Platform for a fan rotor of an aircraft turbine engine and related aircraft turbine engine

By employing a honeycomb composite material structure in the fan rotor platform, with a three-dimensional woven outer layer and a layered inner layer, the platform's stiffness and stability issues are resolved, achieving high-efficiency anti-centrifugal force performance and aerodynamic optimization, while also possessing acoustic capabilities.

CN115485457BActive Publication Date: 2026-06-26SAFRAN AIRCRAFT ENGINES SAS
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
SAFRAN AIRCRAFT ENGINES SAS
Filing Date
2021-04-23
Publication Date
2026-06-26

AI Technical Summary

Technical Problem

Existing fan rotor platforms struggle to maintain rigidity and stability under high loads and centrifugal forces, while also facing challenges in terms of aerodynamic performance and space constraints.

Method used

The composite material platform adopts a honeycomb structure, with a three-dimensional woven outer layer and a layered inner layer. The honeycomb structure enhances impact resistance and rigidity, while the layered inner layer limits deformation. The platform's stiffness and centrifugal force resistance are optimized by adjusting the thickness and structural design.

Benefits of technology

While reducing platform density, it improves mechanical strength and resistance to centrifugal force, enhances platform stability and aerodynamic performance, incorporates acoustic features to reduce noise, and simplifies the manufacturing process.

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Abstract

A platform (4) for a fan rotor of a turbine engine of an aircraft is disclosed, the platform (4) being configured to be fixed between two adjacent fan blades to a fan disc. The platform (4) comprises a longitudinal wall (5) defining an aerodynamic outer surface (6), the wall (5) comprising a honeycomb structure (20) interposed between two skin layers (7; 8), respectively an inner skin layer (7) and an outer skin layer (8), wherein the outer skin layer (8) defines the aerodynamic outer surface (6). The outer skin layer (8) comprises a three-dimensional woven structure and the inner skin layer (7) comprises a layered structure.
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