Ceramic Matrix Composite Turbine Vane with Metallic Spar
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Solution Overview
Problem
The integration of ceramic matrix composite materials into gas turbine engines poses challenges due to mechanical characteristics such as strength and coefficients of thermal expansion, requiring innovative solutions for effective coupling with other components.
Innovation Solution
A turbine vane assembly comprising an airfoil and endwall made of ceramic matrix composite materials, with a metallic spar that carries loads and includes a spar body, spar tail, and retainer to securely position and support the airfoil, along with an inner panel to block fluid communication and an outer endwall to define the primary gas path boundaries.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If ceramic matrix composite materials are integrated into static vane assemblies, then high-temperature capability is improved, but mechanical coupling challenges arise due to differences in strength and coefficients of thermal expansion
Solution Approach 1:
The patent employs ceramic matrix composite (CMC) materials for the airfoil and endwall components, combining ceramic materials with matrix and reinforcement elements to create a composite structure that maintains high-temperature capability while improving mechanical properties and coupling compatibility with metallic components
Solution Approach 2:
The metallic spar acts as an intermediary component between the ceramic airfoil and other engine components, providing a transition zone that accommodates the mechanical property differences between ceramic and metallic materials through careful design of the spar body and its connection interfaces
2Temperature
If ceramic matrix composite materials are used in the airfoil and endwall, then turbine entry temperatures can be increased, but the complexity of coupling with other components increases
Solution Approach 1:
The assembly is segmented into distinct components (airfoil, endwall, spar) with clearly defined interfaces, allowing each component to be optimized independently for its material properties while simplifying the overall coupling process through modular assembly
3Strength
If the spar body engages the radial-inner wall radially inward toward the boundary of the primary gas path, then load carrying capability is improved, but chemical interaction between metallic and ceramic components may occur
Solution Approach 1:
The engagement interface between the metallic spar body and ceramic radial-inner wall is designed with localized contact areas and specific geometric features that concentrate loads in regions optimized for each material's properties while minimizing the surface area exposed to high-temperature gas paths where chemical interaction could occur
Data Source
AI summary
A turbine vane assembly adapted for use in a gas turbine engine includes an airfoil, an endwall, and a spar. The airfoil is shaped to interact with hot gases moving axially along a primary gas path of the gas turbine engine. The endwall is shaped to define a boundary of the primary gas path near a radial end of the airfoil. The spar is located in an interior region of the airfoil to carry loads that act on the airfoil during operation of the gas turbine engine.