Gas Turbine Combustor Seal System for Wear Reduction
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Solution Overview
Problem
Conventional combustor seal systems for gas turbine engines face issues with wear due to rubbing and require multiple sealing pieces, increasing potential failure and air leakage points, especially when the rear inner discharge nozzle and nozzle guide vane move relative to each other.
Innovation Solution
A combustor seal system that includes a seal positioned between the rear inner discharge nozzle and the nozzle guide vane, featuring a seal body that contacts multiple points along the nozzle guide vane and nozzle discharge nozzle, with expanded and contracted portions, slots, and tabs for additional support and positioning, designed to prevent airflow between the combustion chamber and secondary chamber, and includes a flap seal and attachment pin to limit wear and air leakage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple sealing pieces are used to seal the cavity between the rear inner discharge nozzle and nozzle guide vane, then the sealing coverage is improved, but the number of potential failure points and air leakage points increases
Solution Approach 1:
The patent combines multiple separate sealing pieces into a single integrated seal assembly that includes a first seal, second seal, and flap seal all connected together. This unified structure maintains comprehensive sealing coverage while reducing the number of separate components, thereby decreasing potential failure points and simplifying the overall system.
Solution Approach 2:
The seal assembly is segmented into multiple functional sections (first seal portion, second seal portion, flap seal) that can independently contact different surfaces. This segmentation allows each portion to address specific sealing needs while remaining part of a single integrated structure, balancing comprehensive sealing with reduced complexity.
2Adaptability or versatility
If the rear inner discharge nozzle and nozzle guide vane move relative to each other, then the operational flexibility is improved, but the wear due to rubbing increases
Solution Approach 1:
The patent employs a flexible seal assembly that can accommodate relative movement between the rear inner discharge nozzle and nozzle guide vane. The flap seal and connected seal portions can flex and adjust their positions as the components move relative to each other, maintaining sealing effectiveness while reducing friction and wear compared to rigid sealing arrangements.
Solution Approach 2:
The seal assembly is designed with dynamic characteristics, allowing it to adapt its configuration as the nozzle and guide vane move. The connected seal portions can shift and flex dynamically during operation, maintaining optimal contact with sealing surfaces while accommodating operational movements, thereby reducing wear from rigid rubbing.
3Device complexity
If a single robust seal configuration is used, then the number of potential failure points is reduced, but the ability to accommodate movement between components may be limited
Solution Approach 1:
The single integrated seal assembly is segmented into multiple functional portions (first seal, second seal, flap seal) connected together. This segmentation within unity allows each portion to independently accommodate movement in different directions and planes, maintaining flexibility while keeping the overall structure as a single component with fewer failure points.
Solution Approach 2:
The connected seal portions are designed with dynamic flexibility, allowing them to flex, bend, and adjust their relative positions as components move. This dynamic capability within a single integrated structure enables the seal to accommodate operational movements while maintaining sealing effectiveness, without requiring multiple separate rigid sealing pieces.
Data Source
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AI summary
A combustor seal system (200) for a gas turbine engine (100) is provided that includes a rear inner discharge nozzle (RIDN) (202) configured to engage a liner (212) of a combustor (108). The system (200) further includes a nozzle guide vane (NGV) (204) positioned adjacent the RIDN (202). The NGV (204) and the RIDN (202) together define a cavity (216). The system (200) further includes a seal (206) in contact with the RIDN (202) and positioned in the cavity (216). The seal (206) curves along a surface (217) of the cavity (216) and contacts the RIDN (202) at a first point (218) and a second point (220) in the cavity (216). The seal (206) contacts the NGV (204) at a third point (222).