A thrust reverser system for a turbofan propulsion system of an aircraft includes a fixed structure and a translating structure configured to internally define a sequential flow path for air. The translating structure is slidable along an axial direction between a stowed position in which the translating structure is connected to the fixed structure, and an opening position in which the translating structure is spaced apart from the fixed structure in the axial direction to define a circumferential opening for outflow of air to external environment. An iris mechanism has a plurality of blades jointly movable between a rest configuration in which the blades jointly define a passage for air, and a deployed configuration in which the blades at least partially occlude a bypass duct of the turbofan propulsion system.

A thrust reverser system for a turbofan propulsion system of an aircraft includes a fixed structure and a translating structure configured to internally define a sequential flow path for air. The translating structure is slidable along an axial direction between a stowed position in which the translating structure is connected to the fixed structure, and an opening position in which the translating structure is spaced apart from the fixed structure in the axial direction to define a circumferential opening for outflow of air to external environment. An iris mechanism has a plurality of blades jointly movable between a rest configuration in which the blades jointly define a passage for air, and a deployed configuration in which the blades at least partially occlude a bypass duct of the turbofan propulsion system.

A thrust reverser may comprise translating sleeve panel. A first articulating slider and a second articulating slider may be located at a circumferential end of the translating sleeve panel. Each of the first articulating slider and the second articulating slider may include a slider bar and a slider ball. The slider ball may be attached to the translating sleeve panel and located in a spherical opening defined by the slider bar.

A propulsion device that defines a central axis and a circumferential direction is provided. The propulsion device may include a core engine and a core casing. The core engine may include an engine shaft extending along the central axis. The core casing may have an inner surface and an outer surface. The core casing may extend along the circumferential direction about the propulsion device, as well as along the central axis from a forward end to an aft end. The core casing may define a primary air flowpath having an annular inlet at the forward end and an exhaust at the aft end. The core casing may further define a reverse flow passage extending from an outer surface entrance to an inner surface exit.

A propulsion device that defines a central axis and a circumferential direction is provided. The propulsion device may include a core engine and a core casing. The core engine may include an engine shaft extending along the central axis. The core casing may have an inner surface and an outer surface. The core casing may extend along the circumferential direction about the propulsion device, as well as along the central axis from a forward end to an aft end. The core casing may define a primary air flowpath having an annular inlet at the forward end and an exhaust at the aft end. The core casing may further define a reverse flow passage extending from an outer surface entrance to an inner surface exit.

A thrust reverser may comprise translating sleeve panel. A first articulating slider and a second articulating slider may be located at a circumferential end of the translating sleeve panel. Each of the first articulating slider and the second articulating slider may include a slider bar and a slider ball. The slider ball may be attached to the translating sleeve panel and located in a spherical opening defined by the slider bar.

An aircraft propulsion unit including a nacelle and a turbojet engine. The aircraft propulsion unit includes an external envelope, at least one fan casing, at least one actuator, and at least one support structure. The external envelope includes fan cowls. The fan casing cooperates with the fan cowls to define an interior space configured to house a thrust reverser configured to be displaced between a first position and a second position. The actuator configured to move the thrust reverser between the first position and the second position The support structure connects the fan cowls and the fan. The support structure includes at least one aperture configured to allow passage of part of the actuator.

A bypass turbofan engine with a nacelle comprising a fan case and a thrust-reversal system. The fan case comprises an exterior wall, and the reversal system comprises a slider having an upstream frame, a downstream frame and a plurality of spars fixed between the upstream frame and the downstream frame, in which the slider is able to move between a forward position and a retracted position. The fan case comprises, at a rear edge of its exterior wall, a support. Each support comprises, for each spar, a shoe fixed to the exterior wall and positioned radially about the spar, and a skirt secured to the shoes and extending the rear edge, in which, in a forward position, the skirt bears around the downstream frame, and in which in a forward/retracted/intermediate position, the shoes are distant from the spars from the upstream frame.

A method for connecting two components is proposed where a pressure acting on an adhesive between two join partners is supported by an auxiliary body which rests on a cutout of one of the components. Both components to be connected together and the auxiliary body are covered by a vacuum film and once the air has been sucked out, the compressive force is generated below the vacuum film.

A propulsion device that defines a central axis and a circumferential direction is provided. The propulsion device may include a core engine and a core casing. The core engine may include an engine shaft extending along the central axis. The core casing may have an inner surface and an outer surface. The core casing may extend along the circumferential direction about the propulsion device, as well as along the central axis from a forward end to an aft end. The core casing may define a primary air flowpath having an annular inlet at the forward end and an exhaust at the aft end. The core casing may further define a reverse flow passage extending from an outer surface entrance to an inner surface exit.