Ceramic Matrix Composite Vane Endwall Integration with Turbine Shroud
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Solution Overview
Problem
Design and manufacture of turbine components in gas turbine engines using composite materials are challenging due to geometry and strength limitations, particularly in accommodating different thermal expansion rates between ceramic matrix composite materials and metallic materials.
Innovation Solution
A turbine section with a metallic case and ceramic matrix composite flow path ring, supported by a mounting system with spring mounts that allow radial movement to accommodate thermal expansion differences, and a seal at the interface between the turbine vane and flow path ring to maintain efficient operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If ceramic matrix composite materials are used for the flow path ring to withstand higher temperatures, then temperature resistance is improved, but thermal expansion compatibility with metallic case deteriorates
Solution Approach 1:
The mounting system incorporates spring mounts that allow dynamic adjustment and movement to accommodate the different thermal expansion rates between the ceramic matrix composite flow path ring and the metallic case, resolving the stability issue while maintaining high temperature resistance
Solution Approach 2:
The system changes the mounting parameters by using elastic spring mounts instead of rigid connections, allowing the mounting system to adapt to thermal expansion differences through elastic deformation while maintaining structural integrity at high temperatures
2Manufacturing precision
If rigid mounting system is used to maintain precise radial position, then positioning precision is improved, but adaptability to thermal expansion differences deteriorates
Solution Approach 1:
The spring mounts provide a dynamic mounting system that maintains precise radial positioning through elastic forces while automatically adapting to thermal expansion differences between dissimilar materials, eliminating the need for rigid fixed-position mounting
3Temperature
If composite materials are used for flow path components, then temperature resistance is improved, but manufacturing complexity deteriorates
Solution Approach 1:
The turbine section is segmented into distinct components with different materials (metallic case, ceramic matrix composite flow path ring) mounted separately, allowing each component to be manufactured using optimal processes for its material properties while maintaining assembly simplicity
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 enables the use of ceramic matrix composite materials for higher temperature resistance, reduces cooling air usage, and maintains radial position of the flow path ring relative to the case, improving the overall efficiency of the gas turbine engine by accommodating thermal expansion differences.
Implementation Method 1
The mounting system may include a plurality of spring mounts arranged to extend between the flow path ring and the case and configured to elastically deform
Implementation Method 2
The turbine vane and the flow path ring may be free for radial movement relative to each other to accommodate different rates of thermal expansion experienced by the ceramic matrix composite materials of the flow path ring and the metallic materials of the case
Data Source
AI summary
A turbine section of a gas turbine engine includes a case, a plurality of flow path components, and a mounting system. The case extends circumferentially around a central axis of the gas turbine engine. The plurality of flow path components includes a turbine vane, a turbine blade, and a flow path ring. The mounting system is configured to couple the flow path ring to the case.