METHOD FOR MANUFACTURING A BLADE FOR AN AIRCRAFT TURBOMACHINE

The method of producing aircraft turbomachine blades with serrations by thermo-compression of a preform and bonded material addresses the issues of noise reduction and structural integrity, ensuring durability and efficiency across engine modes.

FR3161461B1Active Publication Date: 2026-04-03SAFRAN SA
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Patent Information

Application Number
FR2024004199
Authority / Receiving Office
FR · FR
Patent Type
Patents
Current Assignee / Owner
Filing Date
2024-04-23
Publication Date
2026-04-03
Estimated Expiration
2044-04-23

AI Technical Summary

Technical Problem

Existing aircraft turbomachine blades with serrations for noise reduction become counterproductive in reverse thrust mode and are fragile due to material limitations, and existing manufacturing methods cannot efficiently integrate complex shapes like serrations without compromising structural integrity.

Method used

A method involving the production of a three-dimensional preform using woven fibers and polymerizable resin, followed by thermo-compression to bond a material with the blade body, creating serrations by shaping a mold impression, which uses thermosetting polymers and mechanical or chemical bonding to form serrations on the blade edges.

Benefits of technology

Enables the creation of durable serrations that maintain aerodynamic efficiency and reduce noise across various engine conditions without compromising structural integrity, allowing for complex shapes and potential repair throughout the blade's lifecycle.

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Abstract

A method for manufacturing a blade (30) for an aircraft turbomachine, comprising: a) producing a three-dimensional preform by weaving fibers, b) solidifying the preform with a polymerizable resin to form a blade body (36), and c) forming serrations (35), this formation being carried out by mounting the blade body (36) in a mold (38) having an impression (40) of the serrations (35) to be formed, and by thermo-compressing a material (42) in the mold (38), this material (42) being intended to bond with the blade body (36) and to adopt the shape of the impression (40), the assembly formed by the blade body (36) and the bonded material (42) forming the blade (32) of the turbine (30). Figure for the abstract: Figure 4
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