Cancelling damping induced by drag in synthetic jets using performance enhancements

Patent metadata

Field	Value
Publication number	US-10500602-B2
Application number	US-201615222913-A
Country	US
Kind code	B2
Filing date	Jul 28, 2016
Priority date	Oct 16, 2013
Publication date	Dec 10, 2019
Grant date	Dec 10, 2019

Abstract

An active flow control drag-induced damping reduction apparatus. The apparatus includes a variable frequency signal power supply; a jet generator defining an internal cavity and having pump member, and coupled to the variable frequency signal power supply to receive a control signal; a feedback sensor coupled to the pump member to generate a feedback signal measuring the reciprocating motion of the pump member; a detection circuit that receives the feedback signal and measures a difference compared to the variable frequency generator; and an adjustment circuit that receives the measured difference and tunes the variable frequency signal of the variable frequency signal power supply to maintain the jet generator at an optimum flow.

First claim

What is claimed is:

1. A synthetic jet generator comprising:
a chamber defined by a housing, wherein an aperture is disposed in the housing, and wherein a fluid is disposed in the chamber;
a piston operably disposed to repeatedly compress the fluid in the chamber, wherein during compression strokes the piston forces a jet of the fluid to flow from the aperture;
a motor connected to the piston and configured to drive the piston;
a drive circuit in communication with the motor and configured to control operation of the piston by generating a drive signal communicated to the motor;
a sensor operably connected to one of the piston and the housing, and configured to take a measurement of a motion of the piston;
a feedback circuit connected to the sensor and to the drive circuit, and configured to incorporate a feedback signal into the drive signal, wherein the feedback signal includes the measurement of the motion of the piston at a resonance frequency of the chamber;
wherein the feedback circuit is further configured to add a component to the feedback signal, the component comprising a force calculated to cancel damping effects of a drag on the fluid flowing from the aperture;
wherein the feedback circuit includes a rate estimator and a gain, wherein the rate estimator is a first circuit that is configured to sum the motion of the piston into the feedback signal, and wherein the gain comprises a second circuit that is configured to increase an amplitude of the feedback signal; and
wherein the feedback circuit, in being configured to add a component to the feedback signal, is further configured to increase a first velocity of the jet relative to a second velocity of the jet that occurs when the chamber is at resonance without inclusion of the feedback signal.

2. The synthetic jet generator of claim 1 , wherein the increase is a factor of two or more due to an increase in an amplitude of a resonance frequency of the chamber.

3. The synthetic jet generator of claim 1 , wherein the sensor comprises an accelerometer in direct contact with the piston.

4. The synthetic jet generator of claim 1 , wherein the motor is a piezoceramic device or a voice coil device, and wherein the sensor is connected to the piezoceramic device or the voice coil device.

5. The synthetic jet generator of claim 4 , wherein the sensor comprises an induction coil coupled to the piston.

6. A method of improving operation of a synthetic jet generator, the method comprising:
cancelling a drag-induced damping of a jet of air exiting an aperture of a housing that defines a chamber in which a piston repeatedly compresses the air in the chamber at a resonance frequency of the chamber; and
increasing a gain of a feedback signal until a resonance frequency of the air in the chamber becomes unstable, whereby the air in the chamber resonates at a maximum amplitude for a given drive frequency of the piston without tracking the resonance frequency under changing drive frequency conditions.

7. The method of claim 6 , wherein cancelling comprises:
measuring a motion of the piston;
incorporating the motion of the piston into a feedback signal; and
using the feedback signal to modify operation of a motor that drives the piston.

8. The method of claim 7 , wherein cancelling further comprises:
incorporating a force that cancels the drag-induced damping into the feedback signal.

9. The method of claim 8 , wherein cancelling increases an amplitude of the resonance frequency, thereby increasing a velocity of the jet by at least a factor of two.

10. The method of claim 7 , wherein measuring a motion of the piston is accomplished using an accelerometer.

Assignees

• Boeing Co

Inventors

• Griffin Steven F

Classifications

• F04B37/00

  Pumps having pertinent characteristics not provided for in, or of interest apart from, groups F04B25/00 - F04B35/00 · CPC title

• B64C2230/06

  by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure · CPC title

• F04B35/04

  the means being electric · CPC title

• B64C2230/18

  by using small jets that make the fluid flow oscillate · CPC title

• B64C2230/04

  by actively generating fluid flow · CPC title