CMC Vane Arc Segment Flange Gusset Reinforcement
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Solution Overview
Problem
Implementing ceramic matrix composite (CMC) materials in gas turbine engine airfoils is challenging due to lower material stress limits compared to traditional superalloys, requiring innovative support schemes to manage aerodynamic and thermal stresses effectively.
Innovation Solution
The use of a vane arc segment with an airfoil fairing formed of CMC, featuring flanges and rib extensions that form gussets to reinforce the airfoil section, allowing for efficient load transmission and minimizing stress concentrations, along with angled circumferential mate faces and radial bearing faces to facilitate low-stress mounting and sealing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If CMC materials are used in airfoils to extend temperature capability, then temperature resistance is improved, but material stress limit decreases
Solution Approach 1:
The airfoil is divided into multiple vane arc segments that can be assembled together, allowing each segment to be independently supported and reducing stress concentration in the CMC material
Solution Approach 2:
The support structure extends from two-dimensional platform surfaces into the third dimension with flanges and rib extensions that form gussets, creating a three-dimensional load distribution network that reduces stresses on the CMC airfoil
2Strength
If flanges are added to vane arc segments for load transmission, then structural strength is improved, but device complexity increases
Solution Approach 1:
Multiple structural elements (flanges, rib extensions, and gussets) are merged into an integrated support scheme where the rib extension connects to the flange to form a unified gusset structure, reducing the number of separate components
Solution Approach 2:
The flanges serve multiple functions: providing mounting surfaces for support hardware, creating gussets with rib extensions for additional strength, and enabling load transmission from the airfoil to the support structure
Data Source
AI summary
A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.