Patent ID: 8991749
Filing Date: 2015-03-31
Classification: B64C,B64D,Y02T

Abstract:
1. An aircraft pylon for supporting a turbojet engine that ejects a gas flow including a primary flow from a primary exit nozzle and a secondary flow from a secondary exit nozzle located radially outwardly with respect to the primary exit nozzle in a plane normal to a flow direction of the primary flow, thereby forming an inner shear layer at a boundary between the primary flow and the secondary flow, and an outer shear layer at a boundary between the secondary flow and a surrounding air flow that surrounds the secondary flow, the pylon comprising: an upper face for connection to the aircraft; a base including a portion for connection to the engine and a sole; and two lateral flanks connecting the upper face to the base, the pylon extending radially into the primary flow, the secondary flow, and the surrounding air flow, and extending longitudinally downstream of the primary exit nozzle, the sole including a part swept by the primary flow, and each of the two lateral flanks including