Gas Turbine Combustor Liner Non-Linear Interface
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Solution Overview
Problem
The combustor section of gas turbine engines faces challenges with high temperatures and thermally challenging environments, leading to durability and aerodynamics issues due to the segmented liner panels and their interfaces, which can result in steps, dead regions, and cooling inefficiencies.
Innovation Solution
The forward and aft non-linear interfaces of the combustor liner panels are skewed with respect to the engine axis or combustion gas flow direction, optimizing the design to minimize ingestion of combustion gases and improve durability and aerodynamics by eliminating steps and enhancing cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If liner panels are segmented to accommodate growth and manage thermal expansion, then manufacturing and assembly become easier, but interface regions create steps and dead regions that worsen aerodynamics and cooling efficiency
Solution Approach 1:
The patent applies curvature by transitioning from straight linear interfaces between liner panels to curved non-linear interfaces. This curved geometry eliminates the step changes and dead regions created by straight interfaces, thereby improving aerodynamic flow and cooling efficiency while maintaining the segmented panel structure for thermal expansion accommodation.
2Stability of the object's composition
If liner panels are segmented to accommodate growth, then thermal expansion is managed, but interface regions create dead regions that reduce cooling efficiency
Solution Approach 1:
The patent uses curved non-linear interfaces instead of straight lines to connect segmented liner panels. This curvature eliminates dead regions where cooling airflow could stagnate, ensuring continuous effective cooling across panel joints while still allowing the segmented structure to accommodate thermal growth.
Solution Approach 2:
The patent changes the geometric parameter of the interface from linear to non-linear/curved. This parameter change transforms the interface geometry to eliminate dead regions and improve cooling airflow patterns, thereby enhancing cooling efficiency while maintaining the segmented panel design for thermal management.
3Ease of manufacture
If straight linear interfaces are used between panels, then manufacturing is simpler, but the interfaces create steps that worsen flow path and aerodynamics
Solution Approach 1:
The patent transitions from straight linear interfaces to curved non-linear interfaces between liner panels. This curved geometry eliminates steps and discontinuities in the flow path, improving aerodynamic performance and flow continuity while maintaining manufacturability through standardized curved interface designs.
Data Source
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AI summary
A combustor for a gas turbine engine including a multiple of forward liner panels (72A, 72B) circumferentially mounted within the support shell via a multiple of studs (100), each of the multiple of forward liner panels (72A, 72B) having a non-linear axial edge (126Aa, 126Ab) therebetween to define a forward non-linear interface between each adjacent pair of the multiple of forward liner panels (72A, 72B) and a multiple of aft liner panels (74A, 74B) circumferentially mounted within the support shell via a multiple of studs (100) aft of the multiple of forward liner panels (72A, 72B), each of the multiple of aft liner panels (74A, 74B) having an aft non-linear axial edge (126Ba, 126Bb) therebetween to define a non-linear interface between each adjacent pair of the multiple of aft liner panels (74A, 74B).