Abstract: Spacers interposed between blades attached to the disk of a rotor having slots and bottoms of the slots are disclosed. Each spacer is made of an elastically deformable material and at least one longitudinal segment of the spacer presents a transverse profile of arcuate shape to define two lateral contact zones.

Abstract: Wedging blades attached to the disk of a rotor having slots. According to the invention, each wedging spacer is made of an elastically deformable material and at least one longitudinal segment of the spacer presents a transverse profile of arcuate shape to define two lateral contact zones.

Abstract: Spacers interposed between blades attached to the disk of a rotor having slots and bottoms of the slots are disclosed. Each spacer is made of an elastically deformable material and at least one longitudinal segment of the spacer presents a transverse profile of arcuate shape to define two lateral contact zones.

Abstract: An aircraft turbomachine fan is disclosed. The fan includes a turbomachine inlet cone that has an exterior surface intended to be closely followed by a flow section of the turbomachine, and an annular balancing flange that rotates as one with a fan disk about an axis of rotation and is equipped with a plurality of weight-fixing holes. The fan also includes one or more balancing weights mounted fixedly on the annular balancing flange. The annular balancing flange is positioned inside the inlet cone in such a way that its weight-fixing holes are isolated from the flow section. The flange is produced as a single piece with a fan blade retaining ring.

Abstract: A turbomachine fan including blades and inter-blade platforms having radial flanges fastened to flanges of a rotor disk by threaded rods inserted into bushes mounted in orifices in the flanges of the platforms is disclosed. Each bush includes at least one deformable part interposed transversely between the threaded rod and an edge of the orifice in which the bush is mounted. The deformable part is intended to allow the platform to pivot in the event of an impact of a blade against the platform and to absorb some of the energy of the impact.

Abstract: The rotor disk carries an axial retention plate facing slots having blade roots received therein, the disk and the plate are shaped so as to define outer circumferential interlock and inner circumferential interlock.

Abstract: A fan rotor is provided. Each blade of the fan rotor is held by a bolt. Each blade includes a blade root engaged in a groove of the rim and held by a bolt. The bolt includes a concave plate with its curve directed upstream.

Abstract: A fan rotor is provided. Each blade of the fan rotor is held by a bolt. Each blade includes a blade root engaged in a groove of the rim and held by a bolt. The bolt includes a concave plate with its curve directed upstream.

Abstract: The present invention relates to an aircraft turbomachine fan (1) comprising a turbomachine inlet cone (20) that has an exterior surface (19) intended to be closely followed by a flow section (22) of the turbomachine, an annular balancing flange (34) that rotates as one with a fan disk (4) about an axis of rotation (2) and is equipped with a plurality of weight-fixing holes (24), the fan also comprising one or more balancing weights (26) mounted fixedly on said annular balancing flange. Furthermore, the annular balancing flange (34) is positioned inside the inlet cone (20) in such a way that its weight-fixing holes (24) are isolated from the flow section (22). According to the invention, the flange (34) is produced as a single piece with a fan blade retaining ring (16).

Abstract: Wedging blades attached to the disk of a rotor having slots. According to the invention, each wedging spacer is made of an elastically deformable material and at least one longitudinal segment of the spacer presents a transverse profile of arcuate shape to define two lateral contact zones.

Abstract: A turbomachine fan (10) comprising blades (12) and inter-blade platforms (18) having radial flanges (20) fastened to flanges (22) of a rotor disk (16) by means of threaded rods inserted into bushes (26) mounted in orifices in the flanges of the platforms (18), wherein each bush (26) comprises at least one deformable part (30) interposed transversely between the threaded rod (24) and an edge of the orifice in which the bush (26) is mounted, this deformable part (30) being intended to allow the platform (18) to pivot in the event of an impact of a blade (12) against the platform (18) and to absorb some of the energy of the impact.

Abstract: The rotor disk carries an axial retention plate facing slots having blade roots received therein, the disk and the plate are shaped so as to define outer circumferential interlock and inner circumferential interlock.

Abstract: The invention relates to hammer-fastener blade-locking device affixing the blades in the channel (2) of a turbojet-engine rotor disk (1) and comprising a case (15) of which the cross-section matches that of the channel (2), further a locking element (16) mounted in radially displaceable manner in a traverse orifice in the case (15) and receivable in part in a lock housing (9a, 9b), and a drive bolt (17) acting on the locking element (16). The locking element (16) comprises stops (32a) sliding in windows (22a) of the case (15). The bolthead (4) is large and is radially affixed between the bottom of the channel (2) and the base (20) of the case (15).

Abstract: The invention relates to hammer-fastener blade-locking device affixing the blades in the channel (2) of a turbojet-engine rotor disk (1) and comprising a case (15) of which the cross-section matches that of the channel (2), further a locking element (16) mounted in radially displaceable manner in a traverse orifice in the case (15) and receivable in part in a lock housing (9a, 9b), and a drive bolt (17) acting on the locking element (16). The locking element (16) comprises stops (32a) sliding in windows (22a) of the case (15). The bolthead (4) is large and is radially affixed between the bottom of the channel (2) and the base (20) of the case (15).