An orbital drilling device includes, on the same frame: a motor rotating a cutting tool on itself; a first, interior, eccentric, receiving the motor, mounted so as to be able to rotate; a second, exterior, eccentric, receiving the first eccentric, mounted so as to be able to rotate; a reference body, secured to the frame, receiving the second eccentric, mounted so as to be able to rotate; a first unit for driving the first eccentric; a second unit for driving the second eccentric, simultaneously with the rotation of the first eccentric; and a controller configured to reproduce any path of the cutting tool in the zone by continuous control of the angular offset between the first eccentric and the second eccentric.

A method of manufacturing a metallic rotor of an eccentric screw pump, comprising clamping a workpiece extending along a central longitudinal axis in a workpiece clamping device and removing material from the workpiece by cutting with a cutting tool. The invention further comprises not producing the surface of the rotor in a three-axis whirling process, using the cutting tool to produce the outer surface geometry of the rotor, advancing the cutting tool along an axis of advance that is parallel to the longitudinal axis of the rotor, and rotating the cutting tool about an axis of tool rotation that is parallel to the longitudinal axis of the rotor.

A cracker roller disc has a first portion radially outward of the centre of substantially constant thickness, and a second portion radially outward of the first portion which second portion tapers towards the periphery of the disc. A plurality of upstanding ridges extending radially outward across the second portion on opposed faces of the disc are machined to define respective conical surfaces forming radially extending edges on opposed faces of the disc. The disc is provided with one or more circular or spiral grooves which cut across the edges in a substantially perpendicular direction to the edges. The grooves extend the effective length of each edge.

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 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 tool for shaping an abradable liner of a turbofan engine is disclosed. The turbofan engine includes a shaft to support a fan rotatable about a rotation axis. The abradable liner is configured to surround the fan and has an axial length in the direction of the rotation axis. The tool includes a support configured to be mounted to the shaft and rotatable about the rotation axis. The shaping head is mounted to the support for rotation about the rotation axis and configured to shape the abradable liner by removing material from the abradable liner. A radial position of the shaping head is adjustable relative to the rotation axis. The shaping head may sized to extend substantially across the axial length of the abradable liner.

A tool for shaping an abradable liner of a turbofan engine is disclosed. The turbofan engine includes a shaft to support a fan rotatable about a rotation axis. The abradable liner is configured to surround the fan and has an axial length in the direction of the rotation axis. The tool includes a support configured to be mounted to the shaft and rotatable about the rotation axis. The shaping head is mounted to the support for rotation about the rotation axis and configured to shape the abradable liner by removing material from the abradable liner. A radial position of the shaping head is adjustable relative to the rotation axis. The shaping head may sized to extend substantially across the axial length of the abradable liner.

A turbomachine modification apparatus includes a machining device, and a machining device mount attached to the machining device. The machining device mount is configured to radially and axially adjust a position of the machining device. A blade mount is configured to be attached to one or more turbomachine blades. The blade mount is attached to the machining device mount.

An example end mill includes a shaft, a cutting head positioned on one end of the shaft, and an edge relief cutting head positioned on the shaft spaced apart from the cutting head. The portion of the shaft between the cutting head and the edge relief cutting head has a diameter that is less than the diameters of the cutting head and the edge relief cutting head. The end mill is rotated around a longitudinal axis of the end mill and revolved around a central axis of a hole to be cut, with the longitudinal axis radially offset from the central axis, to cut the hole with the cutting head and cut an edge relief in a leading edge of the hole with the edge relief cutting head.

A system for machining an abradable material of a gas turbine engine and associated methods. The system includes a frame including a first arm extending from a central location. The system further includes an attachment structure coupled to the frame at the central location. Moreover, the attachment structure is configured to couple to at least a fan rotor of the gas turbine engine. Additionally, the system includes a cutting apparatus coupled to a first distal end of the first arm opposite the central location. The cutting apparatus includes a rotating shaft and plurality of cutting disks coupled to the rotating shaft. Further, the plurality of cutting disks define a helical cutting profile configured to machine a contour within the abradable material complementary to at least one fan blade of the gas turbine engine.