According to one or more embodiments, a cover plate for a gas turbine engine is provided. The cover plate includes a cover plate body that extends from a disc blade attachment radially along an outside surface of a disc web to a disc bore of a disc creating a cavity between the cover plate body and the disc web of the disc, and an attachment protrusion extending from the inner most end of the cover plate body toward the disc bore, and wherein the attachment protrusion is configured to engage with a retention ring.

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 wherein the groove extends axially to an 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.

A gas turbine engine bladed rotor arrangement comprises a rotor, a plurality of rotor blades and a plurality of lock plates. The rotor blades are mounted in circumferentially spaced axially extending slots in the periphery of the rotor. A plurality of lock plates are arranged at a first axial end of the rotor. The radially outer ends of the lock plates engage corresponding grooves defined by radially inwardly extending flanges on the platforms of the rotor blades. The radially inner ends of the lock plates also engage a circumferentially extending groove. The radially outer end of at least one lock plate at the first axial end of the rotor has at least one projection extending axially away from the rotor. Each projection locates against a corresponding anti-rotation feature.

A rotor disc has diametrically outer surfaces, a diametrically inner surface, a plurality of blade root grooves recessed diametrically inward from the diametrically outer surfaces and aligned in a circumferential direction, and a plurality of hole groups formed in each of the plurality of blade root grooves and aligned in the circumferential direction. Each of the plurality of hole groups has a hole including a cooling orifice penetrating from the diametrically inner surface through to the diametrically outer surface. The width of each of the plurality of hole groups in the circumferential direction is greater than the width of each of the plurality of hole groups in an axial direction and smaller than a minimum gap among gaps between the plurality of hole groups in the circumferential direction.

A rotor has formed therein a groove with which a moving blade including a dovetail portion and a platform portion connecting the dovetail portion and a blade portion engages. The groove opens in a surface intersecting the axis of rotation of the rotor, and includes a contacting portion extending obliquely with respect to the axis of rotation and coming into contact with the dovetail portion, a bottom portion of an end portion on the radially inner side of the rotor, a joining portion between the contacting portion and the bottom portion, a platform facing portion facing the platform portion, and a chamfered portion formed on an end surface in the groove-extending direction. The chamfered dimension of the joining portion is greater on the side with an acute angle between the groove and the end surface than on the side with an obtuse angle between the groove and the end surface.

A gas turbine engine includes a shaft and a heatshield that circumscribes the shaft. The heatshield defines a cylindrical body that has radially inner and outer sides and extends between first and second axial ends. The heatshield is exclusively supported on the shaft at the first and second axial ends. The heatshield includes at least one seal member on the radially outer side. A damper member is disposed at the radially inner side of the heatshield for attenuating vibration of the heatshield.

A sealing flange sector for a turbomachine rotor disc includes a radially outer part which is configured to bear at least partly against blades of the turbomachine rotor disc to ensure sealing between the blades and a radially inner part configured to bear on an annular strip mounted on a face of the turbomachine rotor disc, the radially inner part having a first groove disposed radially outwardly of a second groove. The first groove includes at least one foolproofing element.

A sealing washer for use in a rotor of a gas turbine, sealing being brought about on one side of the sealing washer by an approximately radially oriented bearing face and on the other side by way of a supporting face which is oriented in an inclined manner with respect to the rotor axis. The sealing washer is of split configuration and has at least one washer segment with a circumferential washer section. At the dividing point, a pressing section and a triangular section overlap along a dividing face. Here, the dividing face intersects the bearing face and makes sealing both with the pressing section and with the triangular section possible. In order to also make sealing on the supporting face with the pressing section and the triangular section possible, the triangular section is reduced to at most 0.3 times the cross-sectional area of the washer section.

A rotor assembly is provided for a piece of rotational equipment. This rotor assembly includes a rotor disk, a rotor blade and a seal element. The rotor disk is configured to rotate about a rotational axis. The rotor disk extends axially along the rotational axis to a rotor disk end face. The rotor blade includes an attachment. The attachment attaches the rotor blade to the rotor disk. The seal element is configured to seal a gap between the rotor disk and the attachment. The seal element has a longitudinal centerline that extends along an interface between the rotor disk and the attachment at the rotor disk end face.

A method for disassembling/assembling a gas turbine including a seal plate disposed on a first side of a rotor disc in an axial direction of the rotor disc, and a seal plate restraint part for restricting movement of the seal plate in a radial direction of the rotor disc. The method includes a seal-plate-restraint-state switching step of operating the seal plate restraint part from a second side in the axial direction via a clearance between a platform of a blade and a region of an outer peripheral surface of the rotor disc except a blade groove for receiving the blade to switch between a seal plate non-restraint state where the seal plate restraint part does not restrict movement of the seal plate in the radial direction and a seal plate restraint state where at least a part of the seal plate restraint part protrudes in the axial direction.