Abstract: An aircraft turbomachine comprising a fan conduit with a wall, a flow of air passing through the turbomachine via the fan conduit. An air passage comprising an air opening is arranged in the wall, the air passage configured to receive a portion of the flow of the air through the fan conduit. A deflector is fixed to the wall upstream of the air opening, the deflector comprising at least one cross-section extending in the fan conduit to capture the flow of air. The at least one cross-section is porous. The deflector protects the air passage structure and is easy to produce and to fix to the wall of the fan conduit when it is screwed or riveted directly thereto. The deflector, as a result of its location in the fan conduit, is easy to access and thus allows rapid maintenance operations without having to disassemble the air passage.

Abstract: An aircraft turbomachine comprising a fan conduit with a wall, a flow of air passing through the turbomachine via the fan conduit. An air passage comprising an air opening is arranged in the wall, the air passage configured to receive a portion of the flow of the air through the fan conduit. A deflector is fixed to the wall upstream of the air opening, the deflector comprising at least one cross-section extending in the fan conduit to capture the flow of air. The at least one cross-section is porous. The deflector protects the air passage structure and is easy to produce and to fix to the wall of the fan conduit when it is screwed or riveted directly thereto. The deflector, as a result of its location in the fan conduit, is easy to access and thus allows rapid maintenance operations without having to disassemble the air passage.

Abstract: An aircraft nacelle comprising a power plant having a pipe with an aerodynamic surface, an air intake having an inside pipe with an aerodynamic surface, and an annular support of at least one measuring device having an aerodynamic surface, wherein the annular support is removably-inserted between the power plant and the air intake. In particular, the annular support is inserted downstream of the air intake and upstream of the power plant in a direction of flow of the stream of air, in such a way as to ensure continuity of the aerodynamic surfaces.

Abstract: An aircraft nacelle includes an air inlet (110) with a lip (114) extended to the back by a passage (116) to channel an air flow to a drive (112), the passage having at least one acoustic treatment panel (120) that includes, from the outside to the inside: an acoustically resistant porous layer (122); at least one cell-like structure (124), whose cells are sized for acoustic treatment; and a reflective or sealed layer (126). The reflective layer includes, near the end thereof that is oriented toward the lip, a surface (130) that is angled so as to be connected to the lip. A cell-like structure (136) is in contact with the angled surface, which forms an angle less than 30° with the tangent on the acoustically resistant layer. The cell-like structure is inserted between the angled surface of the reflective layer and an acoustically resistant porous layer.

Abstract: An aircraft nacelle includes an air inlet (110) with a lip (114) extended to the back by a passage (116) to channel an air flow to a drive (112), the passage having at least one acoustic treatment panel (120) that includes, from the outside to the inside: an acoustically resistant porous layer (122); at least one cell-like structure (124), whose cells are sized for acoustic treatment; and a reflective or sealed layer (126). The reflective layer includes, near the end thereof that is oriented toward the lip, a surface (130) that is angled so as to be connected to the lip. A cell-like structure (136) is in contact with the angled surface, which forms an angle less than 30° with the tangent on the acoustically resistant layer. The cell-like structure is inserted between the angled surface of the reflective layer and an acoustically resistant porous layer.

Abstract: An aircraft nacelle includes an air intake (40) that makes it possible to channel a stream of air (42) in the direction of a power plant (44), whereby the air intake (40) includes an inside pipe (48) that forms an aerodynamic surface (52) that is in contact with the stream of air (42) that is extended toward the rear by an aerodynamic surface (54) of a pipe (56) of the power plant, characterized in that it includes a support (66) of at least one measuring device (68), whereby the support (66), in annular form, is able to be inserted in a removable way between the air intake (40) and the power plant (44) and includes a so-called aerodynamic surface (70) that can ensure the continuity of the aerodynamic surfaces (52, 54) that are arranged downstream and upstream according to the direction of flow of the stream of air (42).