Ceramic Matrix Composite Turbine Vane Assembly with Segmented Support
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Solution Overview
Problem
Design and manufacture of turbine vanes and blades from composite materials in gas turbine engines face challenges due to geometry and strength requirements, particularly in withstanding high temperatures and receiving force loads from hot gases.
Innovation Solution
A turbine vane assembly comprising ceramic matrix composite vanes supported by metallic segmented and full-hoop outer support rings with discrete spars, which are arranged radially and circumferentially to distribute and absorb force loads, reducing leakage and enhancing structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If ceramic matrix composite materials are used for turbine vanes to withstand high temperatures, then temperature resistance is improved, but structural strength and geometry precision become more difficult to achieve
Solution Approach 1:
The patent employs ceramic matrix composite (CMC) materials for turbine vanes, which combine ceramic fibers in a matrix structure to achieve both high-temperature resistance and mechanical strength. This composite approach allows the vanes to withstand combustion temperatures while maintaining structural integrity under centrifugal and thermal loads.
Solution Approach 2:
The support rings incorporate localized reinforcement features including ribs, circumferential strengthening elements, and varying wall thicknesses in specific regions. These local quality modifications enhance structural strength at critical areas without compromising the overall high-temperature performance of the CMC vanes.
2Strength
If full-hoop outer support ring is used to enhance structural robustness, then structural integrity is improved, but device complexity increases
Solution Approach 1:
The support system is divided into modular components: segmented inner support rings that can be assembled in sections, and a full-hoop outer support ring that provides continuous circumferential strength. This segmentation allows for easier manufacturing, assembly, and maintenance while achieving the desired structural integrity through the coordinated action of multiple components.
Solution Approach 2:
The patent combines multiple support functions into integrated structures: the outer support ring merges radial support, circumferential strengthening, and positioning functions into a single component. The support spars combine axial support with radial positioning features, reducing the total number of parts while maintaining structural robustness.
3Force
If discrete support spars extend through interior cavity of turbine vanes, then force load distribution is improved, but manufacturing precision requirements increase
Solution Approach 1:
The support spars are designed to extend through the interior cavities of the turbine vanes, with the spars nested within the vane structures. This nesting arrangement allows the spars to be installed through pre-formed cavities in the CMC vanes, reducing the need for high-precision external alignment while ensuring proper load transfer from the vanes to the support rings.
Solution Approach 2:
The support spars act as intermediary elements between the turbine vanes and the support rings, transferring force loads from the hot gas-exposed vanes to the structurally robust rings. This intermediary function distributes loads more evenly across the support structure while accommodating manufacturing tolerances through the spar's connection geometry and material compliance.
Data Source
AI summary
A turbine vane assembly for use in a gas turbine engine includes turbine vanes, a segmented inner vane support, and an outer vane support. The turbine vanes are arranged around a central axis of the engine. The inner vane support is arranged radially inwardly of the turbine vanes. The outer vane support includes a full-hoop outer support ring located radially outward of the plurality of turbine vanes and extends entirely circumferentially about the central axis. The outer vane support further includes a plurality of discrete support spars coupled to the full-hoop outer support ring and extending radially inward from the full-hoop outer support ring through an interior cavity of a respective turbine vane.