Pin-Mounted CMC Heat Shields With Targeted Impingement Cooling
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Solution Overview
Problem
Ceramic matrix composite (CMC) materials used in gas turbine engine shrouds face challenges due to thermal expansion and material properties, particularly when coupled with traditional cooling methods, leading to potential deformation and reduced pin life.
Innovation Solution
A turbine shroud assembly with a ceramic matrix composite blade track segment and metallic support structure, featuring cooling passageways that direct cooling air onto preselected areas between the shroud wall and pins to dissipate heat before it reaches the pins, using impingement cooling to manage thermal gradients.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional cooling methods are used with ceramic matrix composite components, then the shroud can withstand high temperatures, but thermal expansion and material properties cause deformation and reduced pin life
Solution Approach 1:
The patent applies local quality by implementing impingement cooling at specific preselected areas on the attachment flange rather than uniform cooling across the entire component. Cooling air is directed precisely at the regions between the shroud wall and pins, creating localized cooling zones that address thermal gradients where they most affect pin reliability while preserving the high-temperature resistance of the CMC material in other areas.
Solution Approach 2:
The patent uses cooling air as an intermediary substance to transfer heat away from critical areas. The cooling air flows through passages in the metallic support structure and impinges on preselected areas of the attachment flange, acting as a thermal mediator that absorbs heat before it reaches the pins, thereby protecting them from thermal damage while allowing the shroud to operate at high temperatures.
2Reliability
If cooling air is directed at preselected areas between shroud wall and pins, then thermal gradients are managed and pin deformation is reduced, but the device complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the cooling function into discrete passages within the metallic support structure. Rather than a single complex cooling system, multiple cooling passages are distributed throughout the structure, each directing cooling air to specific preselected areas on the attachment flange. This segmented approach manages thermal gradients effectively while keeping the overall design modular and manageable.
Solution Approach 2:
The patent utilizes composite construction by combining ceramic matrix composite material for the shroud wall with a metallic support structure that incorporates cooling passages. This composite material approach allows the CMC to withstand high temperatures while the metallic structure provides integrated cooling capability, distributing the functional requirements across different materials to manage complexity.
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 gradients, reducing deformation and extending the life of the pins by dissipating heat through targeted cooling, thereby enhancing the durability and performance of the shroud assembly.
Implementation Method 1
The cooling passageway may be shaped to direct cooling air onto a preselected cooling area of the attachment flange included in the blade track segment
Implementation Method 2
heat absorbed by the shroud wall during use of the turbine shroud assembly is dissipated by the cooling air directed onto the preselected cooling area before being conducted to the pin
Data Source
AI summary
An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a pin. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The pin couples the blade track segment to the carrier segment. The carrier segment may include cooling passageways to conduct cooling air to preselected cooling areas located on the blade track segment.


