A high-speed precision interrupted ultrasonic vibration cutting method includes steps of: (1) installing an ultrasonic vibration apparatus on a machine tool, and stimulating a cutting tool to generate a transverse vibration, so as to realize varieties of machining processes; (2) realizing an interrupted cutting process by setting cutting parameters and vibration parameters to satisfy an interrupted cutting conditions; and (3) turning on the ultrasonic vibration apparatus and the machine tool, and starting a high-speed precision interrupted ultrasonic vibration cutting process. High-speed precision interrupted ultrasonic vibration cutting is able to be realized through the above steps during machining of difficult-to-machine materials in aviation and aerospace fields. A cutting speed is enhanced significantly, and exceeds a critical cutting speed of a conventional ultrasonic vibration cutting method and an elliptical ultrasonic vibration cutting method and even a high speed range of a traditional cutting method.

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 vane tip machining fixture assembly includes a first clamp ring mountable to a fixture, the first clamp ring includes a rigid back ring mounted to a resilient ring.

A one-piece cutting tool has a shank portion with a mounting end and a cutting end. The cutting end has a body portion and a substantially hemispherical portion. The cutting end further comprises a plurality of flutes, each flute helically extending adjacent to one another about the cutting end along a length from the body portion to the hemispherical portion. Each flute has a cutting edge divided into a first cutting edge section and a second cutting edge section, the first cutting edge section extending along the body portion and being substantially straight-edged or serrated, and the second cutting edge section extending along the hemispherical portion and being serrated along at least a part of the hemispherical portion. A cutting tool assembly is also provided.

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.

A damper includes a damper body that is configured to be attached to a workpiece during a machining process. A first side of the damper body is configured to abut a first side of the workpiece. The damper body includes a frame forming an outer periphery of the damper body, a plurality of damper nodes with a cavity in each damper node positioned in the frame, and a plurality of ribs extending between the frame and the damper nodes. A damping material is positioned in the cavity of each damper node.

Every junction part for an airplane wing is manufactured with overmaterial. Each part is measured with a laser based interferometer or other scanning technique and the as built measurements are compared with a model to generate a new trajectory milling program to fill or prevent gaps between parts using a points cloud and B-Spline algorithm to generate a new surface to be milled. Once the program is generated (new trajectories) and post processed, it is sent to a milling machine to perform overmaterial milling on already milled parts with overmaterial. This technique can be used to eliminate gaps between junction parts and the corresponding need for shims.

A debris removal apparatus for a milling machine. In one embodiment, the debris removal apparatus includes a hollow, cylindrical suction member that attaches to a tool shaft which holds an end mill to rotate with the tool shaft. The debris removal apparatus further includes a nonrotating canister that applies a suction force to the suction member. The suction member is dimensioned to fit within a hole being cut by the end mill as the end mill is fed into the hole, and to extract debris created by the end mill via the suction force.

A debris removal apparatus for a milling machine. In one embodiment, the debris removal apparatus includes a hollow, cylindrical suction member that attaches to a tool shaft which holds an end mill to rotate with the tool shaft. The debris removal apparatus further includes a nonrotating canister that applies a suction force to the suction member. The suction member is dimensioned to fit within a hole being cut by the end mill as the end mill is fed into the hole, and to extract debris created by the end mill via the suction force.

The invention relates to tooling (24) for machining an annular groove of a turbine engine casing, wherein said tooling (24) comprises a machining tool (25), a baseplate (33), first means of positioning (28) the machining tool (25) in relation to the baseplate (33) along a first axis (Y) forming a radial axis, second means of positioning (30) the machining tool (25) in relation to the baseplate (33) along a second axis (X) perpendicular to the first axis (Y), wherein said second axis (X) extends along the axis of the groove and of the annular casing and third means of positioning capable of positioning the baseplate (33) axially and radially in relation to the groove of the casing.