Gas Turbine Combustor Panel Effusion Cooling Design
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Solution Overview
Problem
Gas turbine combustors face durability issues due to local hot spots causing stress and cracking, which conventional cooling methods may exacerbate by affecting emissions and efficiency, especially in regions with space limitations.
Innovation Solution
A combustor panel arrangement with non-intersecting effusion holes and flow paths on adjacent panels, directed radially inward or outward, to enhance cooling efficiency and prevent cooling losses by maximizing contact area and minimizing intersection of flow paths.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If additional cooling air is used to combat hot spots, then hot spot-induced stress and cracking are reduced, but combustor emissions, pattern factor, and profile are negatively affected
Solution Approach 1:
The patent applies local quality by directing cooling air through effusion holes at specific locations (edges and surfaces of combustor panels) rather than using general cooling. The cooling is localized to hot spot regions while preserving overall combustor performance. The effusion holes are strategically positioned to provide cooling where needed without disrupting the global combustion flow patterns.
Solution Approach 2:
The patent replaces conventional mechanical cooling systems (such as cooling airflows that disrupt combustion) with an effusion-based cooling mechanism. The effusion holes allow controlled leakage of cooling air directly at the panel surfaces, providing a more precise and less intrusive cooling method that maintains combustion stability while protecting against hot spots.
2Use of energy by moving object
If cooling air is directed through effusion holes at panel edges, then cooling efficiency is improved and cooling losses are minimized, but the complexity of panel design increases
Solution Approach 1:
The patent segments the cooling function by dividing the panel into regions with different effusion hole configurations. Edges have effusion holes for cooling, while surfaces have different hole patterns. This segmentation allows optimized cooling at each location without requiring a completely complex redesign of the entire panel, as each segment can be independently designed and manufactured.
Solution Approach 2:
The patent employs porous-like structures through effusion holes distributed across the panel surfaces and edges. This porous approach allows cooling air to permeate through the panel material in a controlled manner, providing efficient cooling while maintaining structural integrity. The effusion hole pattern creates an effective porous cooling system that balances performance and manufacturability.
3Reliability
If effusion holes are positioned to maximize cooling contact area, then hot spot protection is enhanced, but manufacturing precision requirements increase
Solution Approach 1:
The patent applies asymmetry by positioning effusion holes differently at various locations on the panel. Edges have effusion holes oriented to maximize edge cooling, while surfaces have different hole patterns optimized for surface cooling. This asymmetric distribution maximizes cooling effectiveness at each location while allowing for standardized manufacturing processes that can accommodate the varied patterns without requiring extreme precision at every single hole location.
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 effectively reduces hot spot-induced stress and cracking, improves cooling efficiency, and maintains emissions and profile integrity by optimizing the distribution and direction of cooling air through the combustor panels.
Implementation Method 1
A first plurality of effusion holes extend through the first edge towards the second edge along a corresponding one of a first plurality of flow paths. A second plurality of effusion holes extend through the second edge along a corresponding one of a second plurality flow paths towards the first edge.
Implementation Method 2
The first plurality of flow paths and the second plurality of flow paths are non-intersecting, maximizing contact area and minimizing intersection of flow paths for enhanced cooling efficiency.
Data Source
AI summary
A combustor panel arrangement for a gas turbine engine. The combustor panel arrangement includes a first combustor panel that has a first edge. A second combustor panel has a second edge facing the first edge. A first plurality of effusion holes extend through the first edge towards the second edge along a corresponding one of a first plurality of flow paths. A second plurality of effusion holes extend through the second edge along a corresponding one of a second plurality flow paths towards the first edge. The first plurality of flow paths and the second plurality of flow paths are non-intersecting.