Patent ID: 8757319
Filing Date: 2014-06-24
Classification: B64D,F02C,F02K,F05D,Y02T

Abstract:
1. A turbojet engine nacelle including at least one nacelle element having a wall delimiting a main flow channel, said channel having a variable flow passage section with at least one first area of the channel, the passage section of which is greater than that of at least one second area of the channel, wherein the wall of the nacelle element is at least partly covered by an acoustic damping panel extending in the first and the second area of the channel, said panel including: a structuring skin attached against said wall of the nacelle element; a perforated skin at least partly delimiting the channel; and a core inserted between the structuring skin and the perforated skin, said core being made in an acoustic absorption material of the type having many internal cavities, wherein said nacelle further including at least one secondary flow conduit establishing a fluidic connection between the first area and the second area of the channel in parallel on said channel, wherein said or each conduit has a first end crossing the structuring skin in the first area of the channel on the one hand and a second end crossing the structuring skin in the second area of the channel on the other hand, in order to establish the secondary flow in the conduit via the core and the perforated skin of the acoustic damping panel.