Spiral Radial Gaps Combustor Panel Film Cooling
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Solution Overview
Problem
Conventional gas turbine engine combustor cooling systems are inadequate for handling increasingly high temperatures, necessitating an improvement in cooling efficiency.
Innovation Solution
The design incorporates annular walls formed by circumferential arrays of swept-back combustor panels that overlap to create radial gaps in a spiral pattern, allowing air to enter the combustion chamber for film cooling, enhancing heat management and load-bearing capacity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional cooling systems with holes (impingement cooling holes, effusion cooling holes) are used, then the combustor wall can be cooled, but the cooling effectiveness is insufficient for increasingly high temperatures
Solution Approach 1:
The combustor wall is segmented into multiple panels arranged in a circumferential array, with each panel containing cooling gaps. This segmentation allows distributed cooling across the entire combustor surface, improving overall cooling effectiveness while maintaining structural integrity through the load-bearing panel configuration
Solution Approach 2:
Cooling gaps are strategically positioned at specific locations on the panels facing the combustion chamber, providing localized film cooling where heat flux is highest. The cooling air is delivered precisely where needed on the hot side of the combustor wall, optimizing cooling effectiveness at critical thermal zones
2Temperature
If telescoping rings with film cooling air entrances are used, then film cooling can be achieved, but the structure becomes more complex and weight increases
Solution Approach 1:
The panels serve multiple functions simultaneously: they provide structural support as load-bearing components, form the combustor wall geometry, and incorporate cooling gaps for film cooling. This multi-functionality eliminates the need for separate cooling components, reducing overall weight while maintaining both structural and thermal management capabilities
Solution Approach 2:
The cooling system is merged with the combustor wall structure itself, where the panels that form the combustor wall also contain the cooling gaps. This integration of cooling functionality into the primary structure eliminates additional weight from separate cooling components while maintaining effective film cooling
3Temperature
If panels are arranged in overlapping configuration to define radial gaps, then cooling air can enter the combustion chamber, but manufacturing precision requirements increase
Solution Approach 1:
The panels are designed with sweeping angles and overlapping configurations that allow for thermal expansion and manufacturing tolerances. The dynamic geometry of the swept-back panels creates self-aligning features that accommodate normal manufacturing variations while maintaining functional cooling gaps, reducing the stringency of precision requirements
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
This configuration effectively cools the hot side of the combustor walls, improves combustion recirculation, and reduces engine weight while maintaining structural integrity and manufacturing simplicity.
Implementation Method 1
allow air surrounding the at least one annular wall to enter the combustion chamber via the radial gaps for film cooling a hot side of the at least one annular wall
Data Source
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AI summary
A gas turbine engine includes a combustor which has at least one annular wall (40, 42) defining a combustion chamber (44) therein. The annular wall (40, 42) is formed by a circumferential array of panels (60) overlapping one with another to define a plurality of radial gaps (62) between respective adjacent two panels (60). The radial gaps (62) are configured in a spiral pattern and are in fluid communication with the combustion chamber (44) and a space outside the combustor to allow air surrounding the annular wall (40, 42) to enter the combustion chamber (44) via the radial gaps (62) for film cooling.