Turbine Vane Ceramic Matrix Composite Spar Support Sliding Interface
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Solution Overview
Problem
Gas turbine engine vane assemblies face challenges due to the mismatch in thermal expansion coefficients between ceramic matrix composite materials and metallic components, leading to stress and potential failure under high-temperature conditions.
Innovation Solution
A turbine vane assembly design featuring a spar support with sliding interfaces between metallic and ceramic matrix composite components, allowing for relative movement to accommodate thermal expansion differences, and incorporating load transfer pins and low-friction coatings to manage loads and reduce friction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If ceramic matrix composite materials are used for turbine vanes to withstand high temperatures, then temperature resistance is improved, but thermal expansion mismatch with metallic components causes stress and potential failure
Solution Approach 1:
The metallic spar support is divided into multiple segments with sliding interfaces between them, allowing each segment to move independently to accommodate thermal expansion differences between the ceramic matrix composite vane and metallic support structures
Solution Approach 2:
The spar support transitions from a rigid fixed structure to a dynamic structure with sliding interfaces that allow relative movement between metallic segments, enabling the support to adapt to thermal expansion variations while maintaining structural integrity
2Stability of the object's composition
If a fixed rigid spar support is used to maintain vane position, then position stability is improved, but thermal expansion differences cause stress concentration and potential failure
Solution Approach 1:
The rigid fixed spar support is segmented into multiple sections with sliding interfaces, allowing the structure to maintain positional stability through coordinated movement of segments while distributing thermal stress across multiple interfaces rather than concentrating it at single fixed points
3Reliability
If sliding interfaces are introduced to accommodate thermal expansion, then stress management is improved, but device complexity increases
Solution Approach 1:
Low-friction coating layers are introduced as intermediary elements at the sliding interfaces between metallic segments, reducing friction and wear to enable smooth relative movement that accommodates thermal expansion while maintaining simple interface geometry and avoiding complex mechanical components
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 design effectively manages thermal expansion mismatches, ensuring the ceramic matrix composite vanes operate within safe stress limits, maintaining structural integrity and efficiency under high-temperature conditions.
Implementation Method 1
The sliding of the inner support member relative to the outer support member may accommodate different rates of thermal expansion experienced by the ceramic matrix composite materials of the turbine vane and the metallic materials of the spar support during use in the gas turbine engine
Implementation Method 2
The low-friction coating may have a coefficient of friction lower than that of the outer support member and the inner support member to encourage sliding between the outer support member and the inner support member
Data Source
AI summary
A turbine vane assembly adapted for use in a gas turbine engine includes a turbine vane and a spar support. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gases through a primary gas path of the turbine vane assembly. The spar support comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case.