A thrust reverser system for jet aircraft comprising an exhaust tailpipe mounted to the turbine engine aft turbine flange, clamshell doors, actuators and locking systems to prevent inadvertent deployment of the clamshell doors. Improved design clamshell doors shrouding the tailpipe fitted with two patented design actuators, enclosed between the doors and the tailpipe. The actuators throw the doors behind the tailpipe exhaust exit area using improved linkages attached to the tailpipe and the doors, to reverse the exhaust gases forward. The tailpipe can be of circular or any geometric shape. Reverse Exhaust gases are enclosed between the doors and two movable fairings. Several sound attenuation configurations provisions for the tailpipe, the fixed and movable fairings. Three independent locking systems provisions to prevent inadvertent deployment of the doors.

A thrust reverser system for jet aircraft comprising an exhaust tailpipe mounted to the turbine engine aft turbine flange, clamshell doors, actuators and locking systems to prevent inadvertent deployment of the clamshell doors. Improved design clamshell doors shrouding the tailpipe fitted with two patented design actuators, enclosed between the doors and the tailpipe. The actuators throw the doors behind the tailpipe exhaust exit area using improved linkages attached to the tailpipe and the doors, to reverse the exhaust gases forward. The tailpipe can be of circular or any geometric shape. Reverse Exhaust gases are enclosed between the doors and two movable fairings. Several sound attenuation configurations provisions for the tailpipe, the fixed and movable fairings. Three independent locking systems provisions to prevent inadvertent deployment of the doors.

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.

Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface, a fan track liner comprising abradable material layer, and a rear acoustic panel arranged aft of the fan track liner. The fan track liner and the rear acoustic panel are integrated into a single panel structure attached to the fan case inner surface.

Disclosed are systems and methods to bore or tunnel through various geologies in an autonomous or substantially autonomous manner including one or more non-contact boring elements that direct energy at the bore face to remove material from the bore face through fracture, spallation, and removal of the material. Systems can automatically execute methods to control a set of boring parameters that affect the flux of energy directed at the bore face. Systems can further automatically execute the methods to: monitor, direct, maintain, and/or adjust a set of boring controls, including for example a standoff distance between the system and the bore face, a temperature of exhaust gases directed at the bore face, a removal rate of material from the bore face, and/or a thermal or topological characterization of the bore face during boring operations.

Aircraft engine exhaust systems enabling short aft fairings are described. An example turbofan engine exhaust system of an aircraft includes a primary nozzle having a leading edge and a trailing edge, and a heat shield coupled to an aft strut fairing. The heat shield has an upstream end and a downstream end. The downstream end of the heat shield is substantially coterminous with the trailing edge of the primary nozzle.

Aircraft engine exhaust systems enabling short aft fairings are described. An example turbofan engine exhaust system of an aircraft includes a primary nozzle having a leading edge and a trailing edge, and a heat shield coupled to an aft strut fairing. The heat shield has an upstream end and a downstream end. The downstream end of the heat shield is substantially coterminous with the trailing edge of the primary nozzle.

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.

Provided is a supersonic aircraft including: a shield that shields an engine exhaust flow discharged from a jet engine accommodated in an engine nacelle mounted on a fuselage of the aircraft to thereby reduce sonic booms due to the engine exhaust flow; and an exhaust nozzle that is provided in an exhaust port of the engine nacelle and that generates a sound source for high-frequency components at a position at which the shield is capable of shielding the high-frequency components of the engine exhaust flow, to thereby reduce jet noise having the high-frequency components, and promotes mixing of the engine exhaust flow that generates low-frequency noise components with an external air flow to thereby reduce jet noise having the low-frequency components.