In one example, an on-wing apparatus for in-situ cutting on a wing-to-fuselage attachment includes a first linear bearing disposed on a first mount plate to move in a first direction. A second linear bearing is disposed on a second mount plate to move in a second direction. The second mount plate is attached to the first linear bearing. A tool mounting member is attached to the second linear bearing. A cutter is attached to the tool mounting member to be adjustable, relative to the second linear bearing, in a rotational direction around an adjustment axis. One of the first direction and the second direction is a depth direction of the cut parallel to the adjustment axis, and the other is a length direction of the cut. A width position of the cut is determined by rotational adjustment of the cutter with respect to the second linear bearing in the rotational direction.

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.

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.

Dual cutting milling tools for removing material from a workpiece include two cutting portions, with one cutting portion being configured for ruled milling, and the other cutting portion being configured for hemstitch milling. In this manner, the number of tool changes for a given manufacturing process may be reduced. Dual cutting milling tools include a first cutting portion and a second cutting portion both formed in a shank, with the first cutting portion being configured to perform hemstitch milling on the workpiece, and the second cutting portion being configured to perform ruled milling on the workpiece. Methods of removing material from a workpiece may include both hemstitch milling the workpiece with the first cutting portion of the dual cutting milling tool and performing ruled milling of the workpiece with the second cutting portion of the dual cutting milling tool, without changing tools in the milling machine.

An orbital drill includes a drilling portion, a shank portion, and a neck portion between the drilling portion and the shank portion. The drilling portion includes one or more right-handed spiral flutes with cutting edges having a positive axial rake angle for positive cutting action while orbiting into a material. The right-handed spiral flutes have a positive radial and axial rake angle. The drilling portion also includes one or more left-handed spiral flutes located rearward of the one or more right-handed spiral flutes with cutting edges having a positive axial and radial rake angle for positive cutting action while orbiting back out of the material and removing any material left in the hole, thereby eliminating a separate reaming operation. A method of machining a workpiece using the orbital drill is also disclosed.

This processing device is provided with: a tool for machining a workpiece W along the thickness direction thereof, the width-direction external shape of the workpiece W being substantially finished; and a flexible vice 7 that clamps the workpiece W in the width direction without clamping the workpiece W in the thickness direction. The flexible vice 7 is provided with a position adjustment mechanism that prevents the position of the workpiece W from changing in a plane along the width direction before and after the workpiece W is clamped. The present invention is provided with a rough processing tool for performing processing at a rough-processing position, a finishing processing tool for performing processing at a finishing-processing position, and a control unit that causes the position adjustment mechanism to move between the processing performed by the rough processing tool and the processing performed by the finishing processing tool.

A method of machining an attachment flange of an aircraft turbomachine case, the method also including a system to machine the two opposite surfaces of the flange, and including a shape follower machining module, this module being designed to follow the shape of the flange and including a first structure equipped with a first machining tool, and a second structure equipped with a second machining tool, the flange fitting between the structures such that its two opposite surfaces are machined by tools, the module also including shape follower elements carried by the structures; and a device to drive movement of the machining module along a circumferential direction of the flange.

Certain embodiments of the present disclosure provide an acoustic inlet barrel of an engine. The acoustic inlet barrel may include an inner barrel configured to provide a boundary for directing airflow through the engine. The inner barrel may include an inner face sheet separated from an outer face sheet by an acoustic core. The inner barrel may include a plurality of elongated, non-circular perforations formed through the inner face sheet.

An orbital drill includes a drilling portion, a shank portion, and a neck portion between the drilling portion and the shank portion. The drilling portion includes one or more right-handed spiral flutes with cutting edges having a positive axial rake angle for positive cutting action while orbiting into a material. The right-handed spiral flutes have a positive radial and axial rake angle. The drilling portion also includes one or more left-handed spiral flutes located rearward of the one or more right-handed spiral flutes with cutting edges having a positive axial and radial rake angle for positive cutting action while orbiting back out of the material and removing any material left in the hole, thereby eliminating a separate reaming operation. A method of machining a workpiece using the orbital drill is also disclosed.

An edge break apparatus including a frame having a first workpiece interface surface, a second workpiece interface surface arranged relative to the first workpiece interface surface so as to form a predetermined angle between the first workpiece surface and the second workpiece surface, and a first aperture extending through the frame so as to intersect the predetermined angle, and an edge break member extending through and interfaced with the first aperture so as to adjustably define a cutting depth of the edge break member relative to an apex of the predetermined angle.