An EDM machine includes a machine head, a wire guide, a machining wire extending from the wire guide to the machine head, a rotary table mounted to a first surface and a fixed table mounted to the rotary table, and a fixture mounted to the fixed table. The fixture includes a mounting portion substantially circumscribing the fixture. The mounting portion further includes a mounting surface. The mounting surface is closer to a first surface than an upper surface of the fixed table.

A method for restoring a blade or vane platform of a gas turbine assembly configured for a power plant by: providing a blade or a vane having a platform with an edge deterioration zone; removing the deterioration zone electro discharging machining technology; and rebuilding a removed zone by additive manufacturing technology. The removing can be performed to create a recessed plane along a platform edge, the recessed plane being connected to a platform plane by an enter inclined plane and an exit inclined plane arranged opposed along the platform edge.

A method for restoring a blade or vane platform of a gas turbine assembly configured for a power plant by: providing a blade or a vane having a platform with an edge deterioration zone; removing the deterioration zone electro discharging machining technology; and rebuilding a removed zone by additive manufacturing technology. The removing can be performed to create a recessed plane along a platform edge, the recessed plane being connected to a platform plane by an enter inclined plane and an exit inclined plane arranged opposed along the platform edge.

A component for a gas turbine engine is described. The component may comprise a body portion formed from a metallic material. The component may further comprise an abrasive surface forming at least one surface of the body portion, and the abrasive surface may be configured to abrade an abradable material. The abrasive surface may be formed from electrical discharge machining of the metallic material.

The present invention is directed to a method for producing a rotating disk for a turbomachine, forming blade root uptakes on a plurality of circumferential positions, for which, in each case, an axially extending profile groove that is bounded circumferentially by inner wall surfaces of the rotating disk is introduced on a respective circumferential position, in which production method, initially first profile grooves are introduced in a disk on first circumferential positions, and subsequently, a second profile groove is introduced in the disk on a second circumferential position located circumferentially between the first profile grooves.

Tooling (10) for making slots in a multistage disk (1) by electrochemical machining. The tooling comprises first and second rings (20) arranged coaxially about a disk axis and configured to act as cathodes, each ring having an inside periphery with a plurality of radial machining projections. The first and second rings (20) are rigidly secured relative to each other. A method of making slots in a multistage disk by electrochemical machining using such a tool.

Tooling (10) for making slots in a multistage disk (1) by electrochemical machining. The tooling comprises first and second rings (20) arranged coaxially about a disk axis and configured to act as cathodes, each ring having an inside periphery with a plurality of radial machining projections. The first and second rings (20) are rigidly secured relative to each other. A method of making slots in a multistage disk by electrochemical machining using such a tool.

An electrochemical machining device that electrochemically machines a preformed impeller including a plurality of blades arranged along an outer periphery of the impeller. The electrochemical machining device includes a discharge electrode having an electrode surface extending along a machined surface of one of the plurality of blades, and a first nozzle that is disposed adjacently to the discharge electrode and has a first outlet from which electrolyte solution is discharged, the electrolyte solution flowing into a space between the electrode surface and the machined surface along the electrode surface.

The invention relates to a method for manufacturing a turbine engine blade (16) including an active-surface wall (17) and a passive-surface wall (18) separated from one another, this blade (16) including a tip that has a closing wall grouping together the active-surface (17) and passive-surface (18) walls in the region of this tip to define the bottom (23) of a bathtub tip shape located at the tip of the blade, the method comprising a moulding step implementing a core defining the bathtub tip shape. According to the invention, there is a step of adding metal to the bottom (23) of the bathtub tip by means of a Direct Laser Additive Manufacturing (CLAD) method, to deposit material onto the bottom of the bathtub tip to form therein an inner partition (28) supported by the bottom thereof (23).

The invention relates to a method for manufacturing a turbine engine blade (16) including an active-surface wall (17) and a passive-surface wall (18) separated from one another, this blade (16) including a tip that has a closing wall grouping together the active-surface (17) and passive-surface (18) walls in the region of this tip to define the bottom (23) of a bathtub tip shape located at the tip of the blade, the method comprising a moulding step implementing a core defining the bathtub tip shape. According to the invention, there is a step of adding metal to the bottom (23) of the bathtub tip by means of a Direct Laser Additive Manufacturing (CLAD) method, to deposit material onto the bottom of the bathtub tip to form therein an inner partition (28) supported by the bottom thereof (23).