Ceramic Matrix Composite Hanger Heat Shield for Gas Turbine Shroud
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Solution Overview
Problem
Gas turbine shroud assemblies face challenges in managing heat transfer and maintaining structural integrity, particularly in high-temperature environments, where existing solutions often require dedicated cooling flows and complex mounting systems.
Innovation Solution
The turbine shroud assembly incorporates ceramic matrix composite materials for the blade track segment and a mounting assembly with forward and aft hangers, along with hanger heat shields made of different metallic materials, to reduce heat transfer and provide structural support, allowing for efficient heat management without dedicated cooling flows and enhancing the assembly's reliability by capturing failed hangers within a seal segment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If metallic materials are used for hangers in high-temperature environments, then structural support is provided, but heat transfer and radiation loading increase
Solution Approach 1:
A ceramic thermal barrier coating is applied to the hangers as an intermediary layer between the hot gas environment and the metallic hanger material. This coating acts as a thermal insulator, reducing heat transfer to the hanger while maintaining structural support functionality.
Solution Approach 2:
The hanger system utilizes composite construction by combining metallic materials for structural support with ceramic materials for thermal protection. This composite approach allows the assembly to withstand high-temperature environments while maintaining mechanical strength.
2Temperature
If dedicated cooling flows are implemented, then heat management is improved, but system complexity and fuel consumption increase
Solution Approach 1:
The thermal barrier coating provides passive thermal protection without requiring active cooling systems. The coating itself performs the heat management function through its inherent insulating properties, eliminating the need for dedicated cooling flows and associated complexity.
Solution Approach 2:
The cooling function is extracted from the hanger system by applying a thermal barrier coating that provides inherent thermal protection. This removes the need for complex cooling flows and associated system complexity.
3Temperature
If ceramic matrix composite materials are used for blade track segment, then heat resistance is improved, but mounting complexity increases
Solution Approach 1:
A mounting assembly with thermal barrier coatings serves as an intermediary between the ceramic blade track segment and the metallic hanger system. This assembly simplifies the mounting process while maintaining the heat resistance benefits of ceramic materials.
Solution Approach 2:
The mounting assembly utilizes composite materials combining ceramic and metallic components, allowing the ceramic blade track segment to be mounted to metallic hangers through a simplified interface that accommodates the different material properties.
4Temperature
If thermal barrier coatings are applied to hangers, then heat transfer is reduced, but manufacturing complexity increases
Solution Approach 1:
The thermal barrier coating process utilizes plasma spray technology, which deposits ceramic material in a controlled plasma environment. This process parameters approach allows for efficient application of the coating with standardized procedures, reducing manufacturing complexity despite the additional coating step.
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 configuration effectively lowers the temperature of the hangers, eliminates radiation loading, and improves the Specific Fuel Consumption (SFC) by eliminating the need for dedicated cooling flows, while also providing a robust structural support system that manages failure modes effectively.
Implementation Method 1
heat conducted from the flow surface of the runner to the exterior surface of the runner radiates toward the radially-inwardly facing surface of the forward and aft hangers
Implementation Method 2
The hanger heat shields are arranged radially between the exterior surface of the runner and the radially-inwardly facing surfaces of the forward and aft hangers... to reduce the amount of heat transfer to the forward and aft hangers from the exterior surface of the runner
Data Source
Figure 1~2
Figure 3~4
Figure 5
AI summary
A turbine shroud assembly (22, 222) of a gas turbine engine (10) includes blade track segment (26, 226) made from ceramic matrix composite materials. A mounting assembly (28, 228) is used to support the blade track segment (26, 226) and has hanger heat shields (44, 244, 45, 245) adapted to resist radiant heating from the blade track segment (26, 226), especially portions of the blade track segment (26, 226) adjacent to a gas flow path (25) along the turbine shroud assembly (22, 222).