Abstract: The invention relates to a firewall (112) for a turbomachine (100) auxiliary arm (106). This firewall (112), which has one or more through openings (180) in a thickness direction (Z) of the firewall (112), comprises a fixed portion (120) and a first removable portion (130) extending, in a width direction (Y), orthogonal to said thickness direction (Z), from at least one adjacent opening among the through openings (180), to a first outer edge (190) of the firewall (112). To open this firewall (112) in order to allow access to one or more ducts and/or electrical cables (111) received in the through openings (180), the first removable portion (130) can be dismantled.

Abstract: An annular intermediate casing for a turbomachine through which an aerodynamic airstream circulates, including a radially internal shroud (31), a radially external shroud, at least one stator blade including a vane with a leading edge, and at least one aero-dynamic member which is formed of a structural arm extending radially at least in part between the radially internal shroud and the radially external shroud. The aerodynamic member includes a leading edge which is aligned with the leading edge of the stator blade in one plane and which is borne by a profiled portion positioned upstream of the structural arm in the direction of circulation of the aerodynamic airstream, the profiled portion, the structural arm, the radially internal shroud and the radially external shroud being monobloc.

Abstract: The invention relates to a firewall (112) for a turbomachine (100) auxiliary arm (106). This firewall (112), which has one or more through openings (180) in a thickness direction (Z) of the firewall (112), comprises a fixed portion (120) and a first removable portion (130) extending, in a width direction (Y), orthogonal to said thickness direction (Z), from at least one adjacent opening among the through openings (180), to a first outer edge (190) of the firewall (112). To open this firewall (112) in order to allow access to one or more ducts and/or electrical cables (111) received in the through openings (180), the first removable portion (130) can be dismantled.

Abstract: An intermediate turbojet case comprises a hub that supports removable panels and bleed lines, the hub comprising a flank provided with openings, each bleed line having an upstream end engaged in an opening in the flank and a downstream end terminated by a base plate through which it is fixed to an internal face of a removable panel by way of screws, each removable panel having a front edge at which it is fixed to an external lip of the hub by screws. At least one removable panel comprises a downstream edge supporting a retaining element close to the internal face to hold the base plate in contact with the internal face during a phase in which the removable panel is fixed to the hub by screwing, this phase preceding attachment of the base plate to the removable panel by screwing.

Abstract: An intermediate turbojet case comprises a hub that supports removable panels and bleed lines, the hub comprising a flank provided with openings, each bleed line having an upstream end engaged in an opening in the flank and a downstream end terminated by a base plate through which it is fixed to an internal face of a removable panel by way of screws, each removable panel having a front edge at which it is fixed to an external lip of the hub by screws. At least one removable panel comprises a downstream edge supporting a retaining element close to the internal face to hold the base plate in contact with the internal face during a phase in which the removable panel is fixed to the hub by screwing, this phase preceding attachment of the base plate to the removable panel by screwing.

Abstract: A unit including an intermediate turbojet casing formed by a hub including a downstream transverse endplate having formed therein at least one first opening putting the inside of the hub into communication with a duct extending downstream from the endplate and opening out at its downstream end via a second opening formed in an outer annular shroud extending downstream from the hub for defining the inside of an annular flow space for a secondary stream, is provided. The upstream end of the duct is fastened to the downstream endplate of the hub by releasable elastic engagement.

Abstract: A discharge conduit suitable for use with a turbine engine. The discharge conduit includes an air intake end, an air outlet end and a tubular duct for guiding air between the air intake and air outlet ends. The air intake end is equipped with attachment elements for attachment to an intermediate casing of the turbine engine. The attachment element can be of the resilient snap-in type.

Abstract: The invention relates to a unit comprising an intermediate turbojet casing formed by a hub including a downstream transverse endplate having formed therein at least one first opening putting the inside of the hub into communication with a duct extending downstream from the endplate and opening out at its downstream end via a second opening formed in an outer annular shroud extending downstream from the hub for defining the inside of an annular flow space for a secondary stream. More particularly, the upstream end of said duct is fastened to the downstream endplate of the hub by releasable elastic engagement.

Abstract: Discharge conduit for a turbine engine, comprising an air intake end, an air outlet end and a tubular sleeve for guiding air between said ends, said air intake end being equipped with means for attachment to an intermediate casing of the turbine engine, characterized in that said attachment means are of the resilient snap-in type.