Gas Turbine CMC Component with Graded Thermal Conductivity
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engine components, particularly in the combustion and turbine sections, face challenges in withstanding elevated temperatures, and existing ceramic matrix composite (CMC) materials may not effectively manage local thermal gradients for prolonged useful life.
Innovation Solution
A component for a gas turbine engine is designed with multiple regions of different CMC materials, each with distinct thermal conductivity, strategically positioned to alter the thermal profile and manage temperature gradients, achieved through varying the density and fiber arrangement of CMC plies in these regions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If CMC materials are used to withstand elevated temperatures in combustion and turbine sections, then temperature resistance is improved, but thermal gradient management remains insufficient
Solution Approach 1:
The patent applies local quality by creating regions with different thermal conductivities within the CMC component. Specifically, it uses a first CMC material with a first thermal conductivity in a first region, and a second CMC material with a second thermal conductivity in a second region. This allows different parts of the component to have tailored thermal properties, enabling effective management of thermal gradients while maintaining overall temperature resistance.
Solution Approach 2:
The patent employs composite materials by combining different CMC materials with distinct thermal conductivities into a single component. The first CMC material and second CMC material are integrated such that they work together to manage thermal profiles, demonstrating the composite materials principle where multiple material properties are combined to achieve superior overall performance.
2Ease of manufacture
If uniform CMC material is used throughout the component, then manufacturing is simplified, but thermal profile control is insufficient
Solution Approach 1:
The patent implements local quality by varying the thermal conductivity of different regions within the component. The first region uses a first CMC material with a specific thermal conductivity, while the second region uses a second CMC material with a different thermal conductivity. This spatial variation in material properties enables precise thermal profile control while maintaining a relatively straightforward manufacturing process through co-bagging or sequential bagging techniques.
Solution Approach 2:
The patent applies parameter changes by modifying the thermal conductivity parameter across different regions of the component. By selecting CMC materials with different thermal conductivities for different regions, the patent optimizes the thermal profile without requiring complex manufacturing processes, thus balancing thermal control with manufacturing ease.
3Productivity
If higher operating temperatures are implemented for efficiency, then engine efficiency is improved, but component durability decreases
Solution Approach 1:
The patent uses local quality to address the durability-temperature contradiction by creating regions with different thermal conductivities. The first CMC material with its first thermal conductivity and the second CMC material with its second thermal conductivity are strategically positioned to manage thermal gradients, allowing the component to withstand higher operating temperatures for improved efficiency while maintaining durability through optimized thermal stress distribution.
Solution Approach 2:
The patent employs composite materials by integrating multiple CMC materials with different thermal properties into a single component structure. This composite approach enables the component to handle higher operating temperatures required for improved engine efficiency while the varied thermal conductivities protect against thermal gradient-induced degradation, thereby extending component useful life.
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 enhances the durability and operational life of gas turbine engine components by minimizing thermal stresses and ensuring uniform temperature distribution across the component, thereby improving the engine's efficiency and performance.
Implementation Method 1
the first region defines a first thermal conductivity, the second region defines a second thermal conductivity, wherein the first thermal conductivity is different than the second thermal conductivity to alter a thermal profile of the component
Data Source
AI summary
A component for a gas turbine engine includes a first region formed substantially of a first CMC material, wherein first region defines a first thermal conductivity. The component further includes a second region formed substantially of a second CMC material, wherein the second region defines a second thermal conductivity. Further, the component defines a thickness and the first region is positioned adjacent to the second region along the thickness, wherein the first thermal conductivity is different than the second thermal conductivity to alert a thermal profile of the component.