A blade and an assembly tool for assembling a blade set to a rotor disc. The blade has a root portion, an aerofoil and a shroud, the root portion has two lateral sides each defining at least one bearing surface and at least one end surface, the blade has a centre-of-resistance line which passes through the root portion and is generally parallel to a plane of at least one bearing surface, the centre-of-resistance line intersects the at least one end surface at an intersection point, the at least one end surface has an assembly feature having a contact surface arranged about the intersection point.

An adjustable blade root spring device for turbine blade fixation in turbomachinery. The device is designed to be placed in a space in a rotor disk cavity adjacent to a tip of a blade root, where the device applies a radial outward force on the turbine blade to fix the blade position in the rotor disk. The device includes a wave spring with integral end blocks which is compressed by a bolt and a coil spring. When the wave spring is compressed in length, it increases in height and makes contact with the rotor disk and the turbine blade. The force of the wave spring on the turbine blade can be adjusted via the bolt, and the coil spring provides an increased compliance range. The body of the device has an oblong cross-sectional shape, thereby preventing rotation of the device in the space between the blade and the disk.

A fan includes a rotor hub comprising a slot and a blade comprising an airfoil extending from a blade root in a first direction. The blade root is configured to be received in the slot. The fan also includes a deformable spacer situated between the rotor hub and the blade root in the slot, a first blade lock situated at a first side of the slot, and a second blade lock situated at a second side of the slot opposite the first side. At least one of the first and second blade locks includes a tab configured to extend between the blade root and the rotor hub and to compress the spacer such that the spacer exerts a force on the blade in the first direction. A method of assembling a fan and another example fan are also disclosed.

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 platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.

A compressor section includes a compressor disk having a slot receiving a blade with an airfoil extending from a platform and the compressor disk having an upstream end and a downstream end. A cover plate at one of the upstream end and the downstream end covers an area between the blade and the compressor disk across a circumference of the compressor disk. The cover plate covers an area between an inner peripheral surface of the platform to a radially innermost end of the slot in the disk. The compressor disk has hooks, and there is a retention ring mounted in a cavity between the hooks and the compressor disk. The cover plate is mounted between the retention ring and the compressor disk. The retention ring retains the cover plate against the compressor disk. A gas turbine engine is also disclosed.

The present invention relates to a turbine rotor of a turbine engine of an aircraft, the rotor comprising a rotor disc provided at its periphery with a plurality of cavities for receiving the root of a blade. This rotor is characterised in that each blade comprises a circumferential coupling rib, in that it comprises a plurality of platforms, which comprise a main wall that is extended at its two ends by an upstream radial wall and by a downstream radial wall, the two longitudinal edges of each platform comprising a groove for receiving part of said coupling rib of one of the two blades between which this platform is assembled, and in that the height of each upstream radial wall is such that said wall extends radially inwards beyond the bottom of the cavity, until it is in front of the upstream face of the rotor disc.

A blade arrangement is provided having a blade carrier and a retaining groove arranged therein, which retaining groove has projections extending along side walls thereof forming undercuts and into which a number of blades are inserted forming a blade ring of a turbomachine. Each blade has a blade root which engages into the undercuts, and each blade is pressed against the projections by an element arranged between a blade root underside and a groove base of the retaining groove. It is further provided that each element is of plate-like form and has, in the projection of the blade airfoil in the direction of the groove base, at least one bead, arranged beneath the blade airfoil, for imparting a pressing action, and in the longitudinal direction of the retaining groove, only part of the blade root which the element presses against is covered.

A securing plate assortment including multiple different securing plates, the securing plates having different geometric codings. A turbine and method is also disclosed.

A lock plate for preventing relative movement between a first component and an adjoining second component, comprises a first end, a second end, and a planar portion extending between the first end and the second end. The first end is configured to locate against one of the first component and the second component, while the second end is configured to locate against the other one of the first component and the second component. The planar portion comprises a first projection positioned substantially mid-way between the first end and the second end. The first projection protrudes from a plane defined by the planar portion and may readily be severed by a user to thereby separate the first and second component from one another.