A cleaning process (blasted-particles cleaning process) includes performing, a plural number of consecutive cycles, an ultrasonic cleaning treatment including immersing a turbine rotor blade in a water basin and conducting an ultrasonic wave into the water basin to clean the turbine rotor blade, and a pressurized-water cleaning treatment including spraying pressurized water into an internal cooling flow channel after the ultrasonic cleaning treatment is performed. The cleaning process is performed after a bonding coat layer removing process of removing a bonding coat layer (first coating layer) by chemical treatment, and a cleaning process of cleaning the turbine blade by blast treatment. Heat tinging process is then performed.

A diffuser for an oil drainback system drain tube includes a flow chamber configured for attachment to an open end of a drain tube, wherein the flow chamber has a side wall and an end wall, and openings in at least the side wall.

A method comprises inspecting a ceramic matrix composite component assembled in a gas turbine engine to determine an extent of damage to the ceramic matrix composite component, determining a repair technique to repair the damage to the ceramic matrix composite component based on the extent of damage to the ceramic matrix composite component, and repairing the ceramic matrix composite component using the repair technique.

A method for modifying an existing single shaft combined cycle power plant having a steam turbine part and a gas turbine part which are connected to each other rigidly by an intermediate shaft. The gas turbine part is supported by two pin-ended supports allowing a certain axial displacement of the casing by rotating about corresponding axes. The old gas turbine part is replaced by a new gas turbine part having a different structure, namely a rigid support and a flexible support. Relative thermal expansion or displacement of the intermediate shaft is compensated by a hydraulic unit comprising a double-acting piston for displacing the gas turbine rotor with respect to the gas turbine stator. The hydraulic unit is controlled based on a displacement measurement in the steam turbine.

A system and method including receiving a data model representation of a part, the data model representation including at least one layer of the part and inner and outer contours for the at least one layer; determining a hatch pattern for each layer of the at least one layer of the part, the hatch pattern for each layer being dependent on the inner and outer contours for each respective layer; generating a record of the determined hatch pattern for each layer, the record including locations for the hatch pattern for each layer; and saving the record of the determined hatch pattern for each layer of the part. In some aspects, the record of the determined hatch pattern for each layer of the part may be used in an additive manufacturing process.

The invention relates to a method for handling a rectifier of a turbojet of an aircraft, the rectifier having an axis defining the asymmetry thereof, said method comprising a step of placing the rectifier on the rollers of a supporting structure, the structure and the rollers thereof being arranged such that the axis of the rectifier is inclined at a non-null acute angle in relation to the horizontal, and a step of controlling, maintaining, assembling, handling, storing, deburring and/or cleaning the rectifier, during which the rectifier is pivoted about the axis thereof. The invention also relates to a trolley for handling a rectifier for an axial turbojet, said trolley comprising at least two of the lower rollers that have axes inclined in relation to the horizontal of said angle and at least one upper roller, the axis of which is inclined in relation to the vertical of said angle.

A rotor balancing method for a gas turbine having a rotor with a first correction plane and a second correction plane, wherein a first balancing weight is attached to the first correction plane. The method includes performing a first influence run wherein first balancing weight remains fitted for the subsequent second influence run; fitting a first calibration weight to the second correction plane using a reference influence vector; performing a second influence run; removing the first calibration weight from the rotor and calculating an influence vector of the second correction plane using a first set of vibration measurements and a second set of vibration measurements taken during the first influence run and the second influence run, respectively; and carrying out balancing of the rotor by fitting a final balancing weight to the first correction plane and a second balancing weight to the second correction plane using the calculated influence vectors.

Embodiments of the present disclosure generally relate to protective coatings on various substrates including aerospace components and methods for depositing the protective coatings. In one or more embodiments, an aerospace component has a protective coating containing an aluminum oxide layer disposed on a surface of the aerospace component, a metal-containing catalytic layer disposed on the aluminum oxide layer, and a boron nitride layer disposed on the metal-containing catalytic layer. The aerospace component contains a superalloy having at least nickel and aluminum. In some examples, the aerospace component is a turbine blade, a turbine vane, a support member, a frame, a rib, a fin, a pin fin, a fuel nozzle, a combustor liner, a combustor shield, a heat exchanger, a fuel line, a fuel valve, an internal cooling channel, or any combination thereof.

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 bypass valve assembly for a turbine generator includes a valve body, bypass seats, valve stem, valve cap, bypass valve disc, bypass valves, and pressure seal head. The valve body defines a central bore and a plurality of passageways. Each passageway has an inlet smaller than its outlet. Each bypass seat is within the inlet of a corresponding passageway. The bypass seats have a higher wear resistance than the valve body. The valve stem is within the central bore. The valve cap is secured to the valve body. The bypass valve disc is secured to the valve stem. Each bypass valve has a base portion and a nose portion. Each nose portion defines a contoured surface area with a wear coating and extends into a corresponding passageway. The pressure seal head is disposed around the valve stem and defines steps having a wear coating.