CMC Vane Arc Segment Single-Sided Platform Design
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Solution Overview
Problem
Implementing ceramic matrix composite (CMC) materials in gas turbine engine airfoils is challenging due to thermal gradients, interlaminar stresses, and manufacturing difficulties, particularly in forming the desired design shape and attaching CMC vanes without inefficient loading or stress issues.
Innovation Solution
The use of CMC vane arc segments with single-sided platforms that project from the airfoil section, featuring fiber layers with complementary contours and straight portions, which extend from the airfoil section to form self-supporting structures that manage aerodynamic loads and reduce stress through compression loading.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of stationary object
If CMC materials are used in airfoils to extend temperature capability and lifetime, then high temperature resistance is improved, but manufacturing difficulty and stress issues worsen
Solution Approach 1:
The vane is divided into multiple arc segments that can be manufactured separately and then assembled. Each segment contains an airfoil section with platforms, allowing modular manufacturing of CMC components that can be joined together to form complete vanes, thereby reducing individual manufacturing complexity while extending service life through modular replacement
Solution Approach 2:
The patent uses ceramic matrix composite (CMC) materials that combine ceramic fibers with a matrix material to create a composite structure. This composite approach provides high-temperature resistance while managing thermal stresses and improving manufacturability compared to monolithic ceramics, directly addressing both the temperature capability and manufacturing challenges
2Temperature
If CMC vanes are implemented to leverage compressive strength, then temperature resistance is improved, but interlaminar stress and tension issues worsen
Solution Approach 1:
The fiber architecture is varied in different regions of the CMC vane. The platforms have different fiber orientations and densities compared to the airfoil section, with specific attention to creating compressive stress states at the platforms where thermal gradients are most severe. This local optimization reduces interlaminar stresses while maintaining temperature resistance
Solution Approach 2:
The patent modifies the fiber architecture parameters (orientation, density, composition) in different regions of the CMC vane to optimize performance. By changing fiber parameters locally, the structure can better withstand thermal gradients and reduce interlaminar stresses while maintaining high-temperature capability
3Force
If single-sided platforms are designed to project from airfoil section, then load transfer efficiency is improved, but structural complexity worsens
Solution Approach 1:
The platforms are integrated directly into the airfoil section as a unified CMC structure rather than being separate components. The fiber layer extends continuously from the airfoil section onto the platforms, creating an integrated load path that improves load transfer efficiency while avoiding the complexity of separate attachment mechanisms or joints
Data Source
AI summary
A vane arc segment includes ceramic matrix composite (CMC) fairing that has an airfoil section, a first single-sided platform at the outer radial end projecting from the suction side wall, and a second single-sided platform at the inner radial end projecting from the pressure side wall. The first single-sided platform is comprised of a fiber layer that extends from the airfoil section and turns into the first single-sided platform, and the second single-sided platform is comprised of the fiber layer that from the airfoil section and turns into the second single-sided platform.