Counter-flow Point Embedded Electrode Plasma Actuator for Dynamic Stall Control
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Solution Overview
Problem
Existing plasma actuators with large embedded electrodes face challenges in creating effective forcing around high curvature surfaces, limiting their ability to prevent dynamic stall in airfoils during rapid pitching motions.
Innovation Solution
The development of counter-flow point embedded electrode plasma actuators, which include linear or spatially varying embedded electrodes and an exposed electrode, apply alternating current signals to generate three-dimensional forcing over curved surfaces, effectively preventing dynamic stall by orienting the forcing direction appropriately.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If large embedded electrodes are used in plasma actuators, then the voltage differential and plasma generation capability are improved, but the ability to create effective forcing around high curvature surfaces deteriorates
Solution Approach 1:
The patent divides the embedded electrode into multiple segments or uses a point electrode configuration instead of a large continuous electrode. This segmentation allows the plasma actuator to adapt to high curvature surfaces by placing multiple small electrodes at strategic locations, maintaining effective forcing capability while preserving voltage differential through proper electrode spacing and configuration.
Solution Approach 2:
The patent transitions from a two-dimensional planar electrode configuration to a three-dimensional spatial arrangement of point electrodes on the airfoil surface. By positioning electrodes in three-dimensional space and using counter-flow configurations, the system achieves effective plasma forcing on highly curved surfaces while maintaining the necessary voltage differential for plasma generation.
2Reliability
If plasma actuators are used to delay dynamic stall, then the dynamic stall angle is increased, but the device complexity increases due to multiple electrodes and control systems
Solution Approach 1:
The patent combines multiple electrode functions into a unified counter-flow point electrode configuration. By integrating the embedded point electrode with the exposed electrode in a counter-flow arrangement, the system achieves effective dynamic stall control while reducing the number of separate components and simplifying the overall device architecture compared to traditional multi-electrode plasma actuators.
Solution Approach 2:
The patent employs a dielectric barrier discharge mechanism where the dielectric material itself plays an active role in the plasma generation process. The dielectric layer on the airfoil surface serves as both a structural component and an functional element that enables plasma discharge, reducing the need for additional complex electrode structures and control mechanisms.
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 counter-flow point embedded electrode plasma actuators successfully increase dynamic stall angles and prevent flow reversal, enhancing the performance of airfoils by maintaining stable flow over high curvature regions.
Implementation Method 1
The use of plasma actuators for delay of dynamic stall is not new, but recent success using high frequency plasma actuators has revived interest. Plasma actuators function by having large voltage differential across two electrodes.
Implementation Method 2
Plasma actuators function by having large voltage differential across two electrodes
Data Source
AI summary
The present disclosure presents systems and methods for dynamic stall control in aircrafts. One such method involves positioning one or more counter-flow point embedded electrode plasma actuator devices on an edge of an airfoil of an aircraft, wherein a counter-flow point embedded electrode plasma actuator device comprises at least a first electrode that is unexposed and embedded under a surface of the airfoil and a second electrode positioned on or in a top surface of the airfoil; and/or activating the one or more counter-flow point embedded electrode plasma actuator devices during a flight of the aircraft, wherein a dynamic stall angle of a pitching airfoil is increased during the flight of the aircraft by forcing plasma over the edge of the pitching airfoil.