A method is provided for machining an airfoil section (12) of a turbine blade or vane produced by a casting process. The airfoil section (12) has an outer wall (18) delimiting an airfoil interior having one or more internal cooling passages (28). The method involves: receiving design data pertaining to the airfoil section (12), including a nominal outer airfoil form (40.sub.N) and nominal wall thickness (T.sub.N) data; generating a machining path by determining a target outer airfoil form (40.sub.T), the target outer airfoil form (40.sub.T) being generated by adapting the nominal outer airfoil form (40.sub.N) such that a nominal wall thickness (T.sub.N) is maintained at all points on the outer wall around the one or more internal cooling passages (28) in a subsequently machined airfoil section; and machining an outer surface (18a) of the airfoil section (12) produced by the casting process according to the generated machining path, to remove excess material to conform to the generated target outer airfoil form (40.sub.T).

A milling device for machining a slot into an inner surface of a casing for a gas turbine engine. The milling device includes a frame assembly including multiple structural guides configured to engage structural features on the inner surface of the casing to maintain an axial position of the milling device relative to a longitudinal axis of the casing. The milling device also includes a milling cutter coupled to the frame assembly. The milling device is configured to be displaced in a circumferential direction relative to the longitudinal axis to machine the slot, via the milling cutter, along the inner surface of the casing in the circumferential direction.

A manufacturing method of an impeller, the manufacturing method includes: a step of forming an impeller shaped body in which a disc component part constituting a part of the disc, a blade component part constituting a part of the blade, and a cover component part constituting a part of the cover are integrated by laminating a metal layer to extend toward an outer side in a radial direction with respect to the axis by an additive manufacturing method using a metal powder; and a step of grinding the impeller shaped body, in which the steps are repeated a plurality of times, and the step of grinding the impeller shaped body includes a step of polishing an inner surface of the impeller shaped body constituting a part of the flow path.

The present invention concerns a metal reinforcement for a turbomachine blade comprising an aerodynamic surface which extends between a leading edge and a trailing edge, the reinforcement comprising a base (21) forming its leading edge (20) and being extended by two lateral fins (22, 23) so as to define an inner surface capable of receiving the leading edge of the blade, the method comprising the following steps: (a) obtaining at least two parts each forming at least one of the fins of the reinforcement, each part being integral and finished, at least one of the parts being produced by machining a metallic blank; (b) assembling the parts, previously positioned on a tool (8), by a technique of fusion welding or friction stir welding in order to obtain the reinforcement.

An impeller includes a plurality of pressurizing flow paths defined by a hub, a shroud, and vanes, the pressurizing flow paths being configured to cause fluid to flow in from a shaft direction of a turbine shaft, and cause the fluid to flow out toward an outer side in a radial direction of the turbine shaft, and the pressurizing flow paths being arranged in a row in a circumferential direction of the turbine shaft. Each of the pressurizing flow paths is a through hole having an inlet and an outlet and penetrating from the inlet to the outlet in a linear manner. The inlet is on an end surface of the impeller in the shaft direction of the turbine shaft. The outlet is on an outer circumferential surface of the impeller on an outer side in the radial direction of the turbine shaft.

A method of controlling an extent of a thermal barrier coating (TBC) sheet spall and a hot gas path (HGP) component are disclosed. The method provides an HGP component having a body with an exterior surface. Controlling the extent of the TBC sheet spall includes forming a TBC over a selected portion of the exterior surface of the body. The TBC includes a plurality of segments in a cellular pattern. Each segment is defined by one or more slots in the TBC, and each segment has a predefined area such that the extent of the TBC sheet spall is limited by the predefined area of each of the plurality of segments that constitute the TBC sheet spall.

A tool for a slot in a gas turbine engine, according to an example of the present disclosure, includes a head configured to be received in the slot, a first pad removably bonded to the head with an adhesive, and a second pad removably bonded to the head with an adhesive and disposed opposite from the first pad.

In a method for manufacturing a turbine engine element such as a blade or vane, the element has an airfoil. The method includes: applying a load across an assembly of a first cast portion of the airfoil and a second cast portion of the airfoil; and applying current across a junction of the first cast portion and the second cast portion to fuse the second cast portion to the first cast portion.

A gas turbine engine includes a compressor, a combustor, and a turbine arranged around an axis. The turbine includes a turbine vane assembly. A method for creating the turbine vane assembly includes fabricating a plurality of turbine vanes comprising ceramic matrix composite material and selecting and arranging the turbine vanes to form a turbine vane assembly.

A manufacturing method of an impeller, the manufacturing method includes: a step of forming an impeller shaped body in which a disc component part constituting a part of the disc, a blade component part constituting a part of the blade, and a cover component part constituting a part of the cover are integrated by laminating a metal layer to extend toward an outer side in a radial direction with respect to the axis by an additive manufacturing method using a metal powder; and a step of grinding the impeller shaped body, in which the steps are repeated a plurality of times, and the step of grinding the impeller shaped body includes a step of polishing an inner surface of the impeller shaped body constituting a part of the flow path.