Blade tip vortex control
View Patent ↗The present disclosure presents systems, apparatuses, and methods of active flow controls for dissipating tip vortices. In this regard, a method comprises positioning one or more fan-shaped plasma actuators on an end surface of a tip of one or more airfoils of an aircraft, wherein the fan-shaped plasma actuators are surface compliant with the surface of the tip of the one or more airfoils; and activating the one or more fan-shaped plasma actuators during a flight of the aircraft, wherein at least one tip vortex generated by a flight of the aircraft is reduced by an introduction of one or more vortices generated by the one or more fan-shaped plasma actuators on the end surface of the tip of the one or more airfoils of the aircraft. Other systems, apparatuses, and methods are also presented.
1. A method of reducing tip vortices comprising:
positioning one or more fan-shaped plasma actuators on an end surface of a tip of one or more airfoils of an aircraft, wherein the one or more fan-shaped plasma actuators comprise dielectric barrier discharge actuators having two asymmetrically placed electrodes separated by a dielectric material which are configured to ionize ambient air into plasma, wherein an individual fan-shaped plasma actuator comprises a plurality of bent blade members that radially extend from a circular center of the individual fan-shaped plasma actuator;
activating the one or more fan-shaped plasma actuators during a flight of the aircraft, wherein at least one tip vortex generated by a flight of the aircraft is reduced by an introduction of one or more vortices generated by the one or more fan-shaped plasma actuators on the end surface of the tip of the one or more airfoils of the aircraft.
2. The method of claim 1 , further comprising positioning additional fan-shaped plasma actuators on a top surface of the one or more airfoils near the tip of the airfoil and activating the fan-shaped plasma actuators during the flight of the aircraft to reduce the at least one tip vortex generated by the flight of the aircraft.
3. The method of claim 1 , further comprising positioning serpentine plasma actuators on a top surface of the one or more airfoils near the tip of the airfoil and activating the serpentine plasma actuators during the flight of the aircraft to aid in the reduction of the at least one tip vortex generated by the flight of the aircraft.
4. The method of claim 1 , further comprising positioning plasma jet actuators on a top surface of the one or more airfoils near the tip of the airfoil and activating the plasma jet actuators during the flight of the aircraft to aid in the reduction of the at least one tip vortex generated by the flight of the aircraft.
5. The method of claim 1 , further comprising positioning additional fan-shaped plasma actuators on a bottom surface of the one or more airfoils near the tip of the airfoil and activating the fan-shaped plasma actuators during the flight of the aircraft to reduce the at least one tip vortex generated by the flight of the aircraft.
6. The method of claim 1 , further comprising positioning serpentine plasma actuators on a bottom surface of the one or more airfoils near the tip of the airfoil and activating the serpentine plasma actuators during the flight of the aircraft to aid in the reduction of the at least one tip vortex generated by the flight of the aircraft.
7. The method of claim 1 , further comprising positioning plasma jet actuators on a bottom surface of the one or more airfoils near the tip of the airfoil and activating the plasma jet actuators during the flight of the aircraft to aid in the reduction of the at least one tip vortex generated by the flight of the aircraft.
8. The method of claim 1 , wherein the one or more airfoils comprise at least one blade of a rotary-wing aircraft.
9. The method of claim 1 , wherein the one or more airfoils comprise at least one wing of a fixed-wing aircraft.
10. The method of claim 1 , wherein airfoil self-noise is reduced via activation of the one or more fan-shaped plasma actuators.
11. A system of reducing tip vortices comprising:
one or more airfoils of an aircraft;
one or more fan-shaped plasma actuators positioned on an end surface of a tip of the one or more airfoils of an aircraft, wherein the one or more fan-shaped plasma actuators comprise dielectric barrier discharge actuators having two asymmetrically placed electrodes separated by a dielectric material which are configured to ionize ambient air into plasma, wherein an individual fan-shaped plasma actuator comprises a plurality of bent blade members that radially extend from a circular center of the individual fan-shaped plasma actuator; and
a sinusoidal voltage source coupled to the one or more fan-shaped plasma actuators, wherein the sinusoidal voltage source is configured to activate the one or more fan-shaped plasma actuators during a flight of the aircraft in order to reduce at least one tip vortex generated by a flight of the aircraft by an introduction of one or more vortices generated by the one or more fan-shaped plasma actuators on the end surface of the tip of the one or more airfoils of the aircraft.
12. The system of claim 11 , wherein airfoil self-noise is reduced via activation of the one or more fan-shaped plasma actuators.
13. The system of claim 11 , further comprising additional fan-shaped plasma actuators positioned on a top surface of the one or more airfoils near the tip of the airfoil, wherein the sinusoidal voltage source is configured to activate the fan-shaped plasma actuators during the flight of the aircraft to reduce the at least one tip vortex generated by the flight of the aircraft.
14. The system of claim 11 , further comprising serpentine plasma actuators positioned on a top surface of the one or more airfoils near the tip of the airfoil, wherein the sinusoidal voltage source is configured to activate the serpentine plasma actuators during the flight of the aircraft to aid in the reduction of the at least one tip vortex generated by the flight of the aircraft.
15. The system of claim 11 , further comprising plasma jet actuators positioned on a top surface of the one or more airfoils near the tip of the airfoil, wherein the sinusoidal voltage source is configured to activate the plasma jet actuators during the flight of the aircraft to aid in the reduction of the at least one tip vortex generated by the flight of the aircraft.
16. The system of claim 11 , further comprising additional fan-shaped plasma actuators positioned on a bottom surface of the one or more airfoils near the tip of the airfoil, wherein the sinusoidal voltage source is configured to activate the fan-shaped plasma actuators during the flight of the aircraft to reduce the at least one tip vortex generated by the flight of the aircraft.
17. The system of claim 11 , further comprising serpentine plasma actuators positioned on a bottom surface of the one or more airfoils near the tip of the airfoil, wherein the sinusoidal voltage source is configured to activate the serpentine plasma actuators during the flight of the aircraft to aid in the reduction of the at least one tip vortex generated by the flight of the aircraft.
18. The system of claim 11 , further comprising plasma jet actuators positioned on a bottom surface of the one or more airfoils near the tip of the airfoil, wherein the sinusoidal voltage source is configured to activate the plasma jet actuators during the flight of the aircraft to aid in the reduction of the at least one tip vortex generated by the flight of the aircraft.