A device for targeted repair of micro-nano damage of an inner ring of an aeroengine bearing by an electric-magnetic composite field includes a driving device, an ultrasonic shot peening device, a pulsed current generator and a magnet yoke-coil device. The driving device includes a motor and a rotating shaft. The motor drives the rotating shaft to drive a bearing inner ring to synchronously rotate. The ultrasonic shot peening device includes an ultrasonic shot peening cavity, an ultrasonic probe and steel balls, the ultrasonic probe extends into the cavity from an opening in a lower end of the cavity, and the steel balls are placed on the ultrasonic probe. An opening in an upper end of the cavity is placed below the bearing inner ring. The pulsed current generator generates pulsed current on the bearing inner ring. The magnet yoke-coil device can excite a magnetic field around the bearing inner ring.

A method of monitoring turbine blade creep in a gas turbine engine is provided. The method includes: receiving stereo images of a turbine blade of a row of turbine blades, the images having been obtained using a stereo borescope located in the engine adjacent the row of turbine blades; identifying same features of the blade in each of the stereo images; mapping each of the identified features by triangulation onto a 3D space to produce a 3D depth map of at least part of the blade; providing a 3D reference model of the blade; and comparing the 3D reference model with the 3D depth map to measure one or more deviations in shape of the blade to determine an amount of creep-induced distortion of the blade.

A method of monitoring turbine blade creep in a gas turbine engine is provided. The method includes: receiving an image of a turbine blade of a row of turbine blades, the image having been obtained using a borescope located in the engine adjacent a row of turbine blades; measuring on the image a distance between radially inner and radially outer landmarks on the turbine blade; and comparing the measured distance with a reference distance to determine an amount of creep-induced lengthening of the blade.

A method of reprocessing a metal product includes a welding step for welding a dummy member to the metal product, a reprocessing step for reprocessing the metal product in a state where the metal product is supported by a first support unit and the dummy member is supported by a second support unit, and a removal step for removing the dummy member from the metal product after the reprocessing step. The reprocessing of the metal product while the metal product is fixed is thus enabled without restriction from the shape of the metal product.

A method repairs welding of an aircraft turbine engine blade that has a lower surface and an upper surface connected by a leading edge and a trailing edge The blade further includes a free end referred to as the tip. The method includes the repair welding of the tip and including the steps of: securing a first stop to the leading edge at the tip and a second stop to the trailing edge at the tip, depositing a repair weld bead on the tip, from the first stop to the second stop, and removing the first and second stops. The first and second stops are secured solely by squeezing same on the leading and trailing edges.

A method for repairing a part made of composite material includes producing a recessed section by removing the composite material at a damaged area, producing grooves extending on the two faces of the part from edges of the recessed section, producing orifices in the part opening out into the grooves, tree-dimensional weaving of a filling part fiber preforms including a central section having a shape corresponding to the shape of the recessed section and fiber bundles extending from the central section, placing the filling preforms respectively on either face of the part with the fiber bundles in the grooves on the faces of the part and in the orifices such that the fiber bundles open out into the grooves present on the opposite face of the part, impregnating the filling fiber preforms with a precursor resin of a matrix, transforming the resin into a matrix to obtain a filling part.

A method for repairing a flow path surface of a case for a variable vane assembly includes measuring a wear depth at a location within a wear recess formed in the flow path surface of the case, determining a coating thickness corresponding to the wear depth at the location, and repairing the flow path surface of the case by applying a coating to the wear recess, where the coating has the coating thickness at the location.

A service apparatus for use in maintaining a machine including a stator and a rotor is provided. The service apparatus includes a carriage assembly configured to couple to the rotor. The service apparatus is selectively transitionable between a stowed position in which the service apparatus is rotatable with the rotor and an extended position in which the service apparatus is extended toward the stator. The service apparatus also includes at least one maintenance device coupled to the carriage assembly. The at least one maintenance device is operable to perform a maintenance operation on a surface of the stator with the service apparatus in the extended position.

A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.

A maintenance system for a turbine engine includes a pump and a crank device operatively coupled to the pump. The pump includes a pump housing and a pump drive that is configured to operatively couple to the turbine engine. The crank device is operatively coupled to the pump and includes a crank drive that is configured to enable movement of the pump drive and thereby movement of the turbine engine during non-operational periods, such as during a maintenance or inspection period.