CMC Turbine Component Reinforcement for Mounting Loads
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Solution Overview
Problem
Gas turbine engines face challenges due to the high resistance of ceramic matrix composite (CMC) components to temperature, which are used to withstand the hot products of combustion, but existing designs do not effectively manage mechanical forces and stresses.
Innovation Solution
A gas turbine engine component is designed with an inner and outer surface formed of ceramic matrix composite layers, incorporating a mount member and an insert within the outer platform to form a thickened portion that reacts against mechanical forces, using a 3D woven insert or monolithic structure to enhance structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If CMC material is used to form turbine components, then temperature resistance is improved, but mechanical strength and structural integrity deteriorate
Solution Approach 1:
The patent uses ceramic matrix composite (CMC) material that combines ceramic fibers in a ceramic matrix to create a material that maintains both high-temperature resistance and improved mechanical strength. The composite structure allows the material to withstand both thermal and mechanical loads simultaneously.
Solution Approach 2:
The patent implements a thickened portion at the load bearing feature location, creating local reinforcement where mechanical strength is most needed. This allows the component to maintain overall CMC temperature resistance while having localized areas of enhanced mechanical strength to handle mounting loads.
2Temperature
If CMC material is used to form turbine components, then temperature resistance is improved, but resistance to mechanical forces deteriorates
Solution Approach 1:
The patent creates a localized thickened portion at the load bearing feature where mechanical force resistance is most critical. This local reinforcement provides enhanced force resistance at the mounting interface while preserving the overall component's temperature resistance properties.
Solution Approach 2:
The CMC composite material provides inherent toughness and damage tolerance that helps resist mechanical forces while maintaining temperature resistance. The fiber-reinforced structure prevents catastrophic failure under mechanical loading.
3Ease of manufacture
If uniform thickness CMC layers are used, then manufacturing simplicity is improved, but structural integrity under load deteriorates
Solution Approach 1:
The patent introduces a thickened portion at the load bearing feature location, creating non-uniform thickness only where mechanical strength is needed. This localized modification provides enhanced structural integrity at critical areas while maintaining relatively simple manufacturing processes for the overall component.
Solution Approach 2:
The patent segments the component into regions of different thickness - a thickened portion at the load bearing feature and thinner sections elsewhere. This segmentation allows optimization of material distribution to match stress patterns, providing structural integrity where needed while minimizing material usage.
Data Source
Figure 1
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Figure 4A~4F
AI summary
A gas turbine engine component (104) includes an inner surface (108) and an outer surface (106). The outer surface and the inner surface are formed of ceramic matrix composite layers, and mount member (116). The mount member (116) is in contact with an insert (124) that is inserted within outer layers (128) of the outer platform (106) to form a thickened portion (120) having an end surface (125) that will react against forces from the mount member (116).