Gas Turbine Blade Compliant Layer Stress Distribution
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Solution Overview
Problem
Gas turbine engine components face challenges in withstanding elevated temperatures due to material limitations, particularly when different materials are used, leading to inefficiencies and increased emissions.
Innovation Solution
A ceramic matrix composite (CMC) component with a ceramic-free metallic compliant layer is bonded to its surface, allowing for engagement with metallic components and distributing stresses to prevent fracturing, while the compliant layer is processed to provide a desired configuration for secure mating with turbine wheels.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If CMC material is used to withstand elevated temperatures, then temperature resistance is improved, but compatibility and stress distribution with metallic components deteriorates
Solution Approach 1:
The patent applies composite materials by bonding a metallic compliant layer to a CMC substrate, creating a hybrid structure that combines the high-temperature resistance of CMC with the ductility and stress tolerance of metallic materials. This composite construction allows the component to withstand elevated temperatures while maintaining compatibility with metallic engine components through the intermediate metallic layer.
Solution Approach 2:
The metallic compliant layer serves as an intermediary between the CMC component and metallic engine components. This intermediate layer facilitates stress distribution and prevents direct contact between incompatible materials, thereby improving reliability and preventing fracturing while allowing the CMC to function in high-temperature environments.
2Productivity
If different materials are used to improve efficiency, then temperature capability is improved, but stress distribution and durability worsen
Solution Approach 1:
The patent applies local quality by providing the metallic compliant layer specifically at the engagement surfaces where stress concentration occurs, rather than throughout the entire component. This localized treatment maintains the high-temperature capability of the CMC bulk material while providing enhanced stress distribution and durability at the critical interface regions.
3Device complexity
If CMC components are engaged directly with metallic components, then device complexity is reduced, but stress concentration and fracturing increase
Solution Approach 1:
The metallic compliant layer bonded to the CMC substrate creates a composite structure that combines the advantages of both materials. This relatively simple composite construction provides improved stress distribution and durability at engagement surfaces without significantly increasing device complexity, as the layer can be applied through conventional coating or bonding processes.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution enhances the durability and efficiency of gas turbine engine components by absorbing and distributing localized stresses, preventing fracturing and improving the fit between CMC and metallic components, thus improving the engine's performance and reducing material failure under elevated temperatures.
Implementation Method 1
a ceramic-free compliant layer bonded to a surface of the CMC material... absorbing and distributing localized stresses, preventing fracturing
Data Source
AI summary
A blade for a gas turbine engine comprises a blade portion having a first end and a second end and an engagement portion including a first surface coupled to the second end of the blade portion and a second surface coupled to the second end of the blade portion, the first and second surfaces arranged to extend divergently away from one another. The engagement portion is adapted for coupling to a wheel included in a gas turbine engine wheel.