Radiused Combustor Liner Panel Edges
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Solution Overview
Problem
The durability of combustor liner panels in gas turbine engines is compromised due to features like cast in threaded studs and a full perimeter rail, leading to durability issues in high-temperature environments.
Innovation Solution
The combustor design incorporates a radiused edge on the liner panels with a thermal barrier coating, including a bond coat and a top coat, mounted via multiple studs to a support shell, which reduces the risk of coating chipping and enhances oxidation life.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If a full perimeter rail and cast in threaded studs are used to mount liner panels, then the mounting stability is improved, but the durability deteriorates due to coating chipping and stress concentration
Solution Approach 1:
The patent applies curvature by replacing sharp corners and edges with radiused edges (e.g., radius R0.03 to R0.06) on the liner panel. This curvature eliminates stress concentration points and prevents coating chipping at sharp edges, thereby improving durability while maintaining mounting stability through the preserved rail and stud features
2Ease of manufacture
If sharp edges and corners are present on liner panels, then the manufacturing simplicity is improved, but the coating quality deteriorates due to chipping at edges
Solution Approach 1:
The patent introduces radiused edges with specific radius dimensions (R0.03 to R0.06) on liner panels. This curvature modification prevents coating chipping at edges and corners while maintaining manufacturing feasibility through standard casting or machining processes, thus improving coating quality without significantly complicating manufacturing
3Strength
If traditional liner panel features are used, then the structural integrity is maintained, but the oxidation resistance deteriorates in high-temperature environments
Solution Approach 1:
The patent employs a thermal barrier coating system consisting of multiple layers (bond coat and top coat) applied to the liner panel. This composite coating structure provides enhanced oxidation resistance in high-temperature environments while the underlying panel structure maintains structural integrity through the preserved rail and stud mounting features
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 radiused edges and thermal barrier coating significantly reduce the likelihood of coating chipping and enhance the durability and oxidation life of the liner panels in high-temperature environments, addressing the durability issues of traditional designs.
Implementation Method 1
The hot side of the liner panel is exposed to a flow path of hot products of combustion
Implementation Method 2
Each of the liner panels includes a radiused edge along the perimeter of the hot side of the liner panel
Data Source
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AI summary
A liner panel (72, 74) for use in a combustor of a gas turbine engine (20), the liner panel (72, 74) includes a radiused edge (150, 152, 154, 156) blended into a hot side (112) of the liner panel (72, 74). A combustor for a gas turbine engine (20) including a liner panel (72, 74) mounted to a support shell (68, 70) via a multiple of studs (100), the liner panel (72, 74) including a radiused edge (150, 152, 154, 156) blended into a hot side (112) of the liner panel (72, 74), the hot side (112) including a thermal barrier coating. A method of manufacturing including casting a radiused edge (150, 152, 154, 156) blended into a hot side (112) of a liner panel; and applying a thermal barrier coating to the hot side (112) of the liner panel (72, 74).