A turbomachine rotor includes a hub and rotor blades. An imbalance correction device is provided which extends radially inside the hub bottom and includes axially front and rear walls, together with the hub bottom, defining a volume of the imbalance correction device. A mass piece, during normal operation of the rotor, is arranged on the axis of rotation. A filler material at least partially fills the volume and surrounds the mass piece in a radial direction. Radial bores extend in a radial direction from the hub bottom side through the rotor hub to a respectively assigned rotor blade. The radial bores and the filler material are formed and coordinated such that, upon loss of a rotor blade, filler material escapes from the thus exposed radial bore assigned to the lost rotor blade, wherein the mass piece moves on the axis of rotation toward the lost rotor blade.

An abnormality treatment apparatus includes: a sensor which outputs a signal upon detecting an event caused by contact of a rotor of a rotating machine during rotation of the rotor; and a control unit which executes at least one of rotation number control of reducing the number of rotations of the rotor step by step, liquid injection control of injecting liquid into a housing chamber of the rotor step by step, and pressure control of lowering a discharge pressure of the rotating machine step by step based on reception of the signal output from the sensor.

Centralizer apparatuses attached around a unison ring include rub buttons at inner ends of stud attached to and spaced apart from the unison ring and include rolling bearings. Each rolling bearing rotatably trapped within bearing chamber in bearing receptacle at inner end of stud.

Tip cap includes bearing aperture trapping rolling bearing within bearing chamber. Rolling bearing extends partially through bearing aperture. Rolling bearing may be spring loaded within chamber by spring between the bearing receptacle and the rolling bearing. Stud may extend through and may be threaded into mounting aperture in unison ring and nut may be threaded onto outer end of stud. Variable stator vanes rotatably mounted to a casing and connected to vane crank arms connected to the unison ring mounted exterior to casing.

Centralizer apparatuses attached around a unison ring include rub buttons at inner ends of stud attached to and spaced apart from the unison ring and include rolling bearings. Each rolling bearing rotatably trapped within bearing chamber in bearing receptacle at inner end of stud.

Tip cap includes bearing aperture trapping rolling bearing within bearing chamber. Rolling bearing extends partially through bearing aperture. Rolling bearing may be spring loaded within chamber by spring between the bearing receptacle and the rolling bearing. Stud may extend through and may be threaded into mounting aperture in unison ring and nut may be threaded onto outer end of stud. Variable stator vanes rotatably mounted to a casing and connected to vane crank arms connected to the unison ring mounted exterior to casing.

A geared turbofan engine with a sun shaft driving a sun gear of planetary gearbox. The sun shaft having a front section proximal to the gearbox and a rear section distal from the gearbox. The outer diameter of the front section of the sun shaft is smaller than the outer diameter of the rear section of the sun shaft. The front section of the sun shaft having between two and four undulant sections, wherein each undulant section having at least one axial part extending in axial direction of the sun shaft and two diaphragm parts on either side of the at least one axial part extending in radial direction outward, the at least one axial part of the undulant section having an inner diameter smaller than the outer diameter of the front section of the sun shaft.

A damping device that includes features for damping bending vibration of a shaft rotating about its axis of rotation and methods for damping bending vibration utilizing the damping device are provided. In one exemplary aspect, the damping device includes a damping disc operatively coupled with a shaft, e.g., of a turbine engine or shaft system. The damping disc is at least partially received within a chamber defined by a housing. The chamber of the housing is configured to receive a damping fluid. When the shaft is rotated about its axis of rotation, the damping disc is movable within the chamber to move the damping fluid such that the damping fluid absorbs bending vibration emitted by the shaft. The damping fluid moved by the damping disc dampens bending vibration emitted by the shaft.

A method for controlling the bending deformation of a turbomachine shaft at rest subjected to the residual heat of operation of the turbomachine, wherein the shaft is rotated at a rotation speed between 0.1 and 50 revolutions per minute depending on the bending deformation deflection of the shaft when the turbomachine is at rest.

A method for controlling the bending deformation of a turbomachine shaft at rest subjected to the residual heat of operation of the turbomachine, wherein the shaft is rotated at a rotation speed between 0.1 and 50 revolutions per minute depending on the bending deformation deflection of the shaft when the turbomachine is at rest.

Provided is a fan blade including an airfoil body composed of a composite material of thermoplastic resin or thermosetting resin and reinforcement fibers; a sheath made of metal that covers at least a part of a leading edge part of the airfoil body; and a guard made of metal that covers at least a part of a trailing edge part of the airfoil body, wherein a rear end part of the sheath and a front end part of the guard overlap in a thickness direction of the airfoil body on each plane of a pressure side and a suction side of the airfoil body, and the front end part of the guard is interposed between the rear end part of the sheath and the airfoil body in the overlapped section.

A gas turbine engine includes a fan, a fan shaft that rotationally support the fan, a first bearing that rotationally support the fan shaft and a support arrangement configured to support the first bearing. The support arrangement includes a first support member coupled to first bearing and to a mechanical ground to define a first load path, and a second support member coupled to the mechanical ground and first bearing to define a second load path. The second support member is coupled to one of the first bearing and mechanical ground by a first frangible link. A load extends between the bearing and mechanical ground through the first and second loads paths, and in the event of a predetermined radial load being applied to first bearing, the frangible link breaks such that the load extends between the first bearing and the mechanical ground through first but not second load path.