Ceramic Matrix Composite Seal Segment with Integrated Cooling Passages
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Solution Overview
Problem
Turbine shroud assemblies in gas turbine engines face challenges due to components with different thermal expansion coefficients, leading to uneven expansion and potential structural issues under high temperatures, which can affect the longevity and performance of the engine.
Innovation Solution
A turbine shroud assembly comprising a carrier made of metallic materials, a seal segment with ceramic matrix composite materials, and a mount pin assembly that includes air passages to regulate temperature, reducing heat transfer to the pins and enhancing structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If components with different thermal expansion coefficients are used in the turbine shroud assembly, then the assembly can accommodate high temperature exposure, but uneven expansion occurs leading to structural issues
Solution Approach 1:
The patent changes the material parameter (thermal expansion coefficient) by using ceramic matrix composite materials with thermal expansion characteristics matched to the carrier, eliminating differential expansion. It also changes the temperature parameter by implementing cooling passages that maintain lower operating temperatures in the seal segment, reducing thermal stress and expansion issues.
2Temperature
If metallic materials are used for the carrier and ceramic matrix composite materials for the seal segment, then the assembly can withstand high temperatures, but heat transfer to the pins increases causing thermal stress
Solution Approach 1:
The cooling passages act as an intermediary thermal management system, introducing cooling air as a mediator to control heat transfer. This intermediary mechanism regulates the thermal environment of the pins, reducing heat-directed stress while maintaining the high-temperature capability of the metallic carrier and ceramic seal segment combination.
3Temperature
If cooling passages are integrated into the seal segment, then temperature regulation is achieved, but the device complexity increases
Solution Approach 1:
The cooling passages are merged directly into the seal segment structure, combining the cooling function with the existing seal segment component. This integration approach achieves temperature regulation without adding separate cooling devices, thereby minimizing the increase in device complexity while effectively managing thermal loads on the pins.
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 effectively manages thermal expansion and reduces heat-directed stress on the pins, thereby enhancing the durability and performance of the turbine shroud assembly by regulating temperature and distributing heat effectively.
Implementation Method 1
air passages to regulate temperature, reducing heat transfer to the pins
Implementation Method 2
regulate temperature by distributing heat effectively
Implementation Method 3
components with different thermal expansion coefficients, leading to uneven expansion
Data Source
AI summary
A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount pin assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mount pin assembly is configured to couple the seal segment to the carrier.