Abstract: 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.

Abstract: 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

Abstract: The present invention relates to an assembly for a turbomachine, comprising: a first rotor; a second rotor, and a damper (2) configured to damp a displacement of the first rotor relative to the second rotor, the damper comprising: a first portion (21) bearing against the first rotor and having a first thickness, a second portion (22) bearing against the second rotor and having a second radial thickness, and a third portion (23) connecting the first portion (21) to the second portion (22) and having a third radial thickness, wherein the third radial thickness is greater than at least one of the first radial thickness and the second radial thickness.

Abstract: The invention relates to an assembly (1) for a turbomachine 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 with a length less than the first blade (20), and a damping device (4) extending with at least one component along a turbomachine longitudinal axis (X-X), characterized in that the damping device (4) is annular while extending circumferentially around the turbomachine longitudinal axis (X-X) and in that the damping device (4) comprises a first radial external surface (40) 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) in order to damp their respective vibrational movements during operation.

Abstract: A turbomachine assembly is provided. The assembly includes: a first rotor module including a first blade, a second rotor module, connected to the first rotor module, and including a second blade of smaller length than the first blade, and a damping device including a plurality of first radial external surfaces supported with friction against the first module. The damping device is stepped, and includes a second radial external surface supported with friction against the second module, so as to couple the modules for the purpose of damping their respective vibrational movements during operation.

Abstract: A turbomachine assembly is provided. The assembly includes: a first rotor module including a first blade, a second rotor module, connected to the first rotor module, and including a second blade of smaller length than the first blade, and a damping device including a plurality of first radial external surfaces supported with friction against the first module. The damping device is stepped, and includes a second radial external surface supported with friction against the second module, so as to couple the modules for the purpose of damping their respective vibrational movements during operation.

Abstract: The present invention reltues to an assembly Ru a turbomachine, comprising: a first rotor; a second rotor, and, a damper (2) configured to damp a displacement of the first rotor relative to the second rotor, the damper comprising: a first portion (21) bearing against the first rotor and having a first thickness, a second portion (22) bearing against the second rotor and having a second radial thickness, and a third portion (23) connecting the first portion (21) to the second portion (22) and having a third radial thickness, wherein the third radial thickness is greater than at least one of the first radial thickness and the second radial thickness.

Abstract: 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

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a disk (21), a first blade (20) being mounted on the external periphery of the disk (21), the first blade (20) comprising a platform (25) and a support (27), a second rotor module (3), connected to the first rotor module (2) by means of at least two attachments (22) and comprising a second blade of smaller length than the first blade (20), and a damping device (4) attached to the attachment (22) between the first (2) and the second (3) rotor module so as to dampen their vibrational movements during operation, and comprising: a head (40) comprising a first radial external surface (42) supported with friction against the platform (25), and two attachment feet (41) extending on either side of the support (27) of the first blade (20).

Abstract: The invention relates to an assembly (1) for a turbomachine 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 with a length less than the first blade (20), and a damping device (4) extending with at least one component along a turbomachine longitudinal axis (X-X), characterized in that the damping device (4) is annular while extending circumferentially around the turbomachine longitudinal axis (X-X) and in that the damping device (4) comprises a first radial external surface (40) 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) in order to damp their respective vibrational movements during operation.

Abstract: The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a disk (21), a first blade (20) being mounted on the external periphery of the disk (21), the first blade (20) comprising a platform (25) and a support (27), a second rotor module (3), connected to the first rotor module (2) by means of at least two attachments (22) and comprising a second blade of smaller length than the first blade (20), and a damping device (4) attached to the attachment (22) between the first (2) and the second (3) rotor module so as to dampen their vibrational movements during operation, and comprising: a head (40) comprising a first radial external surface (42) supported with friction against the platform (25), and two attachment feet (41) extending on either side of the support (27) of the first blade (20).

Abstract: A shim (20) for a turbomachine blade (14), the shim comprising two branches (20A) for coming against bearing surfaces (16A) of the blade rotor (16), and a base part (20B) interconnecting the branches. The shim presents, at least in its branches (20A), a multilayer structure having at least three layers (31, 32, 33) that are fastened to one another and superposed in the following order: a first layer (31) of a first material; a second layer (32) of a second material; and a third layer (33) of a third material that is optionally different from the first material, said first and third materials presenting respective first and third Young's moduluses of values E and E? at any arbitrary operating temperature in the operating temperature range of the shim, and said second material presenting a second Young's modulus of value lying in the range E/20 to E/5 and in the range E?/20 to E?/5 at said operating temperature.

Abstract: A turbomachine rotor assembly comprising: a rotor disk (2) presenting slots (4) in its outer periphery; blades (14) fastened via their roots (16) in said slot (4); and shims (20) mounted between the blade roots (16) and the disk (2), each shim (20) comprising two branches (20A) and a base part (20B) interconnecting the branches, each branch (20A) being disposed between the bearing surface (16A) of a blade root (16) and the corresponding bearing surface (22A) of the disk (2); each branch (20A) being made of a first material presenting a first Young's modulus of value E, at any operating temperature in the operating temperature range of the shim (20). The rotor assembly includes pads (40) adhering to the bearing surfaces (22A) of the disk and/or to the bearing surfaces (16A) of the blade root, the pads (40) being made of a second material presenting a second Young's modulus of value lying in the range E/20 to E/5 at said operating temperature.

Abstract: This axial mounting of the bottoms (5) of fan blades provides two levels of flexibility, and features rather low stiffness after using up a predetermined clearance (35) between two stop parts (32, 34), which then imposes a significant increase in stiffness; however significant energy was able to be absorbed through the elastic deformation of certain parts (7, 30) located between the blade and the disc (2), which enables the blade to withstand rather significant momentary forces, for example if a neighboring blade breaks and strikes it.

Abstract: A turbojet engine fan rotor including a rotor disk having a peripheral rim with a plurality of axially extending channels carrying a plurality of fan blades each having a blade root interengaging with the channels of the disk, and a mounting arrangement for securing the blades to the disk. The mounting arrangement includes an annular member having a plurality of radially extending teeth, a plurality of wedges each interposed between one of the blade roots and a corresponding one of the channels and including a radially extending boss provided at one end, and a plurality of radially extending protrusions from the disk. The plurality of teeth and the plurality of protrusions cooperate with one another to secure the annular member with the rotor disk.

Abstract: This axial mounting of the bottoms (5) of fan blades provides two levels of flexibility, and features rather low stiffness after using up a predetermined clearance (35) between two stop parts (32, 34), which then imposes a significant increase in stiffness; however significant energy was able to be absorbed through the elastic deformation of certain parts (7, 30) located between the blade and the disc (2), which enables the blade to withstand rather significant momentary forces, for example if a neighboring blade breaks and strikes it.