Composite Foam Cooling Passages for Turbomachine Airfoils
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing cooled gas turbine engine components face challenges in achieving optimal cooling efficiency and structural integrity, particularly in high-temperature applications, where current systems often compromise on weight and heat transfer effectiveness.
Innovation Solution
The use of composite foam cooling passages within airfoils and other components, formed from materials like ceramic matrix composites, which provide structural integrity and high surface area for heat transfer, allowing for efficient cooling without the need for removable core support pins, and incorporating controlled density variations to enhance pressure drops and heat exchange.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If traditional cooling passages are used in gas turbine components, then manufacturing is simpler, but cooling efficiency and heat transfer effectiveness are reduced
Solution Approach 1:
The patent employs foam structures with controlled porosity to create cooling passages. The foam material provides a three-dimensional network of interconnected pores that enable efficient coolant flow and heat transfer throughout the component volume, achieving superior cooling efficiency compared to traditional hollow passages while maintaining manufacturability through foam infiltration or expansion processes
Solution Approach 2:
The patent utilizes composite foam structures combining different materials (e.g., metal foams, ceramic foams, or polymer-fiber composites) to achieve optimal thermal and mechanical properties. These composite foam materials provide enhanced heat transfer characteristics and structural integrity simultaneously, resolving the contradiction between manufacturing ease and cooling efficiency
2Reliability
If cooling passages are added to improve cooling efficiency, then heat transfer effectiveness increases, but structural integrity may be compromised
Solution Approach 1:
The foam structure's cellular architecture provides both cooling passages and structural support. The three-dimensional pore network distributes thermal loads and mechanical stresses throughout the material, maintaining structural integrity while enabling efficient cooling. The cell walls and struts of the foam act as load-bearing elements that prevent catastrophic failure
Solution Approach 2:
The patent implements variable density foam structures where the pore size, cell structure, and material composition are locally optimized to match thermal and mechanical requirements at different locations. High-density regions provide structural support in high-stress areas, while low-density regions enhance cooling efficiency in high-heat-flux zones, achieving both goals simultaneously
3Reliability
If foam structures with controlled density variations are used, then heat transfer effectiveness is enhanced, but manufacturing complexity increases
Solution Approach 1:
The patent achieves controlled density variations by modifying foam formation parameters such as expansion ratio, cross-linking density, or material composition during the foaming process. These parameter changes create gradient structures or zoned density distributions that optimize heat transfer pathways without requiring complex post-processing or assembly operations, maintaining manufacturing simplicity
Solution Approach 2:
The desired density distribution and pore structure are built into the foam material during the initial foaming or infiltration process rather than requiring subsequent machining or assembly. The foam is formed in-situ or pre-formed with the exact density gradient needed, eliminating the need for complex manufacturing steps to create the thermal management structure
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 approach enhances the structural integrity and cooling efficiency of gas turbine engine components, enabling effective heat transfer and weight reduction, thus improving the overall performance and reliability of the engine.
Implementation Method 1
configured to pass a cooling fluid therethrough
Implementation Method 2
high surface area for heat transfer
Implementation Method 3
incorporating controlled density variations to enhance pressure drops and heat exchange
Data Source
AI summary
One embodiment of the present invention is a unique method of manufacturing a component for a turbomachine, such as an airfoil. Another embodiment is a unique airfoil. Yet another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooled gas turbine engine components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.


