A rotor blade assembly group for an engine with at least one blade carrier having at least one rotor blade that is provided with multiple rotor blades along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blade, the carrier section comprises a connection area at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the stiffening element is arranged at a first face side of the blade carrier, and the second stiffening element is arranged at a second face side that is facing away from the first face side. The blade carrier is formed in a ring-segment-shaped or disc-segment-shaped-manner.

A rotating blade assembly for a turbine engine having a drive shaft, the rotating blade assembly comprising a disc, at least one blade assembly, and a retainer. The disc being operably coupled to the drive shaft and including a seat having at least a portion of a first through hole. The at least one blade assembly having an upper platform, a lower platform, a dovetail extending from the lower platform, and a blade extending between the upper platform and the lower platform. The retainer assembly securing the disc to the at least one blade assembly and comprising a hollow tubular element, a pin, and a fastener.

A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.

A method for building centrifugal radial stages of turbines, in which the first and the second end of each blade (4) are connected to respective two support rings (2, 3) joining, by means of laser welding, at least a first semi-portion (10) belonging to the respective end of the blade (4) to a respective second semi-portion (10) belonging to the respective support ring (2, 3) so as to form a resilient yielding connecting portion (10, 15) along a radial direction, and providing at least a stop portion (11) belonging to the end of the blade (4) facing, along the radial direction, at least a stop element (14) of the respective support ring (2, 3). The resilient yielding connecting portion (10, 15) enables the stop portion (11) to enter into contact with the stop element (14) when the stage (1) is subjected to the functioning loads of the turbine.

An OGV wheel comprising guide vanes made of polymer matrix composite material reinforced by fibers, each having a vane root and a vane tip, the vane roots being fastened on a hub of the wheel by first connection means and the vane tip being fastened on an outer shroud of the wheel by second connection means, the first connection means including a bearing plane secured to the hub and a first backing plate for securing to the hub, the vane roots being sandwiched between the bearing plane and the first backing plate, and the second connection means including a second backing plate for securing to the shroud, the vane tip being sandwiched between the shroud and the second backing plate.

A turbine or compressor stage for a turbine engine is provided. The stage includes a disk including a metal material configured to be coupled to a shaft of the turbine engine, an airfoil including a ceramic matrix composite material, and an interface part that is distinct from the airfoil and that is configured to be fastened to the disk and to fasten the airfoil. The interface part includes a ceramic or a ceramic matrix composite material.

A fan is provided. The fan may comprise a fan blade and a blade platform coupled to the fan blade. The blade platform may be a thermoplastic. A fan blade platform is also provided. The fan blade platform may comprise a first platform half comprising a slot at a first end of the first platform half and a first receiving member at a second end of the first platform half opposite the first end of the first platform half. A second platform half may comprise a hook. The second platform half may also include a second receiving member at a second end of the second platform half opposite the first end of the second platform half with the hook configured to interface with the slot. A pin may be configured to pass through the first receiving member and the second receiving member.

A rotor, in particular a gas turbine rotor, having multiple rotor discs, each of which has an axial through-opening, and the rotor discs are axially clamped by at least one tie rod extending through the through-openings and are combined so as to form at least one rotor disc unit. At least one support ring which surrounds the tie rod and is in engagement with a paired rotor disc rests against the outer diameter of the tie rod, and the tie rod is supported against the rotor disc by the support ring. In order to axially secure the at least one support ring, at least one securing ring is provided which is secured to the paired rotor disc by a rotational lock and which holds the support ring against the rotor disc. The securing ring is prevented from unscrewing by a securing plate.

An integrally bladed rotor for a gas turbine engine includes a hub, a plurality of blades radially extending from the hub and being integrally formed therewith. The hub having a rim from which the blades project and a pair of axially opposed split hub members extending at least radially inward from the rim. Each of the split hub members has a radially outer flex arm portion extending form the hub and a radially inner moment flange portion. At least one moment inducing element separately formed from the hub is mounted axially between the opposed split hub members and acts on the moment flange portions of the opposed split hub members to generate an inward bending moment on the flex arm portions of the opposed split hub members during rotation of the rotor, thereby deflecting the rim and the blades of the rotor radially inwardly.

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.