Method of processing acoustic waves emitted at the outlet of a turbo engine of an aircraft with a dielectric-barrier discharge device and aircraft comprising such a device

Patent metadata

Field	Value
Publication number	US-9361876-B2
Application number	US-201113643382-A
Country	US
Kind code	B2
Filing date	Apr 18, 2011
Priority date	Apr 27, 2010
Publication date	Jun 7, 2016
Grant date	Jun 7, 2016

Abstract

A method of processing acoustic waves emitted at an outlet of a turbo engine of an aircraft with a dielectric barrier discharge device, and an aircraft including such a device. The method includes activating the dielectric barrier discharge device so as to emit an electric wind in a direction of acoustic waves so as to attenuate the acoustic waves. An aircraft can include such a dielectric barrier discharge device.

First claim

The invention claimed is:

1. A method of processing acoustic waves emitted at an outlet of a turbo engine of an aircraft, the aircraft comprising a wing provided with a lower surface, the turbo engine being fastened to said lower surface by fastening means, the aircraft including a dielectric barrier discharge device, the method comprising:
providing the dielectric barrier discharge device at the lower surface proximate to where the turbo engine is fastened, facing the turboengine, higher than and downstream of an upstream portion of a support pylon which is fastened to the turbo engine, the support pylon connecting the turbo engine to the wing;
activating the dielectric barrier discharge device upon takeoff to emit an electric wind in a direction of the acoustic waves so to attenuate the acoustic waves; and
deactivating the dielectric barrier discharge device in a cruising rate of flight of the aircraft.

2. The method according to claim 1 , wherein the dielectric barrier discharge device is supplied by a current, and the dielectric barrier discharge device is controlled by at least one characteristic of the current so as to control at least one characteristic of the electric wind.

3. An aircraft comprising:
a turbo engine which emits acoustic waves at an outlet thereof;
a wing provided with a lower surface;
a support pylon which connects the turbo engine to said lower surface of the wing, an upstream portion of the support pylon being fastened to the turbo engine; and
a dielectric barrier discharge device provided at said lower surface proximate to where the turbo engine is connected, facing the turbo engine, so as to be disposed higher than and downstream of the upstream portion of the support pylon, the dielectric barrier discharge device configured to emit upon takeoff an electric wind in the direction of the acoustic waves so as to attenuate the acoustic waves and to be deactivated in a cruising rate of flight of the aircraft.

4. The aircraft according to claim 3 , wherein the dielectric barrier discharge device comprises a first high tension electrode and a second electrode connected to ground, which are separated by a dielectric medium.

5. The aircraft according to claim 3 , wherein the turbo engine comprises a primary ejection section and a secondary ejection section, and the dielectric barrier discharge device is axially positioned downstream from the secondary ejection section.

6. The aircraft according to claim 3 , wherein the dielectric barrier discharge device comprises a pressure sensor which measures a flow pressure at a surface of the dielectric barrier discharge device, and the dielectric barrier discharge device is configured to regulate at least one characteristic of the electric wind based on the measured flow pressure.

7. A method of processing acoustic waves emitted at an outlet of a turbo engine of an aircraft, the aircraft including a dielectric barrier discharge device, the method comprising:
providing a cavity in a lower surface of a wing of the aircraft, the turbo engine being fastened to the wing;
providing the dielectric barrier discharge device in the cavity at the lower surface of the wing of the aircraft proximate to where the turbo engine is fastened, facing the turbo engine, the dielectric barrier discharge device being disposed higher than and downstream of an upstream portion of a support pylon which is fastened to the turbo engine, the support pylon connecting the turbo engine to the wing; and
activating the dielectric barrier discharge device upon takeoff to emit an electric wind in a direction of the acoustic waves so to attenuate the acoustic waves,
wherein the dielectric barrier discharge device is provided in the cavity at the lower surface of the wing of the aircraft such that an external surface of the dielectric barrier discharge device is continuous with an external surface of the wing of the aircraft.

8. An aircraft comprising:
a turbo engine which emits acoustic waves at an outlet thereof;
a wing;
a support pylon which connects the turbo engine to the wing, an upstream portion of the support pylon being fastened to the turbo engine; and
a dielectric barrier discharge device provided at a lower surface of the wing proximate to the lower surface to where the turbo engine is fastened, facing the turbo engine, so as to be disposed higher than and downstream of the upstream portion of the support pylon, the dielectric barrier discharge device configured to emit upon takeoff an electric wind in the direction of the acoustic waves so as to attenuate the acoustic waves,
wherein the dielectric barrier discharge device is provided in a cavity provided at the lower surface of the wing of the aircraft such that an external surface of the dielectric barrier discharge device is continuous with an external surface of the wing of the aircraft.

Assignees

• Vuillemin Alexandre Alfred Gaston
• Snecma

Inventors

• Vuillemin Alexandre Alfred Gaston

Classifications

• B64C1/40 Primary

  Sound or heat insulation {, e.g. using insulation blankets} · CPC title

• B64C2230/14

  achieving noise reductions · CPC title

• G10K11/1788 Primary

  Physics · mapped topic

• B64C23/005

  by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds · CPC title

• B64D2033/0286

  for turbofan engines · CPC title