Wave Geometry Combustor Liner Panel for High Heat Load Management
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Solution Overview
Problem
Gas turbine engine combustors face challenges in operating efficiently at high compressor exit temperatures, especially at high altitudes where reduced supply pressure leads to increased heat loads, requiring effective heat transfer solutions to manage convection and radiation heat loads.
Innovation Solution
A combustor panel with a wave pattern on the cold side, featuring convex and concave portions that form a wave pattern, with effusion passages angled through the panel, and impingement passages directed at peaks to enhance heat transfer via impingement and effusion cooling, increasing the heat transfer coefficient and cooling effectiveness.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If high compressor exit temperatures are used to improve engine efficiency, then power output increases, but heat loads (convection and radiation) increase
Solution Approach 1:
The combustor liner panel employs effusion cooling passages that allow cooling air to pass through porous-like structures and form a protective film on the hot side surface, directly addressing the high heat loads generated by high compressor exit temperatures while maintaining power output
2Loss of energy
If supply pressure is reduced at high altitude, then fuel consumption decreases, but heat transfer capability deteriorates
Solution Approach 1:
The wave pattern geometry with convex and concave portions creates curved surfaces that enhance flow turbulence and heat transfer coefficients, compensating for the reduced heat transfer capability caused by lower supply pressure at high altitude operation
3Temperature
If wave pattern geometry is added to enhance heat transfer, then cooling effectiveness increases, but manufacturing complexity increases
Solution Approach 1:
The wave pattern cooling structure integrates multiple functions into a single panel component: the convex and concave portions serve both as geometric features for enhancing heat transfer and as structural elements defining effusion cooling passages, reducing the need for separate cooling components and simplifying manufacturing
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 manages high heat loads by increasing the heat transfer coefficient and cooling effectiveness, ensuring efficient operation at high compressor exit temperatures and altitudes by enhancing convective heat transfer and film cooling.
Implementation Method 1
These operational conditions result in relatively high convection and radiation high heat loads
Implementation Method 2
increasing the heat transfer coefficient and cooling effectiveness
Implementation Method 3
The concave portion is in communication with a passage. The passage may be an effusion flow passage
Implementation Method 4
at least one of the multiple of impingement flow passages may be directed at one of the multiple of peaks
Data Source
AI summary
A panel for a combustor of a gas turbine engine includes a cold side defining at least one convex portion and at least one concave portion. The concave portion is in communication with a passage. A method of operating a combustor section of a gas turbine engine includes: directing an impingement flow toward a multiple of peaks on a cold side of a panel; directing the impingement flow from the multiple of peaks toward a multiple of troughs with a multiple of entrances on the cold side of the panel; and directing the impingement flow through the multiple of entrances and a respective multiple of effusion passages through the panel.