Undulated Ceramic Matrix Composite Hangers for Gas Turbine Engines
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Solution Overview
Problem
Ceramic matrix composite components in gas turbine engines face stress limitations, necessitating increased strength and rigidity to withstand operational stresses without material modification.
Innovation Solution
Incorporating undulated portions with arcuate peaks and troughs in ceramic matrix composite hangers to increase stiffness, allowing direct engagement with metallic brackets while using coating materials to control engagement points and prevent grinding into the composite material.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If ceramic matrix composite components are used in gas turbine engines, then weight is reduced and temperature resistance is improved, but stress承受能力 is insufficient
Solution Approach 1:
The patent applies curved/arcuate geometries to the hanger structure, specifically using arcuate peaks and troughs in the hanger design. These curved features increase the structural stiffness and stress-bearing capacity of the ceramic matrix composite hanger without changing the material itself, thereby resolving the contradiction between using temperature-resistant ceramics and achieving sufficient stress承受能力.
2Strength
If the hanger structure is made stiffer to withstand stresses, then stress承受能力 is improved, but the complexity of the component increases
Solution Approach 1:
The hanger is divided into distinct functional segments: arcuate peaks, arcuate troughs, and straight portions. Each segment serves a specific purpose in distributing stresses and engaging with mating structures. This segmentation allows the complex stiffening geometry to be systematically organized and manufactured, reducing the practical complexity despite the increased structural sophistication.
3Manufacturing precision
If coating material is added to control engagement points, then manufacturing precision is improved, but the device complexity increases
Solution Approach 1:
Coating material is applied selectively to specific localized areas of the hanger, particularly to the arcuate troughs where engagement with the bracket occurs. This local application of coating provides precise control over engagement points and tolerances only where needed, rather than uniformly increasing complexity across the entire component.
Data Source
AI summary
An assembly adapted for use in a gas turbine engine is disclosed herein. The assembly includes a first component including metallic materials and a second component including ceramic matrix composite materials. A portion of the second component is configured to engage a portion of the first component directly so that the second component is supported in a predetermined position.


