Various aspects include a turbomachine bucket, corresponding shim and related turbine rotor. In some cases, a steam turbine bucket includes: a blade having a first end, and a second end opposite the first end; a tip at the first end of the blade; and a base at the second end, the base including a dovetail for complementing a corresponding dovetail slot in a steam turbine rotor, the dovetail having: a body; a plurality of projections extending from the body in opposing directions for complementing a plurality of recesses in the corresponding dovetail slot; and a shim locking slot extending through the body along the opposing directions, the shim locking slot being open at a bottom surface of the body and sized to engage a shim.

A gas turbine engine and a retaining ring are disclosed. The gas turbine engine includes a rotating disc assembly, including a rotating disc, a cover plate, and a retaining ring disposed between the rotating disc and the cover plate, wherein the retaining ring axially retains the rotating disc and the cover plate, the retaining ring including a rotating disc face to interface with the rotating disc; a cover plate face to interface with the cover plate; and an end gap portion defining an end gap, wherein at least one of the rotating disc face, the cover plate face, and the end gap portion includes a stress reducing feature.

The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream at the radially inner ends of the leading edges of the fan blades, divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.

A load absorbing system that may include a rotor blade retention system is provided. The load absorbing system may include a block, a first retainer plate, and a deformable core. The block may be selectively positioned alongside a dovetail groove. The block may have a first face directed away from the blade root and an axially-spaced second face directed toward the blade root. The first retainer plate may be attached to the second face of the block and axially positioned between the block and the axially-directed surface of the blade root. The deformable core may be positioned between the block and the first retainer plate.

A fan for gas turbine engine that includes hub and annular array of fan blades mounted to hub and extending radially outwardly from hub, each fan blade includes blade root. The hub includes a plurality of hub grooves having shape complimentary to shape of blade root and each hub groove receives and radially retains one blade root. A slot is provided on the suction side and on the pressure side of each blade root. Plurality of keys is provided, each key engages with slots in one blade root and with corresponding hub groove so as to axially retain fan blade. The key includes two arms and joining member, two arms are received in slots provided on blade root and joining member extends between the arms. Interface is defined between key arms and slots in blade root, and greater or equal percentage of interface is curved than is planar.

A vane ring assembly capable of preventing vibration of a vane, and wear damage caused thereby, by fixing the vane to a ring through a strong contact therebetween. The vane ring assembly includes a retaining ring having an inner peripheral surface in which a dovetail groove is formed; a vane including a dovetail inserted into the dovetail groove and an airfoil protruding from the dovetail in a radial direction of the retaining ring; and a locking key disposed between the dovetail and the dovetail groove and configured to press the dovetail into the dovetail groove. A method of assembling the vane ring assembly includes steps of inserting the dovetail into the dovetail groove; and forcibly pushing the locking key between the dovetail groove and the bottom surface of the dovetail.

The present disclosure concerns a fan disc assembly, and in particular a fan disc assembly for a gas turbine engine. Example embodiments disclosed include a fan disc assembly for a gas turbine engine, comprising: a fan disc with a central bore comprising a bore forward section, a bore aft section and a bore spline between the bore forward and aft sections; a shaft mounted within the central bore of the fan disc, the shaft comprising a shaft forward section connected to the bore forward section, a shaft aft section connected to the bore aft section and a shaft spline between the forward and aft sections and mating with the bore spline, wherein an outer radial surface of the bore forward section is secured to an inner radial surface of the shaft forward section with a second interference fit.

A wheel disk assembly having a wheel disk, a plurality of blade devices fastened along an outer circumference of the wheel disk, a plurality of sealing plates accommodated between the wheel disk and the blade devices such that the sealing plates are moveable in the circumferential direction, and securing devices designed such that the securing devices secure the sealing plates against movement in the circumferential direction. Pins are provided as securing devices, which pins are detachably retained in bores arranged on the wheel disk and reach into recesses that are formed on surfaces of the sealing plates facing the wheel disk, wherein at least one of the pins, preferably all of the pins, are designed such that, in order to disengage a pin from the associated recess, the pin in question can be plunged further into the bore in a resilient manner.

A foil for a rotating blade of a turbomachine, configured to be mounted to a blade root of the rotating blade and including an overall U-shaped cross-section formed by two lateral legs connected through a lower surface, the lower surface covering a lower face of the blade root, the lateral legs each covering at least part of two lateral flanks of the blade root; and a blocking system for prohibiting at least some of relative movements between the blade root and the foil, the blocking system including at least one oblique tab, partially cut out of a lower surface of the foil and forming, with respect to the lower surface of the foil, a tilted plane protrusion able to be inserted into a housing formed in a lower face of the blade root.

A blade fastening assembly and a gas turbine including the same are proposed. The blade fastening assembly includes a fastening key having a threaded hole, a rotor disk including a disk slot into which a root member is inserted, the rotor disk having a first groove with a shape corresponding to a portion of the fastening key, a first portion of a second groove adjacent to the first groove, and a pin groove connected with the first groove, a platform having a second portion of the second groove formed in communication with the first portion of the second groove and the first groove and forming a shape corresponding to a remaining portion of the fastening key in a state of being inserted into the disk slot, and a fastening pin inserted into the threaded hole and the pin groove.