Gas Turbine CMC Static Vane Clusters with Brazed Joints
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Solution Overview
Problem
The assembly of ceramic matrix composite (CMC) static vanes in gas turbine engines poses challenges due to the high temperatures and the need for robust and reliable bonding of individual vanes to form a continuous hoop structure.
Innovation Solution
The method involves forming airfoils and platforms separately from CMC materials and using a bonding process, specifically brazing with a silicon-containing alloy, to connect them, utilizing frusto-conical bond surfaces for a wide contact area and applying compressive force with heat to create a robust connection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If CMC materials are used for turbine section components to withstand high temperatures, then temperature resistance is improved, but assembly difficulty increases
Solution Approach 1:
The static vane assembly is divided into multiple individual CMC vanes that can be separately manufactured and then assembled together to form a complete hoop structure. This segmentation allows each vane to be independently fabricated using CMC materials while maintaining the overall structural integrity through controlled bonding interfaces.
Solution Approach 2:
A bonding process using a bonding material is introduced as an intermediary between the CMC vane components during assembly. This bonding material facilitates the joining of high-temperature CMC components, enabling their assembly while maintaining the temperature resistance properties of the base materials.
2Stability of the object's composition
If multiple CMC static vanes are assembled together to form a continuous hoop, then structural integrity is improved, but bonding reliability becomes critical
Solution Approach 1:
Multiple individual CMC vanes are merged together through bonding to form a continuous hoop structure. This merging process combines the strength and temperature resistance of individual CMC components into a unified structural assembly, achieving both structural integrity and thermal performance.
Solution Approach 2:
A bonding material serves as an intermediary substance that creates reliable connections between the CMC vane components. This bonding material is specifically selected and applied to ensure the bonded joints can withstand the high-temperature operating conditions while maintaining structural integrity.
3Ease of manufacture
If vanes are formed as individual components rather than a single piece, then manufacturing flexibility is improved, but assembly complexity increases
Solution Approach 1:
The static vane structure is segmented into multiple individually manufacturable components that can be produced using CMC fabrication processes. This segmentation provides manufacturing flexibility by allowing each vane to be independently formed, coated, and prepared before assembly, while the standardized bonding process manages the resulting assembly complexity.
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 approach results in a reliable and robust connection that can withstand high temperatures, ensuring the integrity of the vane assembly and enhancing the durability of the turbine section components.
Implementation Method 1
using a bonding process, specifically brazing with a silicon-containing alloy, to connect them
Implementation Method 2
applying compressive force with heat to create a robust connection
Data Source
Figure 1
Figure 2A~3F
Figure 3C
AI summary
A multiple static vane component includes a plurality of airfoils (120) each formed of ceramic matrix composite materials. Each of the airfoils (120) are attached to an inner platform (126) and an outer platform (116) both formed of ceramic matrix composite materials. There is a plurality of individual parts forming the plurality of airfoils (120), the inner platform (126) or the outer platform (116), bonded to each other with a braze joint. A gas turbine engine (20) and a method are also disclosed.