In one aspect, a fan assembly is provided that can be manufactured while producing a significantly reduced amount of scrap material. More specifically, the fan assembly utilizes a hub ring and one or more hub strips to support a plurality of blades rather than a solid center disc or end disc used by some prior approaches. In another aspect, a method is provided that includes bending a member into an annular configuration and joining end portions of the member together to rigidly fix the member in the annular configuration. The rigid annular member may be used as an end ring, a hub ring, an orifice, or other component, while producing significantly less scrap material than traditional approaches.

Turbine wheels, turbine engines, and methods of fabricating the turbine wheels are provided. An exemplary method includes fabricating a turbine wheel that includes a rotor disk and a plurality of turbine blades operatively connected to the rotor disk through a blade mount. The method includes locating a cooling passage within a blade mount preliminary configuration and a cooling inlet on a surface of the blade mount preliminary configuration. A rotor disk bonding surface geometry and a blade mount bonding surface geometry are designed based upon a stress analysis of the turbine wheel and locations of the cooling passage and cooling inlet. A rotor disk production configuration and a blade mount production configuration are generated based upon the preliminary configurations. A blade mount and a rotor disk are formed based upon the production configurations. A blade ring including a plurality of blade mounts is formed and bonded to the rotor disk.

Tooling for the coating of lips of a turbomachine rotor sector, comprising a support for a rotor sector, a centering plate adapted to be inserted into a rotor sector, said centering plate having a central housing, a tool, said tool comprising a centering arm, adapted to be inserted into the central housing of the centering plate, a torch, adapted to spray a ceramic material, a machining tool, said tooling being configured so as to position the tool relative to the rotor sector via the centering plate, and to simultaneously perform on the rotor sector a spraying of ceramic material and a machining on two distinct sectors of the lips.

Provided is a turbine rotor disc repairing method for removing a defect portion created in an outer peripheral portion of a turbine rotor disc having a blade groove formed in the outer peripheral portion and then reforming the blade groove. The method includes: removing a region including the defect portion from the turbine rotor disc with a rotating shaft supported horizontally to form a disc under repair; annularly joining an edge plate along an outer peripheral edge of the disc under repair by welding; performing build-up welding of a surface to be welded while rotating the disc under repair around the rotating shaft; and removing an excess thickness of a build-up weld and the edge plate from the disc under repair, wherein the disc under repair includes a first groove and a first route surface continuous with the first groove.

A method of fabricating a functionally graded turbine engine component is disclosed and includes the step of depositing layers of powder onto a base and solidifying/fusing each layer with a first directed energy beam to define a component. The method further includes varying a process parameter between deposited layers to define different material properties within the component. The method also proposes surface enhancement approach that can be used after depositing each layer to locally customize the material properties. The method also proposes machining the different internal surfaces to achieve the proper surface finishing required.

A hybrid additive manufacturing process is utilized for creating a shrouded rotor with the shrouded rotor having a hub at a radial center, a shroud at a radial outer side, and vanes extending therebetween. The hybrid additive manufacturing process includes forming the shrouded rotor in stages, with a first stage being formed by depositing material in an axial direction through a first stage of the hub, machining an outer surface of the first stage of the hub to smooth the outer surface, depositing material on the first stage of the hub in a radial direction through a first stage of the vanes and the shroud, and machining all surfaces of the first stage of the vanes and an inner surface of the first stage of the shroud to smooth the surfaces. Subsequent stages of the shrouded rotor are formed similarly to the first stage.

The invention relates to the manufacturing of a rotor (23) of a high-pressure compressor. Various installation constraints are proposed in terms of temperature, angle and unevenness and/or runout defects to be considered. For example, when installing the sealing disk (25) on the first drum (27) of the rotor and/or the intermediate disk (29) on the first drum assembled with the sealing disk, axial packing (X1) is applied with a pressure ranging from 40 to 6010.sup.5 Pa.

A rim seal between a stator and a rotor in a gas turbine engine is described. The seal includes an axial overlap between platform rims of the stator and the rotor. The axial length of the platform rim of one of the stator and the rotor is accommodated within a radially aligned trench defined in the other of the stator and the rotor.

A method for manufacturing impellers is described. The method provides for manufacturing a plurality of tubular components, each tubular component forming an inner passage, which is shaped as one of the flow passages of the final impeller. The tubular components are assembled together forming a semi-finished impeller. The semi-finished impeller is provided with annular cavities extending around the rotation axis of the impeller and gaps between adjacent tubular components. The gaps and cavities are filled with metal powder and the semi-finished impeller is subject to hot isostatic pressing, to densify the metal powder and form a monolithic final impeller.

A method for designing and building a wheel that is simultaneously a turbine and an impeller with a plurality of impeller blades, wherein each impeller blade of the plurality of impeller blades is hollow along an entire length of the impeller blade and which leads into a peripheral circular chamber that operates as a fueled engine (THRA). The method includes building an evolving section of an inner channel of the impeller blades with a plurality of strips each having a neutral axis, wherein each impeller blade rests on a profile of a plurality of profiles of a corresponding neutral axis, the profile built for an inlet to the turbine and for inlets to each impeller blade.