A method and apparatus for maintaining integrally bladed rotors (IBR) includes using first vibration data from a IBR vibration apparatus of a first IBR to determine a set of values for a corresponding set of inherent vibratory properties based on a reduced order model for an IBR type to which the first IBR belongs. Shape data indicating an initial shape of a surface of a first blade is used, with repair data that indicates a candidate repair to form a restored shape, to determine a change in a value of an inherent blade section vibratory property of the set of inherent vibratory properties. A condition of the first IBR is determined based at least in part on the change in the value of the inherent blade section vibratory property. The first IBR is maintained based on the condition.

A method and apparatus for maintaining integrally bladed rotors (IBR) includes using first vibration data from a IBR vibration apparatus of a first IBR to determine a set of values for a corresponding set of inherent vibratory properties based on a reduced order model for an IBR type to which the first IBR belongs. Shape data indicating an initial shape of a surface of a first blade is used, with repair data that indicates a candidate repair to form a restored shape, to determine a change in a value of an inherent blade section vibratory property of the set of inherent vibratory properties. A condition of the first IBR is determined based at least in part on the change in the value of the inherent blade section vibratory property. The first IBR is maintained based on the condition.

Damping systems are provided for a rotor blade platform. The damping system may include a blade platform defining a damper pocket and a CMC wedge damper positioned within the damper pocket. The CMC wedge damper has at least one damper angled surface parallel to a longitudinal axis. The damper pocket comprises a pocket angled surface positioned about the at least one damper angled surface.

A gas turbine engine having an optical imaging system with a housing configured for mounting to a wall of the turbine engine, a hollow probe extending from the housing and having a longitudinal axis, and an image receiving device at an end of the hollow probe configured to receive at least one of a perspective or image.

A damper ring is mounted in frictional engagement with a radially inwardly facing surface of a circumferential groove defined in a rotary part of a gas turbine engine. Energy dissipation is provided via sliding friction of the ring in the groove. The damper ring has a circumferentially segmented ring body having a non-uniform circumferential stiffness around its circumference including a locally reduced stiffness in a circumferential direction between each pair of circumferentially adjacent ring segments.

A damper ring is mounted in frictional engagement with a radially inwardly facing surface of a circumferential groove defined in a rotary part of a gas turbine engine. Energy dissipation is provided via sliding friction of the ring in the groove. The damper ring has a circumferentially segmented ring body having a non-uniform circumferential stiffness around its circumference including a locally reduced stiffness in a circumferential direction between each pair of circumferentially adjacent ring segments.

A blade (1) for a turbomachine, including an impact chamber (2), a single impulse body (3) being situated in the impact chamber, a clearance (S1+S2) between the impulse body and the impact chamber being at least 10 μm and/or at most 1.5 mm in at least one direction.

A blade (1) for a turbomachine, including an impact chamber (2), a single impulse body (3) being situated in the impact chamber, a clearance (S1+S2) between the impulse body and the impact chamber being at least 10 μm and/or at most 1.5 mm in at least one direction.

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).