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.

A method for deburring an aeronautical part with an articulated tooling including a plurality of axes of rotation, the aeronautical part including at least one edge to be deburred, the articulated tooling including a tool holder, holding a calibration tool and a machining tool, the calibration tool and the machining tool being fixed to the tool holder and being immovable relative to one another, the method including steps of calibrating the calibration tool and the machining tool, of parameterizing the aeronautical part, of deburring the at least one edge to be deburred with the machining tool moving along a predetermined trajectory, on the basis of the parameters obtained during the parameterization step.

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.

Disclosed herein is a duplicator assembly for forming a first void, which can be layered, in a laminated material of a part that matches a second void in a scarf repair guide. The duplicator assembly comprises an arm that comprises a first end portion and a second end portion. The first end portion is spaced apart from the second end portion. The duplication assembly also comprises a probe that is fixed to the first end portion of the arm and configured to trace the second void in the scarf repair guide. The duplication assembly further comprises a milling tool that is fixed to the second end portion of the arm such that the milling tool is co-movably coupled with the probe via the arm.

In one example, an on-wing method for in-situ cutting on a wing-to-fuselage attachment includes attaching a first mount plate having a first linear bearing to provide movement in a first linear direction relative to the first mount plate, attaching a second mount plate having a second linear bearing to provide movement in a second linear direction relative to the second mount plate, attaching a tool mounting member to the second linear bearing to move with the second linear bearing, attaching a cutter to the tool mounting member to be adjustable relative to the second linear bearing, adjusting a depth position of a cut to be made on the wing-to-fuselage attachment, adjusting a width position of the cut, and moving the tool along a length direction of the cut to make the cut on the wing-to-fuselage attachment along the length direction at the adjusted depth position and the adjusted width position.

The present invention is to eliminate formation of a shape that induces reduction of fatigue strength, without forming a step part, in a shape portion formed by machining. This processing apparatus includes end mills having bottom blades formed in a curved convex shape, and arcuately formed radial blades provided in corner areas; a drive section for driving the end mills; and a control unit for controlling the drive unit. The control unit includes a planar-shape-formation unit that controls the drive unit so as to form, in a workpiece, only a planar-shape portion adjacent to a fillet shape portion in such a manner that a portion of the shape to be processed corresponding to the fillet shape portion is left unprocessed; and a fillet formation unit that controls the drive unit so as to form the fillet shape portion in the workpiece in a single pass using the radial blades.

Disclosed herein is a duplicator assembly for forming a first void, which can be layered, in a laminated material of a part that matches a second void in a scarf repair guide. The duplicator assembly comprises an arm that comprises a first end portion and a second end portion. The first end portion is spaced apart from the second end portion. The duplication assembly also comprises a probe that is fixed to the first end portion of the arm and configured to trace the second void in the scarf repair guide. The duplication assembly further comprises a milling tool that is fixed to the second end portion of the arm such that the milling tool is co-movably coupled with the probe via the arm.

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 combination cutting and burnishing orbital drilling tool may include an elongate tool body including a cutting end and extending along a longitudinal axis. The tool body may include a burnishing portion spaced from the cutting end and configured to induce residual stress in a side wall of a hole without removing material. The tool body may further include a cutting portion interposed between the cutting end and the burnishing portion. The cutting portion may be configured to remove material from a workpiece, thereby creating the hole, during an orbital drilling process.

A magnetorheological support method for blisk processing is disclosed. In the method, a fork structure and a soft film are used to wrap magnetorheological fluid. The magnetorheological fluid is used for flow filling under certain pressure. The bulged soft film can conduct shape matching on the surface of a blisk blade. The magnetorheological fluid can be cured through magnetic field excitation, thereby ensuring the flexible support for a weak rigid component. Electric permanent magnets are symmetrically arranged at both ends of the fork structure to construct a uniform magnetic field that can realize a global excitation of magnetorheological fluid, so that the magnetorheological fluid works in a shear mode to achieve damping force controlling by magnetic field. The solid-liquid conversion of the magnetorheological fluid is controlled by an electric permanent magnet field.