Ceramic Matrix Composite Turbine Vane Integrated Platform Joint
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Solution Overview
Problem
Design and manufacture of vanes and blades from composite materials in gas turbine engines face challenges due to the need for high-temperature resistance and specific geometry and strength requirements, which existing technologies struggle to meet effectively.
Innovation Solution
A turbine vane design incorporating a vane core tube, vane cover overwrap, and platform insert, all made from ceramic matrix composite materials, with a three-dimensional woven ceramic structure that eliminates filler material and strengthens joints between components, enhancing the structural integrity and thermal resistance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If composite materials are used for vanes and blades, then high-temperature resistance is improved, but manufacturing complexity and structural integrity challenges increase
Solution Approach 1:
The patent combines the airfoil and platform into a single integrated ceramic matrix composite structure, eliminating the need for separate components and complex joining processes. This integration maintains high-temperature resistance while simplifying manufacturing by reducing the number of parts and assembly steps required.
Solution Approach 2:
The patent utilizes ceramic matrix composite materials that inherently provide high-temperature resistance while maintaining structural integrity. The composite structure allows for optimized material properties that withstand thermal environments without requiring additional protective measures or complex cooling systems.
2Temperature
If composite materials are used for vanes and blades, then high-temperature resistance is improved, but achieving desired geometry and strength becomes more difficult
Solution Approach 1:
The patent employs preliminary shaping of the ceramic matrix composite structure during manufacturing, where the airfoil and platform are formed with precise geometric features and structural reinforcements built-in from the outset. This preliminary action ensures that geometry and strength requirements are met before the component enters service, eliminating the need for post-manufacturing adjustments.
Solution Approach 2:
The patent implements local quality enhancements by concentrating material density and structural reinforcement in specific areas of the integrated vane where geometric precision and strength are critical. This localized optimization ensures that geometry and strength requirements are met in key areas without compromising the overall high-temperature resistance of the entire structure.
3Adaptability or versatility
If multiple components are assembled to form the vane, then design flexibility is improved, but joint strength and structural integrity deteriorate
Solution Approach 1:
The patent merges the airfoil and platform into a single integrated ceramic matrix composite structure, eliminating joints and connections between components. This consolidation maintains design flexibility through monolithic construction while ensuring maximum structural integrity by removing potential weak points at joints and interfaces.
Data Source
AI summary
An integral, one-piece ceramic matrix composite turbine vane adapted for use in a gas turbine engine includes an airfoil and two platforms. The airfoil extends radially relative to an axis of the gas turbine engine between the first platform and the second platform. The platforms extend circumferentially partway about the axis of the gas turbine engine.