Abstract: The present invention relates to a gas turbine engine comprising a shaft, a bearing, a coupling supported by the bearing, the shaft being engaged by an end trunnion inside the coupling and fixed to the coupling by means of a cylindrical nut. The engine is characterized in that the nut is in axial abutment in a first direction against the coupling and the trunnion is screwed onto the nut, a slotted stop ring housed in an annular groove of the nut forms an axial abutment in the direction opposing the first direction, so as to allow the removal of the trunnion from the coupling by unscrewing the nut.

Abstract: The relief device is designed to divert a portion (94) of a main flow (90) toward a by-pass flow (92) in a turbojet that comprises a main flow stream (10), a by-pass flow stream (14) and an intermediate casing (20).

Abstract: The present invention relates to an accessory gear box driveshaft (125) in a turbojet engine with intermediate casing (119), designed to be mounted in a radial arm (119c) of the intermediate casing (119), said shaft being connected, at a first end, to a means (126) of mechanical transmission to an engine shaft of the turbojet engine, and, at a second end, to a means of mechanical transmission to said box and comprising a bevel gear (125a1) between the two ends, to provide mechanical transmission to an additional accessory (128). This shaft is notable in that, together with said gear (125a1), it is contained in a case (131) forming an oil circuit sealed against said arm (119c). The invention also relates to an accessory (128) comprising a drive shaft (128a) collaborating with the gear (125a1) of the transmission shaft (125) and forming a modular assembly (130) therewith.

Abstract: The turbine engine of the invention includes a rotor with at least one bearing, mounted on a bearing supporting part, said part being connected to the fixed structure by an uncoupling device, including at least one fusible screw passing through at least one bore, said screw comprising a head and a threaded portion, a fusible portion forming a preferential failure area, located between the head of the screw and its threaded portion. The screw comprises, between its threaded portion and its fusible portion, a portion for blocking the screw in rotation, cooperating with a complementary blocking portion provided in the bore. By means of the invention, the torsional torque related to the tightening of the screw is not transmitted to its fusible portion.

Abstract: The invention relates to a system for attaching the end of a shaft (14) of a gas turbine engine engaged inside a coupling (15) supported by a bearing (3). Said system comprising a nut (16) is characterized in that the nut (16) comprises a first thread (16f1) by which it is screwed into said shaft (14) and a second thread (16f2) by which it is screwed to said coupling (15). Advantageously, the screw pitches of the two threads (16f1, 16f2) of the nut (16) are reversed relative to one another so as to form an adjusting nut.

Abstract: The invention relates to a system for fastening the end of a gas turbine engine shaft (4) engaged inside a sleeve (15) supported by a bearing (3). Said system comprises a nut (16) and is characterized in that the nut (16) is screwed at one end inside said sleeve (16) and is connected by a segment-type connection (18) with the shaft at the other end.