Gas Turbine Combustor Liner Curved Panel Interface
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Solution Overview
Problem
The combustor section of gas turbine engines faces challenges with high temperatures, leading to cooling issues and adverse local aerodynamics due to the segmentation of liner panels and their interfaces, which can result in durability problems and inefficiencies in flow path management.
Innovation Solution
The design incorporates a non-linear interface between forward and aft liner panels with contoured edges and dilution passages to enhance cooling and reduce steps and dead regions, improving durability and aerodynamics by optimizing the combustor geometry and using a combination of impingement and effusion cooling passages.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If liner panels are segmented to accommodate thermal growth and operational considerations, then ease of manufacture and installation are improved, but steps and dead regions form at panel interfaces causing adverse local aerodynamics and cooling challenges
Solution Approach 1:
The patent applies curvature by transitioning from traditional straight panel edges to contoured, curved edges at panel interfaces. The forward panel has a curved aft edge and the aft panel has a curved forward edge that complement each other, eliminating sharp corners and steps. This curved geometry allows for smoother airflow transition while maintaining the segmented panel structure for ease of manufacture and thermal growth accommodation.
2Ease of manufacture
If traditional straight-edged panel interfaces are used, then manufacturing simplicity is maintained, but steps and dead regions create cooling challenges and durability problems
Solution Approach 1:
The curved panel edges eliminate sharp corners and steps that create dead regions prone to cooling challenges and durability issues. The complementary curved surfaces of adjacent panels provide continuous, smooth transitions that prevent flow separation and ensure uniform cooling airflow distribution across panel interfaces, thereby improving reliability without significantly complicating manufacturing.
Solution Approach 2:
The patent applies different geometric qualities to different regions: the bulk of each panel maintains a relatively simple quadrilateral shape for ease of manufacture, while the interface regions feature contoured curved edges specifically designed to eliminate steps and improve aerodynamics. This localized application of complexity only where needed preserves manufacturing simplicity while enhancing durability.
3Ease of manufacture
If linear panel edges are used, then panel geometry is simple and manufacturing is easier, but cooling efficiency is reduced due to dead regions and steps at interfaces
Solution Approach 1:
The curved panel edges eliminate dead regions where hot gas could stagnate and create localized heating that would reduce cooling efficiency. The smooth curved transitions ensure continuous airflow paths for cooling air across panel interfaces, preventing flow separation and ensuring uniform cooling distribution. This improves cooling efficiency while maintaining relative geometric simplicity through the use of contoured surfaces rather than complex multi-faceted shapes.
Data Source
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AI summary
A combustor for a gas turbine engine including a forward liner panel (72A,72B) mounted to a support shell via a multiple of studs (100), the forward liner panel (72A,72B) including an aft non-linear circumferential edge (124a) and an aft liner panel (74A, 74B) mounted to the support shell via a multiple of studs (100), the aft liner panel (74A,74B) including a forward non-linear circumferential edge (122b) that is complementary to the aft non-linear circumferential edge (124a).