SiC Ceramic Matrix Composite for Low-Porosity Turbine Components
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Solution Overview
Problem
Implementing ceramic matrix composites (CMCs) in gas turbine engines faces unique challenges due to their high temperature resistance requirements, particularly in areas like the compressor and turbine sections, where existing technologies struggle to maintain structural integrity and efficiency.
Innovation Solution
The development of ceramic matrix composites with specific fiber volume fractions (35-40%) and silicon carbide (SiC) reinforcement, combined with a silicon carbide matrix, and manufacturing processes such as chemical vapor infiltration (CVI) to create components like airfoils and blade outer air seals, enhancing mechanical properties and thermal stability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If CMC components are implemented in gas turbine engines to achieve high temperature resistance, then thermal stability is improved, but structural integrity and manufacturing reliability deteriorate due to unique challenges in maintaining consistent fiber volume fraction and reducing porosity
Solution Approach 1:
The invention applies parameter changes by optimizing the fiber volume fraction to a specific range (35-40%) and controlling porosity levels to achieve the desired balance between high temperature resistance and structural integrity. This involves adjusting processing parameters during manufacturing to ensure consistent material properties that maintain reliability at elevated temperatures
Solution Approach 2:
The invention utilizes composite materials by combining ceramic fibers with a matrix material to create CMC components. This composite structure provides both the high temperature resistance of ceramics and the structural integrity needed for gas turbine engine applications, addressing the reliability concerns through material design
2Temperature
If CMC components are implemented in gas turbine engines to achieve high temperature resistance, then thermal stability is improved, but manufacturing complexity increases due to challenges in producing consistent fiber volume fraction and low porosity
Solution Approach 1:
The invention simplifies manufacturing by establishing specific parameter ranges for fiber volume fraction (35-40%) and porosity control. These defined parameters provide clear manufacturing targets that reduce complexity in the production process while ensuring consistent quality and performance of CMC components
Solution Approach 2:
The invention addresses manufacturing complexity by controlling porosity to specific levels. By managing the porous structure within acceptable ranges, the invention balances the inherent porosity of CMC materials with manufacturing feasibility, making the production process more consistent and less complex
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
The solution provides improved mechanical properties and thermal stability, resulting in enhanced interlaminar strength and reduced porosity, thereby improving the performance and durability of CMC components in gas turbine engines.
Implementation Method 1
manufacturing processes such as chemical vapor infiltration (CVI)
Data Source
Figure 1~2
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Figure 4A~4D
AI summary
A ceramic matrix composite includes at least one ply (110) of ceramic fibers (112) and a ceramic matrix material (116) deposited on the ceramic fibers (112). A fiber volume fraction is between about 35-45% and an areal weight of the fibers is between about 150-450 g/m2. A method of fabricating a ceramic matrix composite component (108) is also disclosed.