Method for producing a blade for a turbine engine
A multi-layered wear protection system for aircraft turbomachine blades uses compliant materials to reduce friction and cost, ensuring easy restoration and compliance with environmental and health regulations, overcoming previous manufacturing challenges.
WO2026115219A1PCT designated stage Publication Date: 2026-06-04SAFRAN AIRCRAFT ENGINES SAS +1
Patent Information
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2025-11-24
- Publication Date
- 2026-06-04
AI Technical Summary
Technical Problem
Existing blade manufacturing methods for aircraft turbomachines using composite materials face challenges with wear protection that violate environmental and health regulations, are costly, difficult to position, and cannot be easily restored without impacting the blade integrity.
Method used
A multi-layered wear protection system comprising a bonding, retention, and sliding layer is applied to the blade, using materials that comply with health and environmental standards, ensuring easy manufacturing, restoration, and effective friction reduction.
Benefits of technology
The multi-layered wear protection effectively reduces friction, is cost-effective, and can be easily restored without damaging the blade, addressing the limitations of previous methods.
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Smart Images
Figure FR2025051094_04062026_PF_FP_ABST
Abstract
The invention relates to a method for producing a blade (10) for an aircraft turbine engine (1), the production method comprising the following steps: (a) providing a body made of composite material comprising a polymer matrix and fibres embedded in the matrix; and (b) forming an anti-wear protection (17) on the body, characterised in that the step (b) comprises the following sub-steps: (b0) depositing a bonding layer (18) on the body, the bonding layer (18) comprising an adhesion-promoting layer (22) and an adhesion layer (21) located between the adhesion-promoting layer (22) and the body; (b1) heat-treating the bonding layer (18); (b2) depositing a retention layer (19) on the bonding layer (18); and (b3) depositing a sliding layer (20) on the retention layer (19).
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