Turbine Vane Ceramic Web Metallic Load Shield Cooling
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Solution Overview
Problem
Gas turbine engine vanes face challenges in withstanding high temperatures due to the interaction with combustion products, requiring high-temperature resistant materials and active cooling, which is complex in design and manufacture, especially with composite materials.
Innovation Solution
A turbine vane design incorporating a ceramic-containing web and a metallic load shield with integrated cooling channels and plenums, where the ceramic web forms the pressure side and the metallic load shield forms the suction side, with cooling air pathways through shield-cooling holes and plenums to manage heat and mechanical loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If high-temperature resistant materials and active cooling are used, then the vane can withstand high temperatures, but the design and manufacture becomes complex
Solution Approach 1:
The patent applies composite materials by combining a ceramic-containing web with a metallic load shield to create a hybrid structure. The ceramic web provides high-temperature resistance while the metallic shield provides mechanical strength and load-bearing capability. This composite approach allows the vane to withstand high temperatures without requiring complex active cooling systems, thereby resolving the contradiction between temperature resistance and design/manufacturing complexity.
2Temperature
If ceramic materials are used, then high-temperature resistance is improved, but load-carrying capability is limited
Solution Approach 1:
The patent directly addresses this limitation by creating a composite structure where the ceramic-containing web is combined with a metallic load shield. The metallic component specifically compensates for the low load-carrying capability of ceramic materials, while the ceramic portion maintains high-temperature resistance. The two materials work synergistically to overcome the individual weaknesses of each material.
Solution Approach 2:
The vane is segmented into distinct functional zones: the ceramic-containing web forms the pressure side for thermal resistance, while the metallic load shield forms the suction side for mechanical strength. This segmentation allows each material to be optimized for its specific function while working together as an integrated structure.
3Temperature
If cooling channels are added, then heat management is improved, but the structure becomes more complex
Solution Approach 1:
The patent merges the cooling channel functionality directly into the composite structure itself. The cooling channels are formed as integral parts of the interface between the ceramic web and metallic load shield, rather than being separate added components. This integration provides effective heat management while minimizing additional structural complexity.
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 design effectively reduces the amount of cooling air required, enhances durability, and mitigates load-carrying limitations of ceramic materials, making it suitable for high and moderate turbine operating temperature applications.
Implementation Method 1
A cooling channel may be formed between the ceramic-containing web and the metallic load shield. The cooling channel may extend from a mid-span region of the airfoil toward the trailing edge of the airfoil.
Implementation Method 2
The ceramic-containing web may be formed to include a plurality of shield-cooling holes. The shield-cooling holes may provide fluid communication between the first plenum and the cooling channel.
Implementation Method 3
The interaction of combustion products with the airfoils heats the airfoils to temperatures that require the airfoils to be made from high-temperature resistant materials and/or to be actively cooled
Data Source
AI summary
A turbine vane for use in a gas turbine engine is disclosed. The turbine vane includes an inner platform, an outer platform spaced from the inner platform, and an airfoil that extends from the inner platform to the outer platform. The airfoil includes a ceramic-containing web that forms a portion of the airfoil and a metallic load shield that forms another portion of the airfoil.