467}) · CPC title

• B29C65/544

  by suction · CPC title

• B29C66/00145

  Vacuum, e.g. partial vacuum · CPC title

• B29C65/7832

  by setting the overlap between the parts to be joined, e.g. the overlap between sheets, plates or web-like materials · CPC title

• B29C65/00

  Joining {or sealing} of preformed parts {, e.g. welding of plastics materials}; Apparatus therefor {(general aspects of processes or apparatus for joining preformed parts B29C66/00; using porous material formed by internal pressure generated therein for joining preformed parts B29C44/1228, B29C44/326)} · CPC title