CMC Vane Y-Weave Trailing Edge With No Post-Machining
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Solution Overview
Problem
CMC vanes face limitations in reducing the trailing edge radius due to minimum bend radius constraints, leading to larger sizes and suboptimal aerodynamics, and existing Y-weave plies require additional machining steps at the interface with platforms.
Innovation Solution
A CMC vane design incorporating a Y-weave ply with trimmed consolidated and wing plies that extend through platforms, blended with cap plies, eliminating the need for post-densification machining by matching curvature before densification.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Shape
If a Y-weave ply is used to reduce trailing edge radius, then the trailing edge radius is reduced below typical bend radius, but an extra machining step is required at the interface with platforms
Solution Approach 1:
The Y-weave ply is pre-formed with consolidated and wing plies configured to extend through the platforms before densification. This preliminary configuration eliminates the need for post-densification machining by ensuring the trailing edge geometry is already optimized before the manufacturing process completes.
Solution Approach 2:
The Y-weave ply is divided into consolidated and wing plies with specific configurations. The consolidated ply forms the core trailing edge structure while the wing plies extend through the platforms, allowing each segment to serve its specific function without requiring additional machining steps.
2Ease of manufacture
If fabric layup material is used for CMC vane, then the material can be manufactured, but the minimum bend radius causes the trailing edge to be much larger than metal vane counterparts
Solution Approach 1:
The patent uses a composite fabric layup structure with Y-weave ply configuration where consolidated and wing plies are woven together in part. This composite structure allows the material to be manufactured while achieving a compact trailing edge geometry that overcomes the minimum bend radius limitation of conventional fabric layup.
Data Source
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AI summary
A ceramic matrix composite (CMC) vane or layup therefor includes first and second platforms (110, 120), and an airfoil portion (130) extending therebetween. The airfoil portion (130) includes a first portion (210) of a shear tube (200) extending relatively orthogonal to the first and second platforms (110, 120), wherein the first portion (210) of the shear tube (200) extends through the first and second platforms (110, 120), and wherein the first portion (210) of the shear tube (200) defines a leading edge and a hollow core (205) of the airfoil portion (130). A second portion (220) of the shear tube (200) is connected to the first portion (210) of shear tube (200) and extends relatively orthogonal to the first and second platforms (110), wherein the second portion (220) of the shear tube (200) also extends through the first and second platforms (110, 120), and wherein the second portion (220) of the shear tube (200) includes a Y-weave ply and a trailing edge noodle that define a trailing edge of the airfoil portion (130).