According to the invention, a blade is friction-welded to a rotor disk of a turbomachine, the disk comprising a projecting block having an outer surface to which the blade is to be welded. To this end: a surfacing process is carried out on at least a part of the periphery of the block, in the region of said outer surface; the outer surface of the block and the surfacing are machined in order to level same; and friction-welding is then carried out between the surfaced outer surface of the block and the blade.

A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub. The method further comprises welding the aerofoil to the stub. The method yet further comprises removing material from the stub so as to define a hollow region that extends through the support member and stub to the cavity of the aerofoil.

A method for attaching an abradable piece support by crimping to the radially inner wall of a vane sector of a turbomachine, comprises deforming opposite rims of the radially inner wall on opposite free axial ends of the abradable piece support respectively, jointly, by means of two pressure blocks (40A, 40B) respectively, which are attached to each other and delimiting a space (42) between them intended to accommodate a median portion of the abradable piece support. A crimping attachment device (30) comprising such pressure blocks can in particular be operated by means of a conventional press, and can enable the method for attaching the abradable piece support to be automated.

The present invention relates to a method of manufacturing an impeller blade of a shot peening machine, the method including a part cutting process of forming a shot moving plate in which protrusions are formed by cutting a steel plate and first and second side guide plates in which insertion holes are formed, and a blade assembling process of assembling a blade by inserting the protrusions of the shot moving plate into the insertion holes of the first and second side guide plates, and an impeller blade manufactured according to the method.

In one aspect, a fan assembly is provided that includes a plurality of elongated metallic fan blades, a first metallic end ring, a second metallic end ring, and a metallic hub support connected to the fan blades intermediate the first and second end rings. The fan blades include straight inlet edges radially inward from first and second radially inner edges of the first and second metallic end rings so that inlet portions of the blades extend radially inward from the first and second metallic end rings. In another aspect, a fan assembly is provided that includes a hub support having a hub strip and a hub ring. The hub strip has an elongate configuration with an attachment portion connected to the hub ring at one end of the hub strip and another attachment portion connected to the hub ring at an opposite end of the hub strip.

Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (T.sub.DISK_PROCESS_MIN) for the hub disk and a maximum critical temperature for the rotor blades (T.sub.BLADE_MAX) is established such that T.sub.BLADE_MAX is less than T.sub.DIsK_PROCESS_MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than T.sub.DISK_PROCESS_MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below T.sub.BLADE_MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.

An apparatus includes an electrode assembly comprising a carriage having a plurality of electrode holders, the electrode holders being respectively configured to detachably receive a plurality of electrodes, the electrodes include a plurality of first electrodes and a plurality of second electrodes. The first electrodes are configured for rough machining a workpiece by electric discharging or wire electric discharging to remove material from the workpiece, the second electrodes are configured for finish machining the rough machined workpiece by electric discharging to remove material from the rough machined workpiece.

A cooling device for a rotor assembly of a gas turbine engine includes an airflow nozzle configured to be installed at a cooling location of the rotor assembly. The airflow nozzle extends entirely around a circumference of the rotor assembly and includes a plurality of airflow inlets and a nozzle outlet to direct an airflow toward the cooling location. An airflow source is operably connected to the plurality of airflow inlets.

A process for manufacturing a preformed sheet having geometric surface features for a geometrically segmented abradable ceramic thermal barrier coating on a turbine engine component, the process comprising the steps of providing a preformed sheet material. The process includes forming a partially of geometric surface features in the sheet material. The process includes joining the sheet material to a substrate of the turbine engine component. The process includes disposing a thermally insulating topcoat over the geometric surface features and forming segmented portions that are separated by faults extending through the thermally insulating topcoat from the geometric surface features.

Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (T.sub.DISK_PROCESS_MIN) for the hub disk and a maximum critical temperature for the rotor blades (T.sub.BLADE_MAX) is established such that T.sub.BLADE_MAX is less than T.sub.DISK_PROCESS_MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than T.sub.DISK_PROCESS_MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below T.sub.BLADE_MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.