A panel for a nacelle of an aircraft propulsion assembly includes two skins and a cell structure provided with transverse partitions defining cells. The cell structure includes folds with at least one central part forming at least one part of at least one transverse partition and at least one peripheral part extending along at least one of the skins. A nacelle with such a panel is provided, as well as a method for manufacturing such a panel.

A panel for a nacelle of an aircraft propulsion assembly includes two skins and a cell structure provided with transverse partitions defining cells. The cell structure includes folds with at least one central part forming at least one part of at least one transverse partition and at least one peripheral part extending along at least one of the skins. A nacelle with such a panel is provided, as well as a method for manufacturing such a panel.

A heat shield for a gas turbine engine includes a radial heat shield flange that extends in a circumferential direction and forms a ring. A plurality of bosses extend from a first axial side of the radial heat shield flange. There is a plurality of guide pins. One of the plurality of guide pins extends from a corresponding one of the plurality of bosses.

A heat shield for a gas turbine engine includes a radial heat shield flange that extends in a circumferential direction and forms a ring. A plurality of bosses extend from a first axial side of the radial heat shield flange. There is a plurality of guide pins. One of the plurality of guide pins extends from a corresponding one of the plurality of bosses.

A method for manufacturing a fibrous tubular structure including lobes, in which fibers are draped/deposited on a mandrel having a shape corresponding to that of the fibrous structure, includes draping/deposition carried out such that at least one group of fibers has a same orientation with respect to the axis (A) of said fibrous structure, then, the fibers having been draped over an angular sector less than the total periphery of the mandrel, one of the ends of the fibrous structure is separated from the mandrel in order to allow the continuation of the draping on the same mandrel.

A thrust reverser arrangement may comprise an inner fixed structure (IFS), a track beam, a translating sleeve slideably mounted to the track beam, a bypass duct defined between the IFS and the translating sleeve, and an acoustic treated fairing coupled to the translating sleeve, wherein the acoustic treated fairing is configured to attenuate noise generated during operation of a gas turbine engine.

A thrust reverser arrangement may comprise an inner fixed structure (IFS), a track beam, a translating sleeve slideably mounted to the track beam, a bypass duct defined between the IFS and the translating sleeve, and an acoustic treated fairing coupled to the translating sleeve, wherein the acoustic treated fairing is configured to attenuate noise generated during operation of a gas turbine engine.

An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a perforated sheet that includes a set of perforations with corresponding inlets, the perforated sheet supported by the support layer such that perforations are in overlying relationship with the open faces to form paired perforations and cavities that define acoustic resonator cells, and a coating applied to the perforated sheet.

A thrust reverser system for jet aircraft comprising an exhaust tailpipe mounted to the turbine engine aft turbine flange and two clamshell doors, actuators and a locking system to prevent inadvertent deployment of the clamshell doors in-flight. Two improved design clamshell doors configurations, either one or a combination of both, mounted on either side of the top and bottom of the exhaust tailpipe, fitted with two patented design actuators mounted one on each side of the external sides of the tailpipe between the clamshell doors and the tailpipe, possibly in a depression in the tailpipe called blister, assuming them to be hydraulic actuators for discussion purposes. The actuators drive the clamshell doors using improved floating linkages loosely pivoted to the exterior of the exhaust tailpipe. The actuators are connected to the doors through mechanical linkages, to deploy the doors aft of the tailpipe exhaust area during deceleration after landing, diverting the exhaust gases forward to slow down the aircraft, and the actuators also drive two movable fairings during thrust reverser operation to enclose the reversed exhaust flow forward to prevent its impingement on the skin of the aircraft and provide a ram inlet area with the sides of the clamshell doors allowing ram air from the surrounding free stream to be scooped through the gap between the movable fairing and clamshell doors thereby provide cooling of the door surface in contact with the exhaust gases and mix with the engine exhaust gases in reverse thrust mode thereby augmenting reverse thrust mass flow and energy. The exhaust tailpipe can have a circular or any geometric exhaust section or in other configuration can be fitted in with a flow mixer with the surrounding ambient air to reduce shear noise resulting from the high velocity exhaust gases for noise attenuation. The flow mixer can also be perforated to allow for suction of ambient air by the lower static pressure engine exhaust gases to reduce shear noise and increase mixing and thrust. Two fixed fairings, above and below the tailpipe at the exit section can have perforations and also perforations on the movable fairings to educt surrounding air also to reduce shear noise between surrounding air and the engine exhaust flow during forward thrust based on SAE Aerospace Information Report AIR-1191 and method of calculation. Other configurations for the trailing edges of the fixed and movable fairings can have wavy contour lines to increase the contact area between the engine exhaust gases and the surrounding air to reduce shear noise as well. Fixed circular shape or rolling bodies, depicted as wheels for discussion purpose, but they can be o

A thrust reverser system for jet aircraft comprising an exhaust tailpipe mounted to the turbine engine aft turbine flange and two clamshell doors, actuators and a locking system to prevent inadvertent deployment of the clamshell doors in-flight. Two improved design clamshell doors configurations, either one or a combination of both, mounted on either side of the top and bottom of the exhaust tailpipe, fitted with two patented design actuators mounted one on each side of the external sides of the tailpipe between the clamshell doors and the tailpipe, possibly in a depression in the tailpipe called blister, assuming them to be hydraulic actuators for discussion purposes. The actuators drive the clamshell doors using improved floating linkages loosely pivoted to the exterior of the exhaust tailpipe. The actuators are connected to the doors through mechanical linkages, to deploy the doors aft of the tailpipe exhaust area during deceleration after landing, diverting the exhaust gases forward to slow down the aircraft, and the actuators also drive two movable fairings during thrust reverser operation to enclose the reversed exhaust flow forward to prevent its impingement on the skin of the aircraft and provide a ram inlet area with the sides of the clamshell doors allowing ram air from the surrounding free stream to be scooped through the gap between the movable fairing and clamshell doors thereby provide cooling of the door surface in contact with the exhaust gases and mix with the engine exhaust gases in reverse thrust mode thereby augmenting reverse thrust mass flow and energy. The exhaust tailpipe can have a circular or any geometric exhaust section or in other configuration can be fitted in with a flow mixer with the surrounding ambient air to reduce shear noise resulting from the high velocity exhaust gases for noise attenuation. The flow mixer can also be perforated to allow for suction of ambient air by the lower static pressure engine exhaust gases to reduce shear noise and increase mixing and thrust. Two fixed fairings, above and below the tailpipe at the exit section can have perforations and also perforations on the movable fairings to educt surrounding air also to reduce shear noise between surrounding air and the engine exhaust flow during forward thrust based on SAE Aerospace Information Report AIR-1191 and method of calculation. Other configurations for the trailing edges of the fixed and movable fairings can have wavy contour lines to increase the contact area between the engine exhaust gases and the surrounding air to reduce shear noise as well. Fixed circular shape or rolling bodies, depicted as wheels for discussion purpose, but they can be o