Patent ID: 9361876
Filing Date: 2016-06-07
CPC Classification: B64C,B64D

Claim Text:
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.