CMC Vane Multiplet With Conjoined Singlets
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Solution Overview
Problem
Implementing ceramic matrix composite (CMC) materials in gas turbine engine airfoils is challenging due to difficulties in creating structural multiplets that meet both leakage reduction and structural performance goals, especially since traditional casting methods cannot be used for CMCs.
Innovation Solution
The use of CMC singlet vanes arranged circumferentially with a CMC overwrap that includes fiber plies fused to both platforms, bridging mateface seams and forming a dovetail fitting to secure the vane multiplet to a carrier, effectively eliminating gas path leakage and enhancing structural support.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If traditional casting methods are used to create airfoils, then manufacturing ease is maintained, but CMC material implementation is impossible
Solution Approach 1:
The patent replaces traditional mechanical casting methods with a fiber ply-based construction system. CMC fiber plies are laid up in molds and cured to form airfoils, substituting the casting process with a composite material fabrication process that enables CMC implementation while maintaining manufacturability
Solution Approach 2:
The patent uses ceramic matrix composite (CMC) materials constructed from fiber plies to create airfoils. This composite material approach enables the use of advanced CMC materials that offer high-temperature resistance and other desirable properties while being manufacturable through fiber layup and curing processes
2Temperature
If CMC singlet vanes are used, then high-temperature resistance is achieved, but gas path leakage increases due to mateface seams
Solution Approach 1:
The patent merges multiple CMC singlet vanes into a multiplet assembly where the outer surfaces of adjacent vanes are bonded together. This merging eliminates the gas path leakage that would occur at mateface seams while maintaining the high-temperature resistance of CMC materials
Solution Approach 2:
The patent introduces an intermediary bonding process or material that joins the outer surfaces of adjacent CMC singlet vanes. This intermediary connection seals the mateface seams to prevent gas leakage while allowing the CMC vanes to maintain their thermal resistance properties
3Loss of energy
If CMC vanes are arranged in multiplets, then gas path leakage is reduced, but structural integrity becomes difficult to maintain
Solution Approach 1:
The patent combines multiple CMC singlet vanes into a multiplet structure where the vanes are bonded together at their interfaces. This merging creates a unified structure that maintains structural integrity while reducing gas path leakage through the eliminated mateface seams
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
This configuration reduces gas leakage between airfoil platforms, enhances structural integrity, and maintains high-temperature resistance, addressing the unique challenges of integrating CMCs into gas turbine engine vanes.
Implementation Method 1
A CMC overwrap conjoins the first and second CMC singlet vanes and includes fiber plies that are fused to both the platform of the first CMC singlet vane and the platform of the second CMC singlet vane
Data Source
AI summary
A vane multiplet includes first and second ceramic matrix composite (CMC) singlet vanes that are arranged circumferentially adjacent each other. Each of the CMC singlet vanes includes an airfoil section and a platform at one end of the airfoil section. The platform defines forward and trailing platform edges and first and second circumferential side edges. A CMC overwrap conjoins the CMC singlet vanes. The CMC overwrap includes fiber plies that are fused to the platforms of the CMC singlet vanes.