An assembly for a gas turbine engine has: a fan case with a forward end, an aft end, and an inner surface extending from the forward end of the fan case to the aft end of the fan case; an acoustic liner having a forward end, an aft end, and an acoustic liner body that extends continuously from the forward end of the acoustic liner to the aft end of the acoustic liner; an inlet case located forward of the forward end of the fan case, the forward end of the acoustic liner being secured to the inlet case, and wherein the acoustic liner body is positioned against an inner surface of the inlet case and an inner surface of the fan case, and the aft end of the acoustic liner is secured to the fan case between the forward end and the aft end of the fan case.

An exhaust device and an installation method thereof, a turbine fracturing apparatus, and a disassembly method of a turbine are provided. The exhaust device includes a body, a fixation plate, a pressure plate, and a diffusion pipe; the body includes a side wall; the fixation plate is configured to be fixed to the side wall; the pressure plate is configured to be able to be pre-fixedly connected and fixedly connected with the fixation plate; the diffusion pipe is configured to be fixed to the side wall through the pressure plate and the fixation plate; the fixation plate further comprises a first pre-installation part, and the pressure plate further comprises a second pre-installation part, and the second pre-installation part is matched with the first pre-installation part to realize pre-fixation of the diffusion pipe.

A porous skin including strips and an acoustic attenuation panel. The porous skin (1) includes of strips (2) arranged transversely to a fluid flow (E) and which successively overlap each other laterally, each strip (2) upstream of said fluid flow (E) overlapping the downstream strip or strips (2), each of the strips (2) including at least one lateral edge comprising a contour defining a line with deviations, namely a broken line and/or a curved line, and the arrangement of the strips (2) and the contour or contours of their lateral edges being configured to form openings (11) between the strips (2) connecting an external face of the porous skin (1) to an internal face of said porous skin (1) and to prevent the fluid flow (E) from penetrating into said openings (11), the porous skin (1) thus being adapted to have sound waves pass through it while preventing the fluid flow (E) from passing through it.

Systems and methods for controlling an unducted turbofan engine to limit noise. The unducted turbofan engine may include an unducted fan drivingly coupled with a low-pressure turbine and a plurality of unducted outlet guide vanes. The unducted fan may include a plurality of fan blades and a pitch angle of the fan blades may be variable. A pitch angle of the unducted outlet guide vanes may be variable. A controller is configured to control the engine to limit noise based on a noise sensitive condition.

A forward part of an aircraft propulsion unit nacelle, comprising an air intake lip, an acoustic panel, and a rigid connection between the acoustic panel and the air intake lip. The acoustic panel has a resistive surface and a back skin, and the rigid connection is formed between the air intake lip and the back skin of the acoustic panel to form a propagation path for forces between the air intake lip and the back skin. This configuration gives freedom from design constraints, which enables an increase in the acoustic treatment region toward the front of the nacelle. An aircraft propulsion unit comprising a nacelle having such a forward part is also provided.

An acoustic panel for an aircraft nacelle air intake comprising a resistive skin perforated by noise absorption holes and a core against which the resistive skin extends, wherein the resistive skin has a smooth visible face and a castellated rear face with alternating ribs and grooves. The noise absorption holes are formed exclusively in the grooves, i.e., in a zone where the skin is less thick, which enables the holes to have a diameter that is both greater than the thickness of the skin and small enough not to have any impact on drag. The mechanical strength of the resistive skin provided by the ribs ensures that the lesser thickness of the resistive skin in the grooves does not render the resistive skin overly flexible.

An acoustic panel for an aircraft nacelle air intake comprising a resistive skin perforated by noise absorption holes and a core against which the resistive skin extends, wherein the resistive skin has a smooth visible face and a castellated rear face with alternating ribs and grooves. The noise absorption holes are formed exclusively in the grooves, i.e., in a zone where the skin is less thick, which enables the holes to have a diameter that is both greater than the thickness of the skin and small enough not to have any impact on drag. The mechanical strength of the resistive skin provided by the ribs ensures that the lesser thickness of the resistive skin in the grooves does not render the resistive skin overly flexible.

An optimized protection against ice on the inner and outer faces of an aircraft engine nacelle air intake with the air intake including an outer face and an inner face meeting at a line at the longitudinally extreme, called extremum line, an acoustic panel being installed on the inner surface of a part of the inner face. An elimination system based on vibration of the ice formed is put in place on at least a part of the outer face and an ice formation prevention system using a hot fluid is put in place on at least a part of the inner face and either an ice elimination system or an ice formation prevention system using a hot fluid is installed on the inner face and on the outer face, a marking line marking the boundary between the two systems.

A module ensuring an acoustic attenuation of a flow of a first fluid and a heat exchange between the first fluid and a second fluid. The module comprises a perforated first wall with a cutout, a second wall, a cellular structure extending from the second wall to the first wall, a recess provided in the cellular structure between a perforated bottom and a perforated top, and a heat exchanger which is fixed inside the recess between the bottom and the top and in which the second fluid circulates. Such a module ensures an attenuation of sound waves and a heat exchange without limiting the attenuation surface.

A module ensuring an acoustic attenuation of a flow of a first fluid and a heat exchange between the first fluid and a second fluid. The module comprises a perforated first wall with a cutout, a second wall, a cellular structure extending from the second wall to the first wall, a recess provided in the cellular structure between a perforated bottom and a perforated top, and a heat exchanger which is fixed inside the recess between the bottom and the top and in which the second fluid circulates. Such a module ensures an attenuation of sound waves and a heat exchange without limiting the attenuation surface.