Integrated Vane Air Seal Assembly for Turbine Cooling and Leakage Control
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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, particularly with the use of ceramic matrix composites (CMCs) for improved thermal resistance.
Innovation Solution
Integration of a vane with an integrated blade outer air seal, utilizing ceramic matrix composite materials, which includes cooling channels and passages to supply cooling air to both the vane and the air seal, reducing leakage and enhancing thermal management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional materials are used for turbine components, then manufacturing and cooling are simpler, but thermal resistance and temperature withstand capability are insufficient
Solution Approach 1:
The patent applies ceramic matrix composite (CMC) materials for the vane and air seal components. CMCs provide superior thermal resistance and temperature withstand capability compared to traditional metals, enabling operation in higher temperature environments while maintaining structural integrity. The composite structure allows integration of cooling channels directly into the material architecture.
Solution Approach 2:
The patent merges the vane and air seal into a single integrated CMC component. This integration eliminates the need for separate manufacturing and assembly of multiple parts, reducing overall manufacturing complexity despite using advanced materials. The unified structure allows optimized thermal and flow management across the entire component.
2Loss of energy
If separate vanes and air seals are used, then manufacturing and assembly are simpler, but leakage control and thermal management efficiency are reduced
Solution Approach 1:
The vane and air seal are merged into a single integrated component with unified cooling channels and sealing surfaces. This integration eliminates leakage paths that would exist between separate components, improving sealing efficiency and thermal management. The integrated design allows continuous cooling air flow from the vane through the air seal.
Solution Approach 2:
The integrated CMC component performs multiple functions simultaneously: it serves as both the vane (for flow direction) and the air seal (for leakage prevention), while also incorporating cooling channels for thermal management. This multi-functionality reduces the number of separate components needed and improves overall system efficiency.
3Temperature
If cooling channels are added to manage heat, then thermal management improves, but structural complexity and manufacturing difficulty increase
Solution Approach 1:
The CMC material structure inherently accommodates integrated cooling channels within its composite architecture. The material's layered or porous structure allows cooling passages to be formed during manufacturing without significantly increasing overall complexity. The cooling channels are embedded within the CMC vane and air seal structure.
Solution Approach 2:
The cooling channels are merged into the integrated vane-air seal component, allowing a single cooling air supply to serve both the vane and air seal sections. This unified cooling approach reduces the number of separate cooling systems needed and simplifies the overall thermal management architecture.
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 integrated design effectively cools and seals the turbine components, improving efficiency and reducing leakage, while maintaining structural integrity and thermal resistance using CMC materials.
Implementation Method 1
The outer platform has a cooling channel that extends into the airfoil to receive cooling air. There are cooling air passages within the outer platform and the blade outer air seal and connected into the cooling channel such that air can be communicated from the cooling channel into the blade outer air seal.
Implementation Method 2
At least a portion of the vane and the blade outer air seal are formed of ceramic matrix composite materials. 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.