Abstract: A pylon for supporting an aircraft turbomachine, in particular for a test bench, the pylon having a generally elongated shape along an axis and including, at a first longitudinal end, first members for fixing to a turbomachine and, at a second longitudinal end, second members for fixing to a base plate, the pylon being traversed by at least one fluid pipe including a first end for connecting to the turbomachine and a second end for connecting to a fluid supply circuit, wherein the at least one pipe includes a movable portion movable in translation along the axis so as to be able to adjust the position along the axis of the first connecting end relative to the first longitudinal end. It also concerns a method of mounting an aircraft turbomachine on such a pylon.

Abstract: A pylon for supporting an aircraft turbomachine, in particular for a test bench, the pylon having a generally elongated shape along an axis and including, at a first longitudinal end, first members for fixing to a turbomachine and, at a second longitudinal end, second members for fixing to a base plate, the pylon being traversed by at least one fluid pipe including a first end for connecting to the turbomachine and a second end for connecting to a fluid supply circuit, wherein the at least one pipe includes a movable portion movable in translation along the axis so as to be able to adjust the position along the axis of the first connecting end relative to the first longitudinal end. It also concerns a method of mounting an aircraft turbomachine on such a pylon.

Abstract: A turbomachine for an aircraft including a mechanism forming a case fitted in a rear extension of an inner ferrule of an intermediate casing, and positioned around a central casing. The mechanism includes a structural upstream ferrule assembled on the inner ferrule and defining a front portion of a surface internally delimiting a secondary vein, and a main case extending on the upstream ferrule towards the rear. The turbomachine further includes a structural mechanism rigidifying the central casing, surrounded by the case, and extending towards the rear between the upstream ferrule and the central casing on which these mechanisms are assembled.

Abstract: The invention provides a nacelle for a bypass turbojet, the nacelle comprising: an aerodynamic fairing; a maintenance cover fastened to the aerodynamic fairing by means of at least one connection hinged about a longitudinal axis of the nacelle; a cold stream inner shroud and a cold stream outer shroud placed concentrically inside the aerodynamic fairing so as to define between them a flow passage for a cold stream, the inner shroud having at least one opening closed by a removable access hatch; and the outer shroud includes at least one opening closed by a removable access hatch that is fastened on the maintenance cover.

Abstract: A turbomachine for an aircraft including a mechanism forming a case fitted in a rear extension of an inner ferrule of an intermediate casing, and positioned around a central casing. The mechanism includes a structural upstream ferrule assembled on the inner ferrule and defining a front portion of a surface internally delimiting a secondary vein, and a main case extending on the upstream ferrule towards the rear. The turbomachine further includes a structural mechanism rigidifying the central casing, surrounded by the case, and extending towards the rear between the upstream ferrule and the central casing on which these mechanisms are assembled.

Abstract: Twin-flow turbo-jet engine, comprising a cylindrical casing externally defining an annular flow space for a secondary flow, wherein the cylindrical casing is formed from a lattice framework and from removable cowling panels fixed to the framework, said framework comprising an upstream annular flange for fixing to an intermediate housing, a downstream annular flange for connecting to an exhaust housing and rigid beams parallel or inclined relative to the axis of the turbo-jet engine, connecting the two flanges to one another.

Abstract: In a compressor stage including a movable bladed wheel having movable blades and a fixed bladed wheel having fixed blades, an air tapping circuit arrangement includes a movable wheel manifold designed to collect an air flow aspirated from the movable blades and a fixed wheel manifold designed to collect an air flow aspirated from the fixed blades. The movable wheel manifold is placed on the periphery of the compressor stage facing the movable wheel and the fixed wheel manifold is superposed on the movable wheel manifold.

Abstract: A turbomachine fan duct is disclosed. The fan duct includes two coaxial cylindrical walls, these being an internal wall and an external wall, respectively. The internal wall includes a framework to which panels are removably attached, and the external wall includes a single support structure with openings closed by removable panels. The openings in the external wall have dimensions that allow the panels of the internal wall to pass and allow these panels to be fitted onto and removed from the framework of the internal wall.

Abstract: The invention relates to a deoiling device. It comprises a tube (46), a first bearing (16) and a second bearing (18), the first and second bearings being placed in an oil chamber (20) in which an oil fog is maintained by rotation of the bearings. A deoiler (30) is provided in one wall of the oil chamber. The deoiler centrifuges oil in suspension in air and allows a deoiled air flow to pass inside the tube. The tube (46) comprises a closing cap (48) fitted with one or several outlet orifices (50) in its upper part designed to evacuate air, and an oil drain orifice (52) in its lower part.

Abstract: In a bypass turbomachine, at least one air takeoff orifice is provided in the primary channel, said orifice leading to an air takeoff pipe housed inside an air inlet sleeve of the nacelle. The air takeoff pipe opens out in the vicinity of the pylon into two air diffusion pipes each secured to a respective maintenance cover, each air diffusion pipe opening out into an air injection pipe secured to a thrust reverser cover and itself opening out to the outside of the nacelle via the trailing edge thereof, each air injection pipe being suitable for uncoupling from the corresponding air diffusion pipe when the corresponding thrust reverser cover slides downstream.

Abstract: The invention provides a nacelle for a bypass turbojet, the nacelle comprising: an aerodynamic fairing; a maintenance cover fastened to the aerodynamic fairing by means of at least one connection hinged about a longitudinal axis of the nacelle; a cold stream inner shroud and a cold stream outer shroud placed concentrically inside the aerodynamic fairing so as to define between them a flow passage for a cold stream, the inner shroud having at least one opening closed by a removable access hatch; and the outer shroud includes at least one opening closed by a removable access hatch that is fastened on the maintenance cover.

Abstract: The invention relates to a deoiling device. It comprises a tube (46), a first bearing (16) and a second bearing (18), the first and second bearings being placed in an oil chamber (20) in which an oil fog is maintained by rotation of the bearings. A deoiler (30) is provided in one wall of the oil chamber. The deoiler centrifuges oil in suspension in air and allows a deoiled air flow to pass inside the tube. The tube (46) comprises a closing cap (48) fitted with one or several outlet orifices (50) in its upper part designed to evacuate air, and an oil drain orifice (52) in its lower part.

Abstract: In a bypass turbomachine, at least one air takeoff orifice is provided in the primary channel, said orifice leading to an air takeoff pipe housed inside an air inlet sleeve of the nacelle. The air takeoff pipe opens out in the vicinity of the pylon into two air diffusion pipes each secured to a respective maintenance cover, each air diffusion pipe opening out into an air injection pipe secured to a thrust reverser cover and itself opening out to the outside of the nacelle via the trailing edge thereof, each air injection pipe being suitable for uncoupling from the corresponding air diffusion pipe when the corresponding thrust reverser cover slides downstream.

Abstract: In a compressor stage (7) comprising a movable bladed wheel (10) having movable blades (8) and a fixed bladed wheel (12) having fixed blades (9), the air tapping circuit arrangement comprises a movable wheel manifold (24) designed to collect an air flow aspirated from the movable blades (8) and a fixed wheel manifold (28) designed to collect an air flow aspirated from the fixed blades (9), and said movable wheel manifold (24) is placed on the periphery of said compressor stage (7) facing said movable wheel (10) and said fixed wheel manifold (28) is superposed on said movable wheel manifold (24). Application to a compressor stage (7) of a turbojet (1).