Abstract: A combustion chamber of an aircraft turbomachine having a main axis includes: a body of revolution coaxial with the main axis having a plurality of combustion tubes extending mainly in the direction of the main axis and being distributed in a ring about the main axis; a first perforated rotary disc mounted at a first axial end of the body and rotatable about the main axis to selectively open or close a first end of each of the combustion tubes; and a second perforated rotary disc mounted at a second axial end of the body and rotatable about the main axis to selectively open or close a second end of each of the combustion tubes. The body includes a plurality of cooling segments extending mainly in the direction of the main axis, which are distributed in a ring about the main axis and around the combustion tubes.

Abstract: Engine comprising a propeller unit with a pair of contrarotating propellers (31, 32), a gas generator (5) supplying a power turbine (53), the pair of propellers being rotationally driven by the shaft (53A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset (7) and a first stage (6) comprising a simple gearset connecting the turbine shaft (53A) and the differential gearset (7), the engine air intake comprising an air intake duct (11), the air intake duct (11) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset (7).

Abstract: The assembly (25) links a static housing (24) of the turbomachine, into which supply lines, in particular fluid supply lines (23), arrive, to the blades of the propeller, and comprises: —a system for controlling fluid pitch (27), rigidly connected to the static housing (24), capable of being linked to the supply lines, —a linear actuator (28) having two chambers separated by a piston (71) of which the sliding is dictated by the control system and allows the blades to rotate, and —two concentric tubes (36, 37) housed in the planetary shaft of the epicyclic reduction gear and linking the system (27) to the actuator (28) by delimiting two fluid passages (45, 48) linked, respectively, with the two chambers (72, 73) of the actuator.

Abstract: Engine comprising a propeller unit with a pair of contrarotating propellers (31, 32), a gas generator (5) supplying a power turbine (53), the pair of propellers being rotationally driven by the shaft (53A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset (7) and a first stage (6) comprising a simple gearset connecting the turbine shaft (53A) and the differential gearset (7), the engine air intake comprising an air intake duct (11), the air intake duct (11) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset (7).

Abstract: A turbo engine includes a system for changing a pitch of blades of a propeller, the system including an annular fluid cylinder with a linear drive and a link mechanism linking the cylinder to the blades of the propeller to change an orientation of the propeller. The annular cylinder of the system can be rigidly mounted on a fixed housing supporting the propeller and internal to the propeller, unlike the blades mounted in an external rotating hub of the propeller, and the link mechanism includes a displacement transfer bearing fixed, on one side, to the mobile part of the cylinder and cooperating, on the other side, with a mechanism linking to the blades of the rotating hub of the propeller.

Abstract: The assembly (25) links a static housing (24) of the turbomachine, into which supply lines, in particular fluid supply lines (23), arrive, to the blades of the propeller, and comprises: —a system for controlling fluid pitch (27), rigidly connected to the static housing (24), capable of being linked to the supply lines, —a linear actuator (28) having two chambers separated by a piston (71) of which the sliding is dictated by the control system and allows the blades to rotate, and —two concentric tubes (36, 37) housed in the planetary shaft of the epicyclic reduction gear and linking the system (27) to the actuator (28) by delimiting two fluid passages (45, 48) linked, respectively, with the two chambers (72, 73) of the actuator.

Abstract: A turbo engine includes a system for changing a pitch of blades of a propeller, the system including an annular fluid cylinder with a linear drive and a link mechanism linking the cylinder to the blades of the propeller to change an orientation of the propeller. The annular cylinder of the system can be rigidly mounted on a fixed housing supporting the propeller and internal to it, unlike the blades mounted in an external rotating hub of the propeller, and the link mechanism includes a displacement transfer bearing fixed, on one side, to the mobile part of the cylinder and cooperating, on the other side, with a mechanism linking to the blades of the rotating hub of the propeller.

Abstract: A coupling device for coupling a turbine upstream guide vane which is coupled to a supporting part which itself attached to a stabilizing part is disclosed. The coupling device includes a interlocking device for interlocking a supporting end of the supporting part with a stabilizing end of the stabilizing part, and a retaining part to keep the supporting end and the stabilizing end interlocked. The coupling device may be used to couple an upstream guide vane of a turbojet turbine.

Abstract: A device for detecting breakage of a turbomachine shaft is disclosed. The device includes a shaft having an upstream end and a downstream end; a rod having an upstream end and a downstream end, and placed coaxially inside the shaft, the downstream end of the rod being securely fastened to the downstream end of the shaft and the upstream end of the rod being free to rotate relative to the upstream and of the shaft; and a sensor suitable for detecting a difference in speed of rotation between the upstream end of the rod and the upstream end of the shaft.

Abstract: A device for, in a gas turbine engine, braking a turbine including a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking is disclosed. The device includes a first braking member provided with at least one abrasive element and a second braking member including a ring-shaped element (120A) made of a material capable of being eroded by the abrasive element. One of the two braking members being secured to the rotor and the other of the two braking members being secured to the stator. The braking members come into contact with one another through axial displacement of the rotor once the shaft has broken. The abrasive element of the first braking member eroding the ring-shaped element of the second braking member.

Abstract: A device for supplying ventilation air to a turbine rotor of a gas turbine engine including a first turbine disk, a second turbine disk, and a downstream shell ring together forming a one-piece drum is disclosed. The second turbine disk includes cavities machined in the rim to house the turbine blades, where the blades are axially retained by axial retaining segments. The downstream shell ring has at least one aperture drilled therethrough, downstream of the rim, which places an internal volume of the drum in fluid communication with at least one of the cavities via a passage formed in the segments.

Abstract: A device for, in a gas turbine engine, braking a turbine including a rotor, having at least one disk with a rim driving a shaft and capable of rotating with respect to a stator, is disclosed. The device is for the event of the shaft breaking and includes a first braking member, secured to the rim and provided with at least one cutting element, and a second braking member secured to the stator downstream of the rim and including a ring-shaped element made of a material that can be cut by the cutting element. The two braking members coming into contact with one another through axial displacement of the rotor once the shaft has broken. The cutting element of the first braking member cuts the ring-shaped element of the second braking member.

Abstract: A double-body gas turbine engine, including a low-pressure body LP and a high-pressure body HP, rotatably mounted about a single shaft in a stationary casing, the low-pressure body LP including a compressor and a turbine connected by a low-pressure shaft LP. The low-pressure shaft LP is supported by an upstream LP bearing, a first downstream LP bearing, and an additional downstream LP bearing by the stationary casing, the high-pressure body being supported by an upstream HP bearing and a downstream HP bearing which is an inter-shaft bearing including an inner track rigidly connected to the HP turbine rotor and an outer track rigidly connected to the LP shaft.

Abstract: A device (40) for limiting overspeed in a turbomachine in the event of breakage of the turbine shaft (24), comprising means (38, 44) of propelling a pin (42) into the path of the blades (22), these propelling means being controlled by means (36) that detect overspeed or that the turbine shaft has broken.

Abstract: Devices for intaking gases from the boundary layer through ducts hollowed out in blades. These devices are suitable for variable setting blades, installed on the stator using pivots. The seal is maintained despite the variation in the relative position between the moving pivots through which ducts pass, and the fixed intake header pipe.

Abstract: The present invention relates to a device for supplying ventilation air to a turbine rotor of a gas turbine engine comprising a first and a second turbine disk (11, 12) and a downstream shell ring (14) together forming a one-piece drum, the second turbine disk (12) comprising cavities machined in the rim (12J) to house the turbine blades (6), the blades being axially retained by axial retaining segments (18, 18?). The device is one wherein at least one drilling (12P) is made in the shell ring (14) downstream of the rim (12J) placing the inside of the drum in communication with at least some of said cavities, a passage (18P; 18?P) being formed in the segments (18; 18?).

Abstract: The present invention relates to a device for, in a gas turbine engine, braking a turbine comprising a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking. The device is one which comprises a first braking member (110) provided with at least one abrasive element (110A) and a second braking member (120) comprising a ring-shaped element (120A) made of a material capable of being eroded by the abrasive element (110A), the two braking members being secured one of them to the rotor and the other to the stator and coming into contact with one another through axial displacement of the rotor once the shaft has broken, the abrasive element (110A) of the first braking member (110) eroding the ring-shaped element (120A) of the second braking member (120).

Abstract: The present invention relates to detecting breakage of a shaft of a turbomachine, in particular of the aviation type. The invention relates in particular to a device designed to perform such detection. According to the invention, the device for detecting breakage of a turbomachine shaft comprises: a shaft having an upstream end and a downstream end; a rod having an upstream end and a downstream end, and placed coaxially inside the shaft, the downstream end of the rod being securely fastened to the downstream end of the shaft and the upstream end of the rod being free to rotate relative to the upstream and of the shaft; and a sensor suitable for detecting a difference in speed of rotation between the upstream end of the rod and the upstream end of the shaft.

Abstract: The present invention relates to a device for, in a gas turbine engine, braking a turbine comprising a rotor, having at least one disk (63?) with a rim (63?B), driving a shaft and capable of rotating with respect to a stator, this device being for the event of said shaft breaking and comprising a first braking member (110), secured to said rim and provided with at least one cutting element (110A), and a second braking member (120) secured to the stator downstream of the rim (63?B), comprising a ring-shaped element (120A) made of a material that can be cut by the cutting element (110A), the two braking members coming into contact with one another through axial displacement of the rotor once the shaft has broken, the cutting element (110A) of the first braking member (110) cutting the ring-shaped element (120A) of the second braking member (120).

Abstract: A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the inner collar. The system further includes a locking mechanism between the pipe and the inner collar.