Abstract: An exhaust cone for an aircraft turbomachine, extending along a longitudinal axis and having a radially internal annular wall and a radially external skin delimiting a primary flow path for hot gases and surrounding the internal annular wall, and partitions mounted radially between the external skin and the internal annular wall and intersecting them in a manner that together with the skin and wall delimits acoustic chambers. The exhaust cone can further include at least one seal arranged between a radial end of one of the partitions and at least one among the internal annular wall and the external skin.

Abstract: The invention relates to an acoustic attenuation structure comprising a lower multicellular structure and an upper multicellular structure, at least part of the cells of the upper multicellular structure opening out at least partially into one or several cells of the lower multicellular structure, the acoustic attenuation structure being characterized in that a hollow acoustic element having a shape gradually tapering between a base and a top is present in each cell of at least part of the lower multicellular structure.

Abstract: A sound attenuation panel for an aircraft turbomachine includes first and second skins and a core comprising. The core has at least one polygonal cell provided with an internal cavity in communication with at least one hole formed in the first wall. The cavity has a first height (H1) between the first and second skins. Each cavity includes at least one internal partition that extends substantially from the first skin perpendicular to the first and second skins over a second height (H2) that is less than the first height (H1) and transversely between two side walls of the cell. The internal partition divides the cavity into at least two adjacent pockets in communication with one another and with the hole.

Abstract: An assembly for an exhaust cone of an aircraft turbomachine, including a first annular wall, and first partitions and second partitions defining between them a plurality of acoustic boxes distributed around the first wall, an assembly formed by the first and the second partitions being fastened to the first wall with first fastening members arranged upstream and with second fastening members arranged downstream, the first fastening members being offset circumferentially with respect to the second fastening members.

Abstract: A method for manufacturing an acoustic panel including a first skin, a second skin and an intermediate structure enclosed between these skins and forming oblique cavities with respect to the latter. The method includes an intermediate polymerization step for fastening the intermediate structure to the first skin in order to increase the compressive strength thereof and in particular to support an automated operation of draping the second skin.

Abstract: A method for forming an acoustic resonator panel for an aircraft propulsion assembly nacelle, the acoustic panel including cells with transverse internal obstacles in order to lengthen the path traveled by the sound waves. The method includes forming a perforated metal sheet, stacking a plurality of thermoplastic cellular cores and at least one perforated sheet, two successive cellular cores being separated by a perforated sheet, compacting the stack, and thermoplastic welding.

Abstract: An assembly for an ejection cone of an aircraft turbomachine, including a first annular wall and a plurality of first partitions and of second partitions extending substantially perpendicularly from the first wall, the first partitions additionally extending wholly in the axial direction and the second partitions extending wholly in a circumferential direction between the adjacent pairs of first partitions and being curved partitions including at least one arcuate portion in the axial direction upstream or downstream, the first wall, the first partitions and the second partitions additionally defining between them a plurality of acoustic boxes distributed around the first wall.

Abstract: An exhaust cone for an aircraft turbomachine, extending along a longitudinal axis and having a radially internal annular wall and a radially external skin delimiting a primary flow path for hot gases and surrounding the internal annular wall, and partitions mounted radially between the external skin and the internal annular wall and intersecting them in a manner that together with the skin and wall delimits acoustic chambers. The exhaust cone can further include at least one seal arranged between a radial end of one of the partitions and at least one among the internal annular wall and the external skin.

Abstract: A method for manufacturing a sound attenuating panel uses an alveolar-core structure including a first edge and a second edge separated by alveolar cells, the alveolar cells including walls extending from the first and second edges and defining a primary conduit for the circulation of a sound wave that is to be attenuated. The method includes covering the first edge or the second edge of the alveolar-core structure with a compartmentation wall; deforming the compartmentation wall to define at least one secondary conduit for the circulation of a sound wave that is to be attenuated, the secondary conduit extending at least partially within said primary conduit; and creating an opening in the compartmentation wall to permit communication between the primary and secondary conduits.

Abstract: An acoustic panel comprising a first group of cavities oriented towards a front end of the panel and a second group of cavities oriented towards a rear end of the panel.

Abstract: An acoustic attenuation panel includes a cellular structure including a plurality of acoustic cells separated from one another by peripheral partitions, a perforated acoustic structure, the perforated acoustic structure and the cellular structure being formed in one piece in a first material, and a porous acoustic layer formed of a second material and fastened to a surface of the perforated acoustic structure by entangling the first material and the second material.

Abstract: An assembly for an exhaust cone of an aircraft turbomachine, including a first annular wall, and first partitions and second partitions defining between them a plurality of acoustic boxes distributed around the first wall, an assembly formed by the first and the second partitions being fastened to the first wall with first fastening members arranged upstream and with second fastening members arranged downstream, the first fastening members being offset circumferentially with respect to the second fastening members.

Abstract: An assembly for an ejection cone of an aircraft turbomachine, including a first annular wall and a plurality of first partitions and of second partitions extending substantially perpendicularly from the first wall, the first partitions additionally extending wholly in the axial direction and the second partitions extending wholly in a circumferential direction between the adjacent pairs of first partitions and being curved partitions including at least one arcuate portion in the axial direction upstream or downstream, the first wall, the first partitions and the second partitions additionally defining between them a plurality of acoustic boxes distributed around the first wall.

Abstract: A machining device for producing at least one orifice in a workpiece made of composite material, the machining device including a tool holder and at least one drill bit mounted on the tool holder, the drill bit being configured to be driven in rotation about an axis of rotation. The machining device includes a cylindrical guide body coaxial with the axis of rotation, mounted on the tool holder, and surrounding the drill bit, the guide body being configured to bear on the workpiece during the production of the orifice and the drill bit projecting from the guide body.

Abstract: An acoustic panel for a turbine engine includes a first strip and a second strip each comprising an alternation of first ridges and second ridges connected by sidewalls. The first and second strips are joined to each other to form a plurality of cells, each delimited by a first ridge of the first strip and a first ridge of the second strip. A third strip is interposed between the first strip and the second strip and includes a first lateral wall bearing on the first strip The third strip further includes at least one tab that extends inside one of the cells and delimits all or part of a passage inside the associated cell.

Abstract: An acoustic attenuation panel includes a perforated acoustic wall, a first honeycomb structure coupled to the perforated acoustic wall and including a plurality of acoustic cells defined by peripheral partitions, a second honeycomb structure including a plurality of acoustic cells defined by peripheral partitions, and a septum which includes a plurality of macro-perforations and is positioned between the first honeycomb structure and the second honeycomb structure. Each acoustic cell of the first honeycomb structure and each acoustic cell of the at least second honeycomb structure are arranged opposite a single perforation of the septum.

Abstract: A method for manufacturing an acoustic panel including a first skin, a second skin and an intermediate structure enclosed between these skins and forming oblique cavities with respect to the latter. The method includes an intermediate polymerization step for fastening the intermediate structure to the first skin in order to increase the compressive strength thereof and in particular to support an automated operation of draping the second skin.

Abstract: An acoustic assembly including a multicellular acoustic panel having at least one through cavity along a direction X, wherein the acoustic assembly further includes at least one sealing element including a body enclosing one or more acoustic cells, the body being able to be inserted into the cavity and extending along the direction X between a first face and a second face, the sealing element further including a seal on the second face of the body able to ensure the sealing with the acoustic panel.

Abstract: An acoustic panel for an aircraft turbomachine has a sandwich structure. The sandwich structure includes a cell structure with a plurality of acoustic cells, a perforated acoustic structure, and a porous acoustic structure attached to the perforated acoustic structure. The perforated acoustic structure is arranged between the cell structure and the porous acoustic structure. The porous acoustic structure is multi-layered and has a first woven textile layer and a second woven textile layer connected to the first layer. The second layer is arranged between the first layer and the perforated acoustic structure.

Abstract: An air intake for a nacelle for an aircraft engine includes a front lip connecting a substantially cylindrical internal wall and a substantially cylindrical external wall, and at least one acoustic structure including acoustic cells. The acoustic structure is situated in the space delimited by the internal wall, the external wall and the front lip. The acoustic structure is an added part secured to the air intake. The acoustic cells of the acoustic structure are arranged facing a region of the internal wall or of the lip at a predetermined distance so that the acoustic cells of the acoustic structure are not in contact with the internal wall or the lip while providing an acoustic attenuation function.