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: A turbine engine for aircraft includes a gas generator as well as to a receiver driven by a power turbine, and to an electric power generator, the rotor of which centered on a rotor axis distinct from the longitudinal axis, is driven into rotation by the power turbine, via a mechanical gear transmission, including a toothed drive wheel centered on the axis. Further the receiver includes a first propeller driven by a free power turbine and the toothed drive wheel is attached on an outer case of this power turbine.

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 present invention relates to a turbine engine for aircraft comprising a gas generator as well as to a receiver driven by a power turbine (34), and to an electric power generator (60), the rotor (62) of which centred on a rotor axis (62?) distinct from the longitudinal axis (2), is driven into rotation by the power turbine, via a mechanical gear transmission (80), comprising a toothed drive wheel (82) centred on the axis (2). Further the receiver comprises a first propeller driven by a free power turbine (34) and the toothed drive wheel (82) is attached on an outer case (40) of this power turbine (34).

Abstract: A turbine engine for an aircraft is disclosed. The engine includes a gas generator and a receiver driven by a power turbine. The receiver includes a propeller driven by a free power turbine provided with an outer case. The propeller includes a propeller case located radially outwards relatively to the outer case, and from which blades protrude radially outwards. The engine also includes an electric power generator. The rotor of the generator is centered on the longitudinal axis of the turbine engine, and is driven into rotation by the power turbine while being attached on the propeller case.

Abstract: The present invention relates to a turbine engine (100) for aircraft comprising a gas generator (14) as well as a receiver (30) driven by a power turbine (34, 38), this receiver comprising a propeller (32) driven by a free power turbine (34) provided with an outer case (40), the propeller (32) having a propeller case (46) located radially outwards relatively to the outer case (40), and from which blades (48) protrude radially outwards. According to the invention, it comprises an electric power generator (60), the rotor (62) of which centred on the longitudinal axis (2) of the turbine engine, is driven into rotation by the power turbine (34) while being attached on the propeller case (46).