Abstract: A turbine engine including a stator including variable-pitch vanes that are controlled stage by stage. An actuator ring connected by crank-arms to the variable-pitch vanes is coupled to at least one adjacent specific drive unit in a general form of an actuator.

Abstract: An unducted fan of variable-pitch blades including roots engaged from outside in respective radial housings of an annular rotor element and guided to turn about their respective axes by pairs of rolling bearings, one of which is carried by an annular segment of a cylindrical skirt mounted in a groove of the annular body and by a locknut screwed onto the cylindrical skit. The bearing is covered externally by a ring including outer dog-clutch teeth co-operating with inner dog-clutch teeth of the housing to hold the ring axially in the housing. A blocking mechanism is engaged between the teeth of the housing and the teeth of the ring preventing the ring from turning and preventing the ring from being withdrawn axially from the housing.

Abstract: A variable pitch blade propeller hub for a turbomachine with a longitudinal axis includes a polygonal ring supporting the blades, concentric with the longitudinal axis and including two spaced parallel annular end flanges between which are diametrically fastened, by root areas arising from the annular flanges, collars with cylindrical radial housings to receive the blades. The collars are equi-angularly distributed at the lateral periphery of the polygonal ring and separated from each other by intermediate areas with through-openings. The also includes connectors connecting the polygonal ring to a turbine rotor element of the turbomachine. The intermediate areas defined between two concentric collars and the annular end flanges include elements for reinforcing the collars that are arranged radially and/or tangentially and fastened at least to the lateral walls of two consecutive collars.

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 turbine engine compressor, including a first housing for supporting injectors, a second housing arranged around the first housing while forming with the first housing an annular space therewith, and a plurality of air injectors each mounted in recesses. Each air injector includes at least one inner air injection channel which leads, on one side, into an outflow jet of the gas stream and, on the other side, into the space formed between the recesses, and, at an upstream end, an upstream rim having an inner surface radially bearing against an upstream rim of the corresponding recess of the first housing and an outer surface radially bearing against an inner surface of the second housing. A mechanism clamping the upstream rim of the air injectors between the housings enables the air injectors to be held in position in the recesses of the first housing.

Abstract: An assembly in a turbine engine for controlling plural toothed pivotally-mounted blades arranged in azimuth around the axis of the turbine engine and including an actuator ring controlling a position of the blades. Racks mounted on the ring present corresponding sets of teeth meshing with the set of teeth of a respective one of the blades to place it in a selected angular position, and they are held in the radial direction by radial positioning mechanism fastened to the blade. Each rack is mounted on the ring by plural guides spaced apart circumferentially around the ring, that connect together movements of the rack and of the ring in the circumferential direction, and that are configured to slide relative to the ring, for each guide in its own radial direction, and relative to the rack in a direction of movement that is substantially radial and specific to the rack.

Abstract: A hub for a propeller having variable pitch blades for a turbine engine, for example for a propfan turbine engine. The propeller hub includes: a polygonal ring having substantially radial cylindrical housings distributed about a central axis of the ring for receiving the blades; a rotor element for the turbine of the turbine engine; a supporting flange attached to the ring so as to connect the ring to the rotor element; and a plurality of backup retaining members linked to the rotor element, and each of which includes at least one bearing surface opposite an outer surface of the ring with a radial spacing.

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 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 device for controlling variable-pitch blades in a turbomachine compressor, including at least one control ring surrounding an external casing of the compressor, and a control shaft connected to the ring and to the rod of an actuator, the body of which is mounted such that it can pivot about an axle borne by a support mechanism of the control shaft so as to guarantee a precise relative positioning of the axis of pivoting of the actuator with respect to the control shaft.

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: An unducted fan of variable-pitch blades including roots engaged from outside in respective radial housings of an annular rotor element and guided to turn about their respective axes by pairs of rolling bearings, one of which is carried by an annular segment of a cylindrical skirt mounted in a groove of the annular body and by a locknut screwed onto the cylindrical skit. The bearing is covered externally by a ring including outer dog-clutch teeth co-operating with inner dog-clutch teeth of the housing to hold the ring axially in the housing. A blocking mechanism is engaged between the teeth of the housing and the teeth of the ring preventing the ring from turning and preventing the ring from being withdrawn axially from the housing.

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: A turbine engine including a stator including variable-pitch vanes that are controlled stage by stage. An actuator ring connected by crank-arms to the variable-pitch vanes is coupled to at least one adjacent specific drive unit in a general form of an actuator.

Abstract: An assembly in a turbine engine for controlling plural toothed pivotally-mounted blades arranged in azimuth around the axis of the turbine engine and including an actuator ring controlling a position of the blades. Racks mounted on the ring present corresponding sets of teeth meshing with the set of teeth of a respective one of the blades to place it in a selected angular position, and they are held in the radial direction by radial positioning mechanism fastened to the blade. Each rack is mounted on the ring by plural guides spaced apart circumferentially around the ring, that connect together movements of the rack and of the ring in the circumferential direction, and that are configured to slide relative to the ring, for each guide in its own radial direction, and relative to the rack in a direction of movement that is substantially radial and specific to the rack.

Abstract: A variable pitch blade propeller hub for a turbomachine with a longitudinal axis includes a polygonal ring supporting the blades, concentric with the longitudinal axis and including two spaced parallel annular end flanges between which are diametrically fastened, by root areas arising from the annular flanges, collars with cylindrical radial housings to receive the blades. The collars are equi-angularly distributed at the lateral periphery of the polygonal ring and separated from each other by intermediate areas with through-openings. The also includes connectors connecting the polygonal ring to a turbine rotor element of the turbomachine. The intermediate areas defined between two concentric collars and the annular end flanges include elements for reinforcing the collars that are arranged radially and/or tangentially and fastened at least to the lateral walls of two consecutive collars.

Abstract: A turbine engine compressor, including a first housing for supporting injectors, a second housing arranged around the first housing while forming with the first housing an annular space therewith, and a plurality of air injectors each mounted in recesses. Each air injector includes at least one inner air injection channel which leads, on one side, into an outflow jet of the gas stream and, on the other side, into the space formed between the recesses, and, at an upstream end, an upstream rim having an inner surface radially bearing against an upstream rim of the corresponding recess of the first housing and an outer surface radially bearing against an inner surface of the second housing. A mechanism clamping the upstream rim of the air injectors between the housings enables the air injectors to be held in position in the recesses of the first housing.

Abstract: A turbomachine including a variable-pitch stator vane stage is disclosed. A control ring that is coaxial around the casing includes 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: A hub for a propeller having variable pitch blades for a turbine engine, for example for a propfan turbine engine. The propeller hub includes: a polygonal ring having substantially radial cylindrical housings distributed about a central axis of the ring for receiving the blades; a rotor element for the turbine of the turbine engine; a supporting flange attached to the ring so as to connect the ring to the rotor element; and a plurality of backup retaining members linked to the rotor element, and each of which includes at least one bearing surface opposite an outer surface of the ring with a radial spacing.