Ceramic Matrix Composite Gas Turbine Blade with Monolithic Ceramic Platform
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Solution Overview
Problem
Current gas turbine engine blades face limitations in operating temperature due to the thermal constraints of conventional materials, necessitating the use of exotic metallic components and ceramic matrix composites to enhance high-temperature capabilities.
Innovation Solution
A turbine blade design incorporating a fiber-reinforced ceramic matrix composite airfoil portion and a monolithic ceramic root portion, with a refractory structure providing the platform and outer root, allowing for improved thermal resistance and aerodynamic efficiency through a fillet integration between the airfoil and platform.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If exotic metallic components and monolithic ceramic are used to increase operating temperatures, then temperature capability is improved, but material cost and manufacturing complexity increase
Solution Approach 1:
The patent employs a hybrid composite structure combining CMC layers (for high-temperature airfoil sections) with monolithic ceramic (for platform and root sections requiring machinability). This composite approach enables the blade to operate at higher temperatures while maintaining manufacturability through selective material placement based on functional requirements.
2Temperature
If CMC layers extend from root to airfoil tip encased in monolithic ceramic, then temperature resistance is improved, but ease of manufacture deteriorates
Solution Approach 1:
The patent applies different materials to different sections of the blade based on local functional requirements: CMC layers are used in the airfoil portion where high-temperature resistance is critical, while monolithic ceramic is used in the platform and root sections where machinability and structural integrity are prioritized. This local differentiation resolves the manufacturing complexity issue while maintaining temperature resistance.
3Strength
If monolithic ceramic provides platform and root, then structural integrity is improved, but adaptability to complex geometries deteriorates
Solution Approach 1:
The hybrid CMC-monolithic ceramic composite structure enables the platform and root sections to achieve both structural integrity from the monolithic ceramic and geometric adaptability from the CMC layers that can be formed into complex shapes before encasement in the monolithic ceramic shell.
Data Source
Figure 1~5
AI summary
A blade for a gas turbine engine includes a fiber reinforced ceramic matrix composite structure that provides an airfoil with an exposed exterior airfoil surface and a refractory structure that provides at least an outer portion of a root secured relative to the airfoil.