Dual-Walled Combustor Panel Cooling Airflow Control
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Solution Overview
Problem
Conventional gas turbine engine combustors face limitations in cooling air flow control due to pressure differentials across the combustor shell, leading to reduced cooling effectiveness and increased stress on components, necessitating an improved configuration for enhanced cooling and longevity.
Innovation Solution
A dual-walled combustor panel with internal cooling features and a lattice support structure that allows for controlled airflow and weight savings, incorporating features like trip strips, pedestals, and pin fins for enhanced cooling, and can be additively manufactured for increased durability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a conventional combustor shell is used, then the structure is simple and easy to manufacture, but the cooling air flow control is limited and pressure drop is high
Solution Approach 1:
The combustor shell is divided into multiple discrete panels with dual-walled structures, allowing independent cooling flow control for each panel. This segmentation enables precise cooling air flow management while maintaining overall structural integrity and reducing pressure drop across the entire combustor assembly.
Solution Approach 2:
The dual-walled panel structure incorporates nested cooling channels within the panel thickness, with internal cooling features embedded between the outer and inner walls. This nesting approach integrates cooling functionality directly into the structural panels without adding external complexity.
2Duration of action of stationary object
If cooling air flow is increased to improve cooling effectiveness, then component longevity improves, but pressure differential increases and cooling flow control becomes difficult
Solution Approach 1:
The cooling system incorporates adjustable flow control mechanisms that allow dynamic regulation of cooling air flow rates. This enables optimization of cooling effectiveness under varying operating conditions while maintaining manageable pressure differentials across the combustor panels.
Solution Approach 2:
Different panels and regions of the combustor can be equipped with customized cooling features and flow control settings tailored to local thermal conditions. This localized approach ensures adequate cooling where needed most while avoiding excessive pressure differentials in regions with lower thermal loads.
3Temperature
If conventional combustor panels are used, then manufacturing is straightforward, but weight is high and cooling efficiency is reduced
Solution Approach 1:
The panel structure incorporates porous or latticed wall sections that provide effective cooling surface area while reducing material quantity and weight. These porous structures allow cooling air passage while maintaining structural strength and enhancing heat dissipation efficiency.
Solution Approach 2:
The dual-walled panels utilize composite material constructions combining different material properties to achieve optimal strength-to-weight ratios. The composite structure enables thinner panel walls with adequate mechanical strength while improving cooling efficiency through enhanced thermal management.
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 provides improved cooling effectiveness and reduced pressure drop across the combustor, enhancing the durability and longevity of gas turbine engine components while minimizing weight and optimizing airflow distribution.
Implementation Method 1
one or more internal cooling features for controlling the cooling effectiveness between the first and second wall
Implementation Method 2
the combustor panel is configured to receive air flow and channel airflow into a combustion chamber
Implementation Method 3
there is also a desire to improve the configuration of gas turbine engines and combustors
Data Source
Figure 1
Figure 2A~2B
Figure 3A
AI summary
The present disclosure relates to combustor configurations, panels and components for a gas turbine engine. In one embodiment, a combustor (105; 300; 350) for a gas turbine engine (100) includes a support structure including a plurality of openings (210) and a plurality of panels (115) mounted to the structure. The plurality of panels define a combustion cavity (120) of the combustor. Each panel includes a first wall (311) configured to receive cooling air and a second wall (312) configured to provide air flow for the cavity. The first and second walls form a cavity (315) and include one or more elements for controlling the cooling effectiveness of each panel. Another embodiment is directed to a combustor panel including one or more elements for controlling cooling effectiveness. Another embodiment is directed to a support structure for a combustor of a gas turbine engine. Another embodiment is directed to configurations of panels including single walled portions or single walled panels.