CMC Vane Outer Platform With Integrated Blade Air Seal for Turbine Cooling
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Solution Overview
Problem
Existing gas turbine engines face challenges in efficiently cooling and sealing components in the turbine section to manage high temperatures and combustion product flow for optimal efficiency.
Innovation Solution
Integration of a ceramic matrix composite (CMC) vane with an integrated blade outer air seal, featuring cooling channels and passages within the outer platform and seal, formed from CMC materials, to provide efficient cooling and sealing, reducing leakage and parts count.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional materials are used for turbine vanes and air seals, then manufacturing and cost are manageable, but temperature resistance and cooling efficiency are insufficient
Solution Approach 1:
The patent applies ceramic matrix composite (CMC) materials for the turbine vane and air seal components. CMCs provide superior high-temperature resistance compared to traditional metals, enabling operation in hotter environments while maintaining structural integrity. The composite structure allows integration of cooling channels directly within the material architecture, achieving both temperature resistance and efficient cooling despite increased manufacturing complexity.
2Loss of energy
If separate components are used for vanes and air seals, then manufacturing and assembly are simpler, but leakage control and sealing efficiency are insufficient
Solution Approach 1:
The patent merges the turbine vane and air seal into a single integrated CMC component. The air seal is formed as an integral extension of the vane structure, eliminating gaps and interfaces between separate parts. This integration dramatically reduces combustion product leakage while improving aerodynamic efficiency. The unified structure also reduces the total parts count and simplifies assembly, despite the increased complexity of manufacturing the integrated component.
3Temperature
If cooling channels are not integrated into the outer platform, then manufacturing is simpler, but cooling efficiency and heat management are insufficient
Solution Approach 1:
The patent nests cooling channels directly within the CMC vane structure, embedding the cooling system inside the component itself. The cooling passages are formed as integral cavities within the CMC material architecture, allowing cooling air to flow through the vane and air seal structures. This nested configuration provides superior heat management by directly cooling the high-temperature components from within, while the integrated approach leverages the manufacturing capabilities of CMC to reduce overall 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
Enhances cooling efficiency and reduces leakage, maintaining high-temperature durability and efficiency in the turbine section by utilizing CMC materials for the vane and blade outer air seal assembly.
Implementation Method 1
The outer platform has a cooling channel that extends into the airfoil to receive cooling air
Implementation Method 2
The CMCs can withstand higher temperatures than many other materials
Data Source
AI summary
A combined gas turbine engine vane and blade outer air seal assembly includes a vane having an airfoil extending from the leading edge to a trailing edge, and has an outer platform. The outer platform has a cooling channel that extends into the airfoil to receive cooling air. The outer platform extends to an integral blade outer air seal to be positioned radially outwardly of a turbine blade in a gas turbine engine. At least a portion of the vane and the blade outer air seal are formed of ceramic matrix composite materials. A gas turbine engine is also disclosed.