A turbine rotor includes a disc with cavities, a plurality of blades, each with a root received in one of the cavities, and an axial retention system including a first series and a second series of strips circumferentially distributed around an axis of the rotor, the first and the second series being axially superimposed and arranged such that at least two strips circumferentially adjacent to the first series are axially superimposed on a strip of the second series and each strip of the first and second series is arranged opposite a cavity of the disc so as to axially block the root of a blade.

A turbine rotor includes a disc with cavities, a plurality of blades, each with a root received in one of the cavities, and an axial retention system including a first series and a second series of strips circumferentially distributed around an axis of the rotor, the first and the second series being axially superimposed and arranged such that at least two strips circumferentially adjacent to the first series are axially superimposed on a strip of the second series and each strip of the first and second series is arranged opposite a cavity of the disc so as to axially block the root of a blade.

A turbomachine having an engine centerline and a first rotor. The first rotor having a first annular drum and being connected to a first plurality of blades. At least one blade of the first plurality of blades having a blade root, a blade tip, a first arm, a second arm and a first seal. The first arm extending from the blade root and having a radial retention hook. The second arm extending from the blade tip.

The present invention relates to a fan rotor with variable pitch blades, comprising a rotor disc, equipped at its periphery with a plurality of rotary fasteners (16), each fastener (16) comprising a cell (17) for receiving the root (150) of a blade (15). This rotor is characterised in that an elongated wedge (2) and a prestressing rod (3) with at least one cam (33) are also arranged in each cell (17), the bottom of the cell (17) comprising as many retraction cavities (173) as the rod (3) comprises cams (33), in that the prestressing rod (3) is interposed between the wedge (2) and the bottom (171) of the cell (17), so that said cam (33) is facing a corresponding retraction cavity (173) and in that the prestressing rod (3) can rotate about its longitudinal axis (X2-X′2), between a rest position, in which the cam (33) is housed in the retraction cavity (173), and an armed position, in which the cam (33) exerts a radial pressure on the central region (22) of the wedge (2) so as to move the wedge (2) towards the blade root (150).

The present invention relates to a fan rotor with variable pitch blades, comprising a rotor disc, equipped at its periphery with a plurality of rotary fasteners (16), each fastener (16) comprising a cell (17) for receiving the root (150) of a blade (15). This rotor is characterised in that an elongated wedge (2) and a prestressing rod (3) with at least one cam (33) are also arranged in each cell (17), the bottom of the cell (17) comprising as many retraction cavities (173) as the rod (3) comprises cams (33), in that the prestressing rod (3) is interposed between the wedge (2) and the bottom (171) of the cell (17), so that said cam (33) is facing a corresponding retraction cavity (173) and in that the prestressing rod (3) can rotate about its longitudinal axis (X2-X′2), between a rest position, in which the cam (33) is housed in the retraction cavity (173), and an armed position, in which the cam (33) exerts a radial pressure on the central region (22) of the wedge (2) so as to move the wedge (2) towards the blade root (150).

A fan disc is provided for supporting fan blades of a gas turbine engine. The fan disc has a disc body having axially extending slots for receiving, in use, dovetail root fixings of a circumferential row of fan blades. The fan disc further has an annular drive arm which extends radially inwardly from a forward portion of the disc body to a connector for engaging, in use, with a corresponding connector portion of a drive shaft of the engine. The fan disc further has a hoop stiffening ring which is removably mounted to a rear portion of the disc body, the stiffening ring being axially spaced from the drive arm to increase the torsional stiffness of the fan disc.

A workpiece clamp device with single side is disclosed. When a bolt is screwed in relative to a base plane, an elastic member is compressed by a first and a second stop portions and a second clamp surface of a driving block is limited by a second wall surface. A first inclined surface is pushed leftward by a second inclined surface so that a tool is clamped by the first clamp surface and a first wall surface. When the bolt is screwed out relative to the base plane, the elastic member is reset due to the compression of the first and the second stop portions. Since the second clamp surface is limited by a second wall surface, the first inclined surface is pushed rightward by the second inclined surface to move the driving block upward so that the force for clamping the tool is released and the tool is disassembled.

A workpiece clamp device with single side is disclosed. When a bolt is screwed in relative to a base plane, an elastic member is compressed by a first and a second stop portions and a second clamp surface of a driving block is limited by a second wall surface. A first inclined surface is pushed leftward by a second inclined surface so that a tool is clamped by the first clamp surface and a first wall surface. When the bolt is screwed out relative to the base plane, the elastic member is reset due to the compression of the first and the second stop portions. Since the second clamp surface is limited by a second wall surface, the first inclined surface is pushed rightward by the second inclined surface to move the driving block upward so that the force for clamping the tool is released and the tool is disassembled.

A rotor of a steam turbine includes a plurality of rotor blades attached to a disk portion and a key configured to restrict movement of each of the plurality of rotor blades in an axial direction. The disk portion includes a blade embedding groove and a circumferential groove. The plurality of rotor blades include a first rotor blade and a second rotor blade adjacent to the first rotor blade on one side in a circumferential direction. A platform of the first rotor blade includes an access groove communicating with the circumferential groove, and a platform of the second rotor blade includes a second side surface facing a first side surface in the circumferential direction and a key accommodating groove communicating with the access groove in the circumferential direction. A key is arranged in the circumferential groove and the key accommodating groove.

A rotor of a steam turbine includes a plurality of rotor blades attached to a disk portion and a key configured to restrict movement of each of the plurality of rotor blades in an axial direction. The disk portion includes a blade embedding groove and a circumferential groove. The plurality of rotor blades include a first rotor blade and a second rotor blade adjacent to the first rotor blade on one side in a circumferential direction. A platform of the first rotor blade includes an access groove communicating with the circumferential groove, and a platform of the second rotor blade includes a second side surface facing a first side surface in the circumferential direction and a key accommodating groove communicating with the access groove in the circumferential direction. A key is arranged in the circumferential groove and the key accommodating groove.