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 wheel disc arrangement having a wheel disc, having multiple vane devices which are fastened along an outer circumference of the wheel disc, having at least one sealing plate received between the wheel disc and the vane devices so as to be displaceable in a circumferential direction, and having at least one securing device designed so as to secure the sealing plate against a displacement in the circumferential direction, wherein the securing device has a bolt, which extends through a passage opening provided in the sealing plate, and a recess, which is provided on the wheel disc or on a vane device, which recess receives the free end of the bolt and the wall of which recess limits a movement of the bolt in the circumferential direction, wherein the bolt is, in an axial direction, secured on the sealing plate against undesired release by way of a detent connection.

A retaining ring for a turbomachine disk and coverplate assembly includes a ring body defining a coverplate interface side and an opposed disk lip interface side. A flow feature is defined by the ring body on the coverplate interface side to allow airflow between the turbomachine disk coverplate and the ring body such that a pocket defined between the coverplate and the turbomachine disk is in fluid communication with a conditioning flow pathway through the retaining ring.

A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades.

The invention relates to a rotary assembly for a turbomachine, comprising: a disk (16) having an external periphery exhibiting an alternation of slots (22) and of teeth (20), vanes (14) extending radially from the disk (16), the roots (24) of which are engaged axially and retained radially in the slots (22) of the disk, upstream and/or downstream of the disk, an annular sealing flange (52) of cavities (36) formed radially between, respectively, the roots of the vanes and the bottoms of the slots of the disk, said flange comprising an external part (56) arranged axially facing the upstream and/or downstream ends, respectively, of the teeth of the disk and of the roots of the vanes.
According to the invention, the assembly further comprises an intermediate ring (66) which is arranged axially between the flange (52) and the teeth (20) of the disk, and also comprises a seal (70) which is arranged axially between, on the one side, the intermediate ring (6) and, on another side, the teeth (20) of the disk and the vane roots (24).

A rotor for a turbine engine includes a disk having cavities called primary cavities at its periphery; a plurality of blades each having a root of which the lower part is composed of a bulb locked axially in the primary cavities; a plurality of added platforms, each being arranged between two consecutive blades, wherein the platforms have: a substantially straight plate and a bulb extending radially under the plate, the bulb being locked axially in the secondary cavities arranged at the periphery of the disk, the secondary cavities being positioned between two consecutive primary cavities; a spoiler extending in the axial direction, the spoiler forming an annular sector facing at least two consecutive blades,

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 rotor of a multi-staged axial compressor which extends along an axis of rotation. The rotor has a shaft which has rotor blade slots. Rotor blades of the rotor are arranged next to one another in the circumferential direction and are each secured to the rotor blade slots by a blade root to form a respective rotor blade stage. At least two rotor blade stages are provided in axial succession and an interspace slot, extending in the circumferential direction, is provided in the shaft axially between the two rotor blade stages. The rotor blade slots open into the interspace slots and blade roots of the rotor blades are insertable radially into the interspace slots and can be pushed into the rotor blade slots. The rotor has an interspace cover which covers the interspace slots, wherein the interspace cover is designed segmented into interspace cover segments in the circumferential direction.

A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a scallop formed along at least one surface of the groove, wherein the scallop is configured to provide a flow path, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

A disc of a gas turbine engine system is provided. The disc includes a disc bore including, an interstage coupling disposed on an axially extending surface at a peripheral edge of the disc bore that includes a protrusion that extends axially beyond an outer surface of the disc bore, and a groove formed on the axially extending surface of the disc bore wherein an aft surface of the groove is also a forward surface of the interstage coupling, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to the aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.