Gas Turbine Stator Tip Vortex Features for Clearance Management
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engines face inefficiencies due to clearance between cantilevered stator tips and rotating structures, which affects energy extraction and pressure distribution in the core airflow.
Innovation Solution
Incorporating vortex creation features such as serrations, teeth, or grooves on the tips of cantilevered stators to establish a tortuous flow path, generating flow vortices that force airflow to bypass the tip clearance and improve pressure distribution across the core flow path.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a clearance is maintained between the cantilevered stator tip and the rotating structure, then mechanical contact and wear are avoided, but gas turbine engine efficiency deteriorates due to adverse airflow effects
Solution Approach 1:
The patent converts the harmful effect of tip clearance airflow into a beneficial vortex flow pattern. By introducing vortex creation features (serrations, teeth, or grooves) on the stator tip, the airflow that would otherwise cause efficiency losses is transformed into controlled vortices that improve pressure distribution and reduce adverse effects, effectively turning the clearance problem into a performance enhancement opportunity
Solution Approach 2:
The patent modifies the geometric parameters of the stator tip by adding vortex creation features such as serrations, teeth, or grooves. These geometric changes alter the airflow characteristics within the tip clearance, creating beneficial vortex patterns that improve engine efficiency while maintaining the necessary mechanical clearance
2Loss of energy
If the tip clearance is minimized to improve engine efficiency, then energy extraction is optimized, but the risk of mechanical contact and component wear increases
Solution Approach 1:
The vortex creation features transform the potentially harmful close-clearance airflow into beneficial vortices that improve pressure distribution. This allows the system to operate with minimized clearance for optimal energy extraction while the vortex patterns prevent direct mechanical contact between the stator tip and rotating structure
Solution Approach 2:
The vortex flow patterns act as an intermediary mechanism between the stator tip and rotating structure. These vortices fill and manage the tip clearance space, allowing minimized clearance for efficiency while preventing direct mechanical contact through the mediating vortex flow field
3Productivity
If vortex creation features are added to the stator tip, then airflow optimization and engine efficiency are improved, but manufacturing complexity increases
Solution Approach 1:
The vortex creation features are implemented as segmented geometric elements (serrations, teeth, or grooves) on the stator tip. This segmentation approach allows the complex vortex generation function to be achieved through multiple simple, discrete geometric features rather than a single complex continuous shape, facilitating manufacturing
Solution Approach 2:
The patent achieves vortex creation through controlled changes in geometric parameters (such as serration depth, tooth height, or groove dimensions) rather than fundamentally complex designs. These parameter adjustments allow optimization of vortex patterns while maintaining manufacturability through standard machining or forming processes
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 vortex creation features enhance gas turbine engine efficiency by minimizing tip clearance and optimizing airflow, leading to improved energy extraction and reduced turbulence.
Implementation Method 1
at least one vortex creation feature formed on the static structure... generating flow vortices that force airflow to bypass the tip clearance
Data Source
AI summary
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a static structure that extends between a radially outer portion and a radially inner portion and at least one vortex creation feature formed on the static structure.