Abstract: This pitch-change mechanism (70) comprises a frame (72), a movable part (102) that is translatable along a longitudinal axis (X), and a locking device (160) for immobilising the movable part (102) with respect to the frame (72). The locking device (160) comprises a movable member (210) that is translatable with respect to a locking member (164) between a retracted position in which it leaves the locking member (164) free to be in an unlocked configuration away from a surface (162) and a deployed position in which it forces the locking member (164) into a locked configuration engaged with the surface (162). It also comprises a biasing member (220) which urges the movable member (210) toward its deployed position and a holding device (222) for holding the movable member (210) in its retracted position.

Abstract: This pitch-change mechanism (70) comprises a frame (72), a moving part (102) which is translatably moveable along a longitudinal axis (X), and a locking device (160) for immobilising the moving part (102) relative to the frame (72). The locking device (160) comprises a blocking surface (162), a guide surface (164) and a blocking member (166) interposed therebetween. It further comprises a biasing member (200) which urges the guide surface (164) and the blocking member (166) toward one configuration of one relative to the other and a holding device (202) for holding the guide surface (164) and the blocking member (166) in another configuration under certain predetermined conditions.

Abstract: A fan module having variable-pitch blades is configured for use with for a propulsion unit having a longitudinal axis. The fan module includes a rotary casing carrying the blades and a pitch-changing system. The pitch-changing system includes a control device that includes an annular actuator having a stationary body added onto the rotary casing and a body configured to translate with respect to the stationary body along the longitudinal axis. A linking mechanism includes a synchronizing ring coupled to the mobile body, connected to the blades and configured to be translated along the longitudinal axis by the mobile body so as to change the pitch of the blades. A feathering device includes fly-weights coupled to the ring by a connecting rod of which the ends include ball-and-socket joints.

Abstract: An assembly for a propeller of a turbine engine of an aircraft is provided. The assembly includes a variable-pitch vane having a blade connected to a root, the vane having a longitudinal axis aligned with a vane pitch axis which passes through the root, a base rigidly connected to the vane to rotate together with the vane about the axis and connected to a portion of a toothed wheel extending around the axis, and a counterweight device having a shaft which can rotate about an axis substantially perpendicular to the axis, the shaft being connected to at least one flyweight and to a pinion meshed with the toothed wheel portion. The toothed wheel portion can be attached to the base by at least one shear pin.

Abstract: A fan module having variable-pitch blades is configured for use with for a propulsion unit having a longitudinal axis. The fan module includes a rotary casing carrying the blades and a pitch-changing system. The pitch-changing system includes a control device that includes an annular actuator having a stationary body added onto the rotary casing and a body configured to translate with respect to the stationary body along the longitudinal axis. A linking mechanism includes a synchronizing ring coupled to the mobile body, connected to the blades and configured to be translated along the longitudinal axis by the mobile body so as to change the pitch of the blades. A feathering device includes fly-weights coupled to the ring by a connecting rod of which the ends include ball-and-socket joints.

Abstract: An assembly for a propeller of a turbine engine of an aircraft is provided. The assembly includes a variable-pitch vane having a blade connected to a root, the vane having a longitudinal axis aligned with a vane pitch axis which passes through the root, a base rigidly connected to the vane to rotate together with the vane about the axis and connected to a portion of a toothed wheel extending around the axis, and a counterweight device having a shaft which can rotate about an axis substantially perpendicular to the axis, the shaft being connected to at least one flyweight and to a pinion meshed with the toothed wheel portion. The toothed wheel portion can be attached to the base by at least one shear pin.

Abstract: The invention proposes a guide arm for guiding at least one element having an elongated shape (20), corresponding to a set of cables and/or pipes. The arm comprises an inner cavity (62) opening on the outside of the arm at each of the ends thereof, and in which the elements having an elongated shape can extend. According to the invention, this structure more particularly comprises: a frame (8) comprising a beam (18) linked to means (30, 36, 44) for holding the elements having an elongated shape on the outside and along the beam, and a cover (54) of which the walls (56, 58) cover the holding means of the frame, and are engaged with the beam, in such a way as to form the inner cavity in which the elements having and elongated shape extend, shock-absorbing means (68) being arranged between the means (30, 36, 44) for holding the elements having an elongated shape (20), and the longitudinal walls (56, 58), in such a way as to reduce and damp the movements of the means for holding in the cavity (62).

Abstract: An aircraft casing structure including a shroud surrounding the engine and made up of a plurality of sectors; a plurality of radial arms, each mounted between two adjacent shroud sectors and each having a base; and a plurality of fasteners for fastening the shroud sectors on the bases of the radial arms; the fasteners including a plurality of plates each mounted flush in a respective groove of corresponding shape in a shroud sector, and a set of headed bolts held captive in the plate by a difference of diameter between their shanks and their threads, a set of captive nuts being fastened to the bases to provide a secure connection between the shroud sectors and the radial arms by each nut receiving the thread of a respective captive bolt of the set of headed bolts.

Abstract: A casing structure interposed between the engine and the nacelle of an aircraft, the structure including a shroud surrounding the engine having an engine axis and including a stationary portion and a plurality of sectors; a radial arm providing the connection to the nacelle; fasteners for securing the plurality of shroud sectors to one another or to the radial arm; and the fasteners include two series of holes formed in two parallel side walls of the shroud sectors for the purpose of receiving two respective series of bolts, each passing through a corresponding set of orifices of an adjacent shroud sector or of an adjacent radial arm, a hinge arranged between each of the shroud sectors and the stationary portion of the shroud to enable the shroud sectors to be pivoted in individual manner about a common pivot axis perpendicular to the side walls arranged along the engine axis.

Abstract: A casing structure interposed between the engine and the nacelle of an aircraft, the casing structure including a shroud surrounding the engine and including a plurality of sectors; at least one radial arm providing the connection to the nacelle; and a plurality of fasteners for securing the plurality of shroud sectors to one another or to the at least one radial arm; the plurality of fasteners including a plurality of connection tabs, each provided with two parallel series of holes for receiving two respective series of headed bolts, a first series passing through a corresponding set of orifices of one shroud sector, and a second series passing through a corresponding set of orifices of an adjacent shroud sector or an adjacent radial arm.

Abstract: A case structure interposed between the engine and the nacelle of the aircraft is provided. The case structure includes: a ferrule surrounding the engine and including a plurality of segments; at least one radial arm ensuring connection to the nacelle; and a plurality of attachment devices for securing the plurality of ferrule segments together or with at least one radial arm. The plurality of attachment devices includes an articulation device configured for ensuring coupling of the lifted-rotated-pushed type ensuring after disengagement of the ferrule segment, its pivoting about a pivot axis parallel to a longitudinal axis of the engine and then its blocking in a disengagement position.

Abstract: The invention proposes a guide arm for guiding at least one element having an elongated shape (20), corresponding to a set of cables and/or pipes. The arm comprises an inner cavity (62) opening on the outside of the arm at each of the ends thereof, and in which the elements having an elongated shape can extend. According to the invention, this structure more particularly comprises: a frame (8) comprising a beam (18) linked to means (30, 36, 44) for holding the elements having an elongated shape on the outside and along the beam, and a cover (54) of which the walls (56, 58) cover the holding means of the frame, and are engaged with the beam, in such a way as to form the inner cavity in which the elements having and elongated shape extend, shock-absorbing means (68) being arranged between the means (30, 36, 44) for holding the elements having an elongated shape (20), and the longitudinal walls (56, 58), in such a way as to reduce and damp the movements of the means for holding in the cavity (62).

Abstract: A casing structure interposed between the engine and the nacelle of an aircraft, the structure including a shroud surrounding the engine having an engine axis and including a stationary portion and a plurality of sectors; a radial arm providing the connection to the nacelle; fasteners for securing the plurality of shroud sectors to one another or to the radial arm; and the fasteners include two series of holes formed in two parallel side walls of the shroud sectors for the purpose of receiving two respective series of bolts, each passing through a corresponding set of orifices of an adjacent shroud sector or of an adjacent radial arm, a hinge arranged between each of the shroud sectors and the stationary portion of the shroud to enable the shroud sectors to be pivoted in individual manner about a common pivot axis perpendicular to the side walls arranged along the engine axis.

Abstract: A casing structure interposed between the engine and the nacelle of an aircraft, the casing structure including a shroud surrounding the engine and including a plurality of sectors; at least one radial arm providing the connection to the nacelle; and a plurality of fasteners for securing the plurality of shroud sectors to one another or to the at least one radial arm; the plurality of fasteners including a plurality of connection tabs, each provided with two parallel series of holes for receiving two respective series of headed bolts, a first series passing through a corresponding set of orifices of one shroud sector, and a second series passing through a corresponding set of orifices of an adjacent shroud sector or an adjacent radial arm.

Abstract: An aircraft casing structure including a shroud surrounding the engine and made up of a plurality of sectors; a plurality of radial arms, each mounted between two adjacent shroud sectors and each having a base; and a plurality of fasteners for fastening the shroud sectors on the bases of the radial arms; the fasteners including a plurality of plates each mounted flush in a respective groove of corresponding shape in a shroud sector, and a set of headed bolts held captive in the plate by a difference of diameter between their shanks and their threads, a set of captive nuts being fastened to the bases to provide a secure connection between the shroud sectors and the radial arms by each nut receiving the thread of a respective captive bolt of the set of headed bolts.

Abstract: A case structure interposed between the engine and the nacelle of the aircraft including: a ferrule surrounding the engine and comprising a plurality of segments (12A, 12B), at least one radial arm (14) ensuring connection to the nacelle, a plurality of attachment means for securing this plurality of ferrule segments together or with at least one radial arm, the plurality of attachment means including an articulation device (24) configured for ensuring coupling of the lifted-rotated-pushed type ensuring after disengagement of the ferrule segment, its pivoting about a pivot axis parallel to a longitudinal axis of said engine and then its blocking in a disengagement position.