A method of reprocessing a metal product includes a welding step for welding a dummy member to the metal product, a reprocessing step for reprocessing the metal product in a state where the metal product is supported by a first support unit and the dummy member is supported by a second support unit, and a removal step for removing the dummy member from the metal product after the reprocessing step. The reprocessing of the metal product while the metal product is fixed is thus enabled without restriction from the shape of the metal product.

A miniaturized turbogenerator (200) to directly provide electrical propulsion (307 308, 309) to small land, air, and maritime vehicles without an intervening electricity storage battery (315). The invention comprises of a process of miniaturization (500) of a turbine engine core (100), in particular its compressors and turbines (400), by means of hyper-feed machining by linear force alone, i.e. without rotation of either the workpiece or the cutting tool (505), and a resulting apparatus of a miniaturized turbogenerator (200) that has sufficient power density to provide high-performance electrical propulsion (310) for commercially feasible automobiles, urban air mobility vehicles, and other small vehicles and vessels with greater performance than battery-electric vehicles (300).

A method for producing an integrally bladed rotor includes providing imaginary front and rear lattice points on the ridges of the front and rear edges; providing a first imaginary line on positive-pressure and negative-pressure surfaces to connect a first imaginary front lattice point and a first imaginary rear lattice point; providing a second imaginary line on the positive-pressure and negative-pressure surfaces to connect a second imaginary front lattice point next to the first imaginary front lattice point and a second imaginary rear lattice point next to the first imaginary rear lattice point; providing a spiral path on the positive-pressure and negative-pressure surfaces by connecting the first and second imaginary lines with a spiral curve; and cutting the positive-pressure and negative-pressure surfaces by moving a cutting point corresponding to a cutting edge of a turning tool along the spiral path. point around the blade.

A method for producing an integrally bladed rotor includes providing imaginary front and rear lattice points on the ridges of the front and rear edges; providing a first imaginary line on positive-pressure and negative-pressure surfaces to connect a first imaginary front lattice point and a first imaginary rear lattice point; providing a second imaginary line on the positive-pressure and negative-pressure surfaces to connect a second imaginary front lattice point next to the first imaginary front lattice point and a second imaginary rear lattice point next to the first imaginary rear lattice point; providing a spiral path on the positive-pressure and negative-pressure surfaces by connecting the first and second imaginary lines with a spiral curve; and cutting the positive-pressure and negative-pressure surfaces by moving a cutting point corresponding to a cutting edge of a turning tool along the spiral path. point around the blade.

A method and apparatus for producing a hole in any material by means of controlled fracturing using non-spindle CNC machining includes the steps of: fixturing a workpiece to the table of a non-spindle CNC holemaking machine tool. The cutting tool is then secured to the column of the machine tool and the face of the cutting tool is positioned perpendicular to the centerline of the proposed hole. The surface of the workpiece is approached with the cutting tool to a predetermined clearance level. Thereafter, the cutting tool is driven with sufficient linear force to induce instantaneous strain in the material of the workpiece to a depth necessary to create a hole of a desired size and shape using a drive mechanism. The cutting tool is then repositioned so that the face of cutting tool is perpendicular to centerline of a subsequent hole to be produced.

The invention relates to a guide vane intended to be arranged in all or part of an air flow of an aircraft bypass turbomachine fan, the vane comprising an aerodynamic part equipped with at least one interior lubricant cooling passage delimited in part by an intrados wall and an extrados wall of the vane, there being flow-disturbing lugs, made as one piece with one of the intrados and extrados walls, passing across the passage. According to the invention, in any plane of section passing orthogonally through the lugs, the space defined between these lugs has a geometry defined exclusively by a set of annulus shapes of the same dimensions, partially overlapping one another and each in part delimiting at least two of these lugs.

Various embodiments include a system for machining a hole in a turbine blade. The system can include: a mount for engaging a first side of a turbine rotor, the mount including: a drill plate for coupling with the first side of the turbine rotor, the drill plate having: a body; a feed opening on a first side of the body; a passage extending from the feed opening through the body; and a second opening on a second side of the body, the second opening coupled with the passage and positioned to align with the pre-formed hole in the turbine rotor; an alignment bushing for engaging the pre-formed hole in the rotor at a second side of the rotor; and a cutting device for extending through the body and alignment bushing, the cutting device for machining the hole in the blade, the cutting device aligned along a chamfer axis relative to a primary axis of the turbine rotor.

A method for processing a CMC airfoil includes nesting an airfoil fiber preform in a cavity of a fixture that has first and second tool segments, closing the fixture by rotating a first tool segment about a hinge, the closing causing the tool segments to clamp on a tail portion of the fiber preform and thereby conform the tail portion to the fixture. While in the fixture, the fiber preform is then partially densified with an interface coating material to form a partially densified fiber preform. While still in the fixture, one or more cooling holes are drilled into the trailing edge of the partially densified fiber preform. After the drilling, the partially densified fiber preform is removed from the fixture and further densified with a ceramic matrix material to form a fully densified CMC airfoil.

A method and apparatus for producing a hole in any material by means of controlled fracturing using non-spindle CNC machining includes the steps of: fixturing a workpiece to the table of a non-spindle CNC holemaking machine tool. The cutting tool is then secured to the column of the machine tool and the face of the cutting tool is positioned perpendicular to the centerline of the proposed hole. The surface of the workpiece is approached with the cutting tool to a predetermined clearance level. Thereafter, the cutting tool is driven with sufficient linear force to induce instantaneous strain in the material of the workpiece to a depth necessary to create a hole of a desired size and shape using a drive mechanism. The cutting tool is then repositioned so that the face of cutting tool is perpendicular to centerline of a subsequent hole to be produced.

According to an aspect of this disclosure, an ultrasonic machining apparatus may include a machining head disposed at an angle, a machining platform for mounting a component, and one or more actuators for imparting ultrasonic vibration on the component wherein the angled machining head operates on the component according to the angle of the machining head, a position of the component, and the ultrasonic vibration.