A bladed rotor system for a turbomachine includes a circumferential row of blades mounted on a rotor disc, and includes a plurality of under-platform dampers. Each damper is located between adjacent blade platforms. The plurality of dampers includes a first set of dampers and a second set of dampers. The dampers of the first set are distinguished from the dampers of the second set by a cross-sectional material distribution in the damper that is unique to the respective set. Dampers of the first set and the second set are positioned alternately in a periodic fashion in a circumferential direction, to provide a frequency mistuning to stabilize flutter of the blades.

A bladed rotor system for a turbomachine includes a circumferential row of blades mounted on a rotor disc, and includes a plurality of under-platform dampers. Each damper is located between adjacent blade platforms. The plurality of dampers includes a first set of dampers and a second set of dampers. The dampers of the first set are distinguished from the dampers of the second set by a cross-sectional material distribution in the damper that is unique to the respective set. Dampers of the first set and the second set are positioned alternately in a periodic fashion in a circumferential direction, to provide a frequency mistuning to stabilize flutter of the blades.

A damper seat for a ring damper that redirects axial loads and is disposed within a gas turbine engine with at least one disk rotatable about a rotational axis and having a disk neutral axis extending radially from the rotational axis.

A damper seat for a ring damper that redirects axial loads and is disposed within a gas turbine engine with at least one disk rotatable about a rotational axis and having a disk neutral axis extending radially from the rotational axis.

The invention concerns a turbomachine rotor (1), characterised in that it comprises a threaded or tapped part (3, 6) and a damping nut (8) screwed onto the threaded or tapped part (3, 6) so as to allow the threads of the nut (8) and of the threaded or tapped part (3, 6) to rub against each other in the event of vibration of the rotor (1).

The invention concerns a turbomachine rotor (1), characterised in that it comprises a threaded or tapped part (3, 6) and a damping nut (8) screwed onto the threaded or tapped part (3, 6) so as to allow the threads of the nut (8) and of the threaded or tapped part (3, 6) to rub against each other in the event of vibration of the rotor (1).

A turbine wheel in a turbine engine is provided. The wheel includes a disk having a plurality of blades with roots that are axially engaged and radially retained in longitudinal slots in the outer periphery of the disk, the blades having platforms that extend circumferentially end to end and that are radially facing longitudinal teeth of the disk that define the slots. Protection members for protecting the flanks of the slots and made out of sheet metal are mounted on the teeth of the disk and held thereon by co-operating shapes, the protection members bear radially against the platforms of the blades in order to oppose circumferential tilting of the blades, and at least partially close the radial gaps between the teeth and the platforms of the blades.

A turbine wheel in a turbine engine is provided. The wheel includes a disk having a plurality of blades with roots that are axially engaged and radially retained in longitudinal slots in the outer periphery of the disk, the blades having platforms that extend circumferentially end to end and that are radially facing longitudinal teeth of the disk that define the slots. Protection members for protecting the flanks of the slots and made out of sheet metal are mounted on the teeth of the disk and held thereon by co-operating shapes, the protection members bear radially against the platforms of the blades in order to oppose circumferential tilting of the blades, and at least partially close the radial gaps between the teeth and the platforms of the blades.

A gas turbine engine rotor having an axis, comprising: a body about the axis having an inner surface, a seat having an outer seat edge at a first radial location surrounded by the inner surface at a second radial location, a lip along the inner surface having an inner lip edge spaced axially away from the seat to define a gap, the lip at a rated axial location between the inner lip edge and the seat facing toward the seat at a normal angle; a damper in the gap having first and second damper surfaces, the first damper surface adjacent the seat; and a split ring in the gap adjacent the second damper surface, having an outer ring edge spaced from the inner surface, engaging the lip at the rated axial location and resiliently expandable against the lip deflects the split ring to load the damper against the seat.

A rotor for a contrarotating turbine comprising a drum and a blading mounted inside, the drum comprising a hook delimiting a housing having an outer wall and an inner wall, the blading comprising a blade and an outer platform provided with spoiler placed inside the housing, wherein the rotor comprises a foil comprising an elastic inner wing and an outer wing, the outer wing being arranged radially between the spoiler and the outer wall, the inner wing having a first support with the inner wall and a second support with the spoiler, the inner wing being arranged in the housing so as to exert a force on the spoiler so as to press the spoiler against the outer wall via the outer wing.