Turbomachine Fan Platform Composite Weave Design
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Solution Overview
Problem
The manufacturing of aeronautical turbomachine fan platforms made of composite materials is complex and costly due to the need for machining to thin edges for shock absorption, which increases the risk of damage during impacts.
Innovation Solution
A platform with a vein wall made of composite material featuring a central portion with three-dimensional weave and edges with a mixed two-dimensional and three-dimensional weave pattern, eliminating the need for additional machining and providing flexible contact with blades.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the edges of the platform are thinned to improve flexibility and shock absorption, then the contact between blades and platforms is optimized, but additional machining steps are required which lengthen manufacturing time and increase costs
Solution Approach 1:
The patent changes the material composition parameter by incorporating a specific percentage of elastomer (5-50% by weight) into the composite material formula. This parameter change enables the material itself to provide the required flexibility and shock absorption properties without requiring geometric modifications through machining, thus resolving the contradiction between reliability improvement and manufacturing complexity increase.
Solution Approach 2:
The patent replaces the mechanical solution (machining thinned edges to create flexibility) with a material-based solution (elastomer-modified composite material that inherently provides flexibility). This substitution eliminates the need for additional machining operations while achieving the same shock absorption function, thereby reducing manufacturing complexity.
2Reliability
If the edges are thinned to absorb shocks, then damage to blades and platforms is reduced, but gaskets must be installed to ensure watertight seal, increasing assembly complexity
Solution Approach 1:
The elastomer-modified composite material provides self-sealing properties due to its elastic nature. When subjected to impact or deformation, the material can deform and then return to its original shape, maintaining the seal automatically without requiring additional gasket components. This self-service capability eliminates the need for separate sealing elements and simplifies the assembly process.
Solution Approach 2:
The modified composite material performs multiple functions simultaneously: it provides structural support, shock absorption, and sealing capabilities all in one component. This multi-functionality eliminates the need for separate gasket components, reducing assembly complexity while maintaining impact resistance.
3Ease of manufacture
If traditional composite material is used with uniform weave, then manufacturing is simpler, but the material lacks the flexibility needed for optimal blade contact during impacts
Solution Approach 1:
The patent modifies the material composition parameter by adding elastomer to the composite formula, changing it from a rigid traditional composite to a flexible elastomer-modified composite. This parameter change maintains manufacturing simplicity while providing the required flexibility for optimal blade contact during impacts.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This design enhances the platform's flexibility and reduces the risk of damage during impacts without additional seals, simplifying the manufacturing process and reducing costs.
Implementation Method 1
the fibrous reinforcement present in the central portion has a three-dimensional weave, and in that the fibrous reinforcement present in each of the first and second edges comprises at least a first strip of fabric in a first portion having a two-dimensional weave
Data Source
Figure 1~2
Figure 3A~3B
Figure 4A~4B
AI summary
The invention relates to an inserted platform (1) intended for being positioned between two adjacent blades of an aeronautical turbine engine fan, said platform comprising a flow section wall (10) made of composite material including a central portion (16), and first and second edges (18) extending in a longitudinal direction of said wall, each edge extending over a predetermined distance (D) from the central portion (16) in a transverse direction of said wall, said flow section wall comprising a fibrous reinforcement densified by a matrix, characterised in that the fibrous reinforcement present in the central portion (16) has a three-dimensional weave, and in that the fibrous reinforcement present in the first and second edges (18) has at least in part a two-dimensional weave. The invention also relates to a fan module, a turbine engine and a method for manufacturing such a platform.