Abstract: A nozzle stage for a turbine engine includes two substantially cylindrical rings, respectively an inner ring and an outer ring, with, extending between them: vanes carried by a first one of the rings; vanes carried by the second ring; and spacer-forming vanes interconnecting the two rings; the vanes of the first and second rings being arranged in alternation.

Abstract: A prestressing device extending about an axis between a first plane and a second plane, the first plane being located at a predetermined distance from the second plane, each plane being perpendicular to the axis. The device includes at least three deformation areas. The deformation areas extend in the first plane. The device further includes, between each deformation area, a planar contact surface extending in the second plane.

Abstract: A prestressing device extending about an axis between a first plane that is substantially perpendicular to the axis and a second plane that is substantially parallel to the first plane and axially offset relative to the latter. The device includes a first annular body extending in the first plane, and a first series of at least three tabs, each of which is connected to the first body and extending in an essentially radial direction, each of the tabs of the first series including a planar surface extending in the second plane. This arrangement ensures surface contact between the parts of the elements to be subjected to prestressing. The device can be used for example for a rotor, and for example for a rotor of an unducted propeller for a turbine engine.

Abstract: A control device of variable pitch vanes in a turbomachine is disclosed. The control device includes a ring surrounding a casing of the turbomachine and connected by links to the variable pitch vanes, and a jack connected to the ring in order to displace it in rotation around the casing. The jack is mounted pivoting on the casing and its piston rod is connected to the ring by a connecting rod. The piston and connecting rods are articulated on an axis which is connected to the casing by a guiding device maintaining it at a substantially constant distance from the casing.

Abstract: A hub of a propeller with variable-pitch blades for a turbine engine, for example for a propfan engine. The hub of the propeller includes a polygonal ring with substantially radial cylindrical recesses distributed about a central axis of the ring for receiving the blades, a turbine rotor element of the turbine engine, and a securing flange that is attached to the ring so as to connect the ring to the rotor element. The hub further includes a plurality of back-up hooks inserted with clearance in openings, the back-up hooks being connected either to the ring or to the rotor element, and the openings being connected to the other one of the two.

Abstract: A non-streamlined propeller including blades with a variable setting for a turbine engine, the blades of the propeller being rotatably mounted about the axes thereof in radial recesses of a rotor element, and each blade being supported by a plate held in a recess by a sectored ring, and including an inner portion mounted, by interlocking, in a groove of the plate, the ring sectors being inserted into the recess from the inside and locked by a nut screwed onto the plate.

Abstract: A variable-pitch control device for a turbomachine compressor is disclosed. The device includes a rod, a fastening device for fastening a first end of the rod to a pivot of a vane to be controlled, and a connection device between a second end of the rod and a control ring. The rod is substantially cylindrical, its first end being engaged in a bore in the pivot of the vane. The device further includes a clamping device for clamping the first end of the rod in the bore in the pivot in order to fasten it to the pivot.

Abstract: A control system for controlling at least two variable-geometry devices of a turbomachine, and a turbomachine including such a control system, the system including an actuator that actuates both devices; one of the devices including at least one stage of variable-pitch stator vanes, and the other device being an air-bleed valve for a turbomachine body. The system is configured to control progression opening of the vane stage and progressive closing of the air-bleed valve as an actuation parameter of the actuator increases. As a result, the control system serves advantageously to control two devices using a single control system.

Abstract: The stator includes a casing and at least one stage of variable-pitch stator vanes. The vanes are moved by an actuator ring outside the casing and are carried thereby. The ring is connected by links to the vanes in order to actuate them simultaneously. The casing includes a stationary coaxial rail projecting from the outside surface of the casing and at least three circumferentially spaced-apart groups of wheels are constrained to move along the rail. Each group of wheels is coupled to the ring by a radial guidance arrangement. Each group of wheels includes at least two wheels engaged with the rail, and each wheel being mounted to rotate on a radially-oriented pin, said pin being mounted directly on said ring.

Abstract: A controllable variable length link device is disclosed. The device includes a first half-link having a first end connected to a driving system and a second end, a second half-link having a first end connected to a driven system and a second end, a rotary displacement member including a rotator shaft and a rotary head cooperating with the second ends of the half-links to bring about opposite movement of the half-links, a bearing unit in which the rotator shaft is mounted, respective guiding units which guide the two half-links in translation in at least two parallel directions, the guiding units being mechanically connected to the bearing means; and a driving unit which drives the shaft in rotation in both directions in accordance with a predetermined relationship.

Abstract: Controllable pitch blade non-ducted propeller for a jet engine, comprising a rotor member comprising radial housing for mounting blade support plates, each plate being attached in a ring centered and guided in rotation in a housing of the rotor member and comprising external toothing engaged and locked in internal toothing of the ring, to withstand the centrifugal forces to which the propeller blades are subjected in operation.

Abstract: The assembly comprises a fixed fork (10) of which the lugs (22, 30) support a rod (60) onto which a spherical ball is slipped (46) about which a cage (44) and a support (42), of the part which is mobile in rotation, swivel. The maintaining of the axial and angular positions of the spherical ball (46) in the fork is ensured, in particular, by a tight fit (A3) which replaces conventional screw and nut systems positioned at the end of the rod and which project disadvantageously. According to the invention, a pair of planar facets which are opposing and in abutment (including 23) carry out a blocking of one of the assembly pieces in rotation. Application to bell cranks for the transmission of movement, in particular in aircraft engines.

Abstract: Member for the guidance of a movable piece, including at least one surface in friction and sliding contact with a complementary surface of the movable piece, including several separate ceramic elements carried by a support having resilience characteristics, and for example, made of an elastomer.

Abstract: A bushing for a variable-pitch vane pivot in a turbomachine, the bushing being for mounting in a recess in a ring of the turbomachine, the recess being of a shape that is substantially complementary to the shape of the bushing, the bushing comprising a body that is substantially tubular having a longitudinal axis, and at least three branches extending radially outwards relative to the longitudinal axis of the tubular body, and axially over the full height of said tubular body, said branches being distributed in substantially equidistant manner around the circumference of the tubular body.

Abstract: Control device of variable pitch vanes in a turbomachine, including a ring (14) surrounding a casing (10) of the turbomachine and connected by links to the variable pitch vanes, and a jack (16) connected to the ring in order to displace it in rotation around the casing, the jack being mounted pivoting on the casing and its piston rod (18) being connected to the ring by a connecting rod (24), the piston and connecting rods being articulated on an axis (20) which is connected to the casing by guiding means (33) maintaining it at a substantially constant distance from the casing.

Abstract: A pivot bushing for a variable-pitch vane of a turbomachine, the bushing being for mounting in a recess in a ring of the turbomachine, the recess being of a shape that is substantially complementary to the shape of the bushing. The bushing comprises a substantially tubular body of longitudinal axis provided at one end with a first conical collar and at an opposite end with a second conical collar, the conical surfaces defined by the first and second collars being disposed facing each other.

Abstract: Assembling a plurality of parts together in a manner that enables a device of complex shape to be reconstituted. At least one of the parts includes two ribs in a chevron configuration and at least one other part includes two grooves in a chevron configuration, the ribs and the grooves being complementary in shape and of corresponding dimensions.

Abstract: A turbomachine including a variable-pitch stator vane stage. A control ring that is coaxial around the casing comprises two segments that are assembled together by side connection straps fastened on either side of the segments with mutual insetting and in the vicinity of the ends of the segments.

Abstract: The assembly comprises a fixed fork (10) of which the lugs (22, 30) support a rod (60) onto which a spherical ball is slipped (46) about which a cage (44) and a support (42), of the part which is mobile in rotation, swivel. The maintaining of the axial and angular positions of the spherical ball (46) in the fork is ensured, in particular, by a tight fit (A3) which replaces conventional screw and nut systems positioned at the end of the rod and which project disadvantageously. According to the invention, a pair of planar facets which are opposing and in abutment (including 23) carry out a blocking of one of the assembly pieces in rotation. Application to bell cranks for the transmission of movement, in particular in aircraft engines.

Abstract: A variable pitch stator vane stage, said vanes being moved by an automatically-centered rotary actuator ring. The casing carries a stationary coaxial annular rail projecting from its outside surface, and circumferentially spaced apart moving equipments are provided that are constrained to move along said rail, each moving equipment being coupled to the actuator ring via a radial guide arrangement.