The present invention relates to a turbomachine assembly, comprising: a casing (10), a first rotor (12) which is movable in rotation with respect to the casing (10) about a longitudinal axis (X-X), and comprising: *a disk (120), and *a plurality of blades (122) capable of flapping with respect to the disk (120) during a rotation of the first rotor (12) with respect to the casing (10), a second rotor (140) which is movable in rotation with respect to the casing (10) about the longitudinal axis (X-X), and a damper (2) which is configured to damp a displacement of the first rotor (12) with respect to the second rotor (140) in a plane orthogonal to the longitudinal axis (X-X), the displacement being caused by a flapping of at least one blade (122) among the plurality of blades (122), the damper (2) comprising: o a first bearing part (21): *bearing against the first rotor (12), and *being configured to apply a first centrifugal force (C1) to the first rotor (12), o a second bearing part (22): *bearing against the second rotor (140), and *being configured to apply a second centrifugal force (C2) on the second rotor (140), and o a linking part (20): *connecting the first bearing part (21) to the second bearing part (22), and being thinned relative to the first bearing part (21) and the second bearing part (22), and o a flyweight (3) which is fixedly mounted on the damper (2).

The present invention relates to a turbomachine assembly, comprising: a casing (10), a first rotor (12) which is movable in rotation with respect to the casing (10) about a longitudinal axis (X-X), and comprising: *a disk (120), and *a plurality of blades (122) capable of flapping with respect to the disk (120) during a rotation of the first rotor (12) with respect to the casing (10), a second rotor (140) which is movable in rotation with respect to the casing (10) about the longitudinal axis (X-X), and a damper (2) which is configured to damp a displacement of the first rotor (12) with respect to the second rotor (140) in a plane orthogonal to the longitudinal axis (X-X), the displacement being caused by a flapping of at least one blade (122) among the plurality of blades (122), the damper (2) comprising: o a first bearing part (21): *bearing against the first rotor (12), and *being configured to apply a first centrifugal force (C1) to the first rotor (12), o a second bearing part (22): *bearing against the second rotor (140), and *being configured to apply a second centrifugal force (C2) on the second rotor (140), and o a linking part (20): *connecting the first bearing part (21) to the second bearing part (22), and being thinned relative to the first bearing part (21) and the second bearing part (22), and o a flyweight (3) which is fixedly mounted on the damper (2).

A turbomachine assembly includes a casing, first and second rotors, and a damper. The first rotor includes a disk and blades and is movable in rotation relative to the casing. The second rotor is movable relative to the casing around a longitudinal axis. The damper damps a movement of the first rotor relative to the second rotor. The damper includes first to third parts. The first part bears on the first rotor in a first area extending over a first angular sector around the longitudinal axis and applies a first centrifugal force on the first rotor. The second part bears on the first rotor in a second area that is smaller than the first angular sector and extends over a second angular sector around the longitudinal axis. The third part bears on the second rotor and applies a second centrifugal force on the second rotor.

A turbomachine assembly includes a casing, first and second rotors, and a damper. The first rotor includes a disk and blades and is movable in rotation relative to the casing. The second rotor is movable relative to the casing around a longitudinal axis. The damper damps a movement of the first rotor relative to the second rotor. The damper includes first to third parts. The first part bears on the first rotor in a first area extending over a first angular sector around the longitudinal axis and applies a first centrifugal force on the first rotor. The second part bears on the first rotor in a second area that is smaller than the first angular sector and extends over a second angular sector around the longitudinal axis. The third part bears on the second rotor and applies a second centrifugal force on the second rotor.

During operation, a bladed rotor disk typically experiences out-of-plane vibration which can result in deterioration and/or cracking at the interface between adjacent shrouds of the turbine blades. In an embodiment, slots are formed at the end of a labyrinth seal segment of each shroud. Preloaded spring strips are inserted through the slots to couple adjacent shrouds while preventing the natural frequency of the turbine blades from drifting to the operating speed range and/or providing vibration damping to the untuned blade mode.

A method to monitor rotor blade vibration using unsteady casing pressure. The method applies a non-intrusive blade vibration monitoring technique by using an array of unsteady pressure sensors which may be flush-mounted in the casing of a compressor. The method comprises using spinning mode theory and temporal-spatial analysis to obtain frequency and nodal diameter information of spinning pressure waves associated with the rotor blade vibration. An example of the compressor can be a multistage axial compressor.

The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade of smaller length than the first blade (20), and a damping device (4) comprising a first radial external surfaces (41) supported with friction against the first module (2), as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) for the purpose of damping their respective vibrational movements during operation.

The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade of smaller length than the first blade (20), and a damping device (4) comprising a first radial external surfaces (41) supported with friction against the first module (2), as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) for the purpose of damping their respective vibrational movements during operation.

An aircraft turbomachine rotor comprising a rotor disc extending transversely with respect to a longitudinal axis X, a plurality of blades and a damping device comprising: a support ring configured to extend transversely with respect to the longitudinal axis X and configured to be mounted on the outer periphery of the rotor disc, and a plurality of damping members that are secured to the support ring and extend projecting upstream from the support ring, each damping member being configured to extend at least under a platform of a blade so as to exert a radially outward force so as to damp the radial movement of said blade when the turbomachine is in operation.

Counter-rotating turbine (C) of a turbomachine (10) extending about an axis (X) and comprising an inner rotor configured to rotate about the axis of rotation (X), and comprising an inner drum on which an inner movable blading (22) is fixed, an outer rotor configured to rotate about the axis of rotation (X) in a direction opposite to the inner rotor, and comprising an outer drum (50) on which an outer movable blading (20) is fixed, the outer movable blading (20) comprising at least one fixing rod (212) extending through an orifice (51) of the outer drum (50), the outer movable blading (20) being fixed to the outer drum (50) via a clamping means (100) fixed to the fixing rod (212) from an outer face of the outer drum (50), a set ring (80) being disposed around the fixing rod (50) in the orifice (51) of the outer drum (50).