Gas Turbine Variable Geometry Vane Segments
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Solution Overview
Problem
Existing gas turbine engine flow components with variable geometry face limitations in efficiently altering flow path characteristics and cooling fluid management, necessitating advancements in design and operation.
Innovation Solution
A gas turbine engine component featuring movable airfoil extensions that change positions between fixed airfoil members, altering flow path characteristics and cooling fluid exposure, along with a ring system that adjusts circumferential orientation to interact with airflow members, thereby modifying incidence angle, exit swirl, and camber, while managing cooling fluid flow through strategically positioned apertures and passages.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a movable airfoil extension is introduced to alter flow path characteristics, then operational flexibility and efficiency are improved, but device complexity increases
Solution Approach 1:
The airfoil extension is designed to be movable rather than fixed, allowing it to change position between different operating positions. This dynamic capability enables the component to adapt flow path characteristics according to operational requirements, resolving the contradiction between operational flexibility and device complexity by making the extension movable between defined positions.
Solution Approach 2:
The airfoil extension is divided into multiple segments or sections that can move independently or collectively. This segmentation allows for controlled movement and adjustment of flow path characteristics while maintaining structural integrity, thereby achieving operational flexibility without excessive device complexity.
2Temperature
If cooling apertures are exposed in the first operating position, then cooling efficiency is improved, but thermal stress management becomes more complex
Solution Approach 1:
The cooling apertures are designed to be selectively exposed or covered based on the operating position of the airfoil extension. In the first operating position, the apertures are exposed to maximize cooling efficiency, while in the second operating position, they are covered. This dynamic exposure control allows the system to optimize cooling only when needed, reducing unnecessary thermal management complexity.
3Adaptability or versatility
If the movable airfoil extension moves between operating positions, then flow path characteristics are altered, but mechanical wear and reliability concerns increase
Solution Approach 1:
The airfoil extension moves between discrete operating positions rather than continuous positions, reducing the complexity of motion control and minimizing wear on moving components. The defined first and second operating positions provide stable, repeatable configurations that reduce mechanical stress and wear compared to continuous adjustment mechanisms.
4Adaptability or versatility
If the ring is positioned in different circumferential orientations, then collective orientation of airflow members is modified, but positioning precision requirements increase
Solution Approach 1:
The ring is divided into multiple segments or sections, each capable of independent or collective movement to different circumferential orientations. This segmentation allows for adjusted positioning requirements compared to a monolithic ring, as each segment can be positioned independently or in groups, reducing the overall precision requirements while maintaining adaptability.
Data Source
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AI summary
A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments (64,66) which are coupled to a rotatable ring, or rings (68,70), are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments (64,66) can be rotated through the ring, or rings (68,70), between a first position associated with the first vane (60) and a second position associated with a second vane (62) to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments (64,66) can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.