Pull-Plane Effusion Combustor Panel Cooling
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Solution Overview
Problem
Gas turbine engine combustors face challenges in effectively managing heat protection due to the limitations of existing cooling systems, which struggle to maintain efficient thermal protection across the hot surfaces exposed to combustion gases.
Innovation Solution
A heat shield panel with a specific configuration of holes, each having a central axis defined by a common vector, is designed to provide a cooling air film across the hot side, utilizing a combination of casting and advanced drilling techniques such as electrical discharge machining, laser drilling, or water jet drilling to create a pattern of holes that extends from one axial or circumferential end to the other, ensuring comprehensive thermal protection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional cooling systems are used in combustor panels, then the structure is simple and manufacturing is easier, but thermal protection efficiency is insufficient
Solution Approach 1:
The patent applies effusion cooling through porous panel structures with multiple holes distributed across the hot surface. Cooling air is supplied through these holes to form a protective film that adheres to the hot surface, providing effective thermal protection. This porous approach allows comprehensive cooling coverage while maintaining a relatively simple overall structure.
Solution Approach 2:
The patent implements location-specific hole configurations where different groups of holes are positioned at different locations on the panel. Each group is oriented to supply cooling air to specific high-heat zones, creating locally optimized cooling patterns that match the thermal load distribution across the combustor panel.
2Temperature
If multiple groups of holes are positioned at different orientations and locations, then thermal protection coverage is improved, but manufacturing precision requirements increase
Solution Approach 1:
The cooling system is segmented into multiple groups of holes, with each group positioned and oriented to address specific thermal zones. This segmentation allows the complex cooling pattern to be manufactured in discrete sections, reducing the overall precision requirement compared to a single uniform hole pattern while still achieving comprehensive thermal protection.
Solution Approach 2:
The patent employs multiple groups of holes with orientations that may exceed the minimum required for basic cooling. This excessive action ensures complete coverage of all high-heat areas and provides redundancy, allowing for some variation in manufacturing while maintaining effective thermal protection across the entire panel surface.
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 heat shield panel effectively distributes cooling air to protect the hot surfaces from combustion gases, enhancing thermal management and reducing thermal stress on the combustor components.
Implementation Method 1
The cooling cavities fluidly couple impingement apertures defined in the shells with effusion apertures defined in the panels
Implementation Method 2
The heat shield panel effectively distributes cooling air to protect the hot surfaces from combustion gases, enhancing thermal management
Data Source
AI summary
A heat shield panel for a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface and a plurality of holes, each hole including a central axis having vector components defined by a common vector.