Combustor-to-Vane Brush Seal Assembly With Bypass Cooling Channels
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Solution Overview
Problem
Gas turbine engines face uncontrolled leakage and hot spot formation due to inadequate sealing between the combustor and turbine sections, which can lead to bow wave distress and reduced cooling effectiveness.
Innovation Solution
A brush seal assembly with a brush seal backing plate, retaining ring, and bristles, combined with cooling channels and passages that provide controlled cooling to maintain effective sealing and prevent hot spots, while accommodating operational movements like rocking and twisting.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If sealing arrangements are made to contact components throughout the range of operation, then sealing efficiency is improved, but device complexity increases due to additional cooling channels and passages
Solution Approach 1:
The sealing arrangement is merged with cooling channels and passages to create a multi-functional component that provides both sealing and cooling functions simultaneously, resolving the contradiction by integrating additional functions into the existing structure rather than adding separate systems
Solution Approach 2:
The sealing arrangement is designed to perform multiple functions including sealing, cooling, and thermal management throughout the operational range, allowing a single component to address multiple requirements and reduce overall system complexity
2Reliability
If cooling leakage is removed to improve sealing, then sealing efficiency is improved, but temperature increases causing hot spots and bow wave distress
Solution Approach 1:
The design converts the potentially harmful uncontrolled leakage into beneficial controlled cooling flow through specifically configured passages and channels, transforming a sealing defect into a thermal management advantage that prevents hot spots while maintaining sealing integrity
Solution Approach 2:
Different regions of the sealing arrangement have different properties - some areas provide sealing contact while others provide cooling flow paths, allowing localized optimization of both sealing and thermal management functions without compromising overall performance
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 enhances sealing efficiency, reduces uncontrolled leakage, and maintains cooling effectiveness, preventing hot spots and bow wave distress by ensuring consistent contact and controlled airflow, thereby improving the overall performance and reliability of gas turbine engines.
Implementation Method 1
at least one cooling channel extending from the exterior side of the combustor to the interior side of the combustor with respect to the combustion chamber. The at least one cooling channel configured to direct cooling air from the exterior side to the interior side
Implementation Method 2
a brush seal assembly with a brush seal backing plate, retaining ring, and bristles
Data Source
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AI summary
A brush seal system includes a component including a first mating surface (136). The brush seal system further includes a brush seal (110) including a brush seal backing plate (112), a retaining ring (114), and a plurality of bristles (116) retained between the brush seal backing plate (112) and the retaining ring (114). The brush seal backing plate (112) includes a second mating surface (138) mounted to the first mating surface (136). The brush seal system further includes at least one cooling channel (128) extending from an exterior side (130) of the component to an interior side (132) of the component so as to bypass the brush seal (110).