A device for recontouring a gas turbine blade includes: a holding device having at least one cutting tool; and a guide configured to guide the cutting tool along a leading edge of the gas turbine blade. The cutting tool is configured to remove material from the gas turbine blade using a rotational movement about an axis of rotation. The axis of rotation forms an angle together with a chord of the gas turbine blade in a profile section plane, which extends perpendicularly to a radial extent of the gas turbine blade, and the angle is less than 45°.

A belt grinding apparatus for grinding the tips of rotor blades supported on a rotating rotor. A casing contains the rotatable rotor. An opening in the casing permits access of a grinding belt into the casing where the belt grinds the tips of the blades rotating past. The belt grinding apparatus being attached at the opening at a parting line in the casing.

Provided is a grinding machine for processing a sweep edge of a rotor blade, including a grinding unit with a driven grinding tool, a workpiece receiving device which is designed for receiving a rotor blade to be ground, and a workpiece drive unit which is configured for moving the workpiece receiving device, with a rotor blade received thereon, relative to the grinding tool for the purpose of machining the sweep edge, wherein the workpiece drive unit has a pivot axis at which the workpiece receiving device is held in such a way that the sweep edge of a rotor blade received thereon is engaged with the grinding tool in the course of a pivot movement of the workpiece receiving device about the pivot axis.

The invention relates to a grinding tool for grinding a leading edge of a wind turbine blade. It comprises two parallel shafts of which at least one is rotationally driven and a frame for holding the two shafts in a fixed mutual relationship. An annular abrasive belt is arranged around a tension device mounted to the frame and guides of which there is one on each of the two shafts. The abrasive belt runs in a plane perpendicular to the shafts and has a longer length than an imaginary curve formed by outer surfaces of the tension device and of the guides. The grinding tool further comprises two abrasive belt retainers movably mounted to the frame. They are shaped and arranged to move between a retaining position in which they retain the abrasive belt along at least parts of the abrasive belt which is in contact with the guides, and a release position in which they are out of contact with the abrasive belt.

A belt grinding apparatus for grinding the tips of rotor blades is supported on a rotating rotor. A casing contains the rotatable rotor. An opening in the casing permits access of a grinding belt into the casing where the belt grinds the tips of the blades rotating past. The belt grinding apparatus is attached at the opening at a parting line in the casing.

An apparatus for machining an object includes a wheel having a first circular surface, a second circular surface oriented parallel to the first circular surface, a first rim surface extending from the first circular surface at a first edge, and a second rim surface extending from the second circular surface at a second edge and towards the first rim surface. A gradient of the first rim surface has a radial component, and a gradient of the second rim surface has a radial component. The first edge defines a curved surface between the first circular surface and the first rim surface, and the second edge defines a curved surface between the second circular surface and the second rim surface.

A manufacturing method is provided that includes controlling a robotic polishing device, at a controller, to polish a plurality of first zones of a bladed rotor for an aircraft engine based on a first operating parameter associated with the robotic polishing device. An exterior of the bladed rotor includes the first zones and a plurality of second zones. The first zones are distributed circumferentially about an axis of the bladed rotor in a first array. The second zones are distributed circumferentially about the axis of the bladed rotor in a second array. The method further includes controlling the robotic polishing device, at a controller, to polish the second zones using the robotic polishing device based on a second operating parameter. The second operating parameter for the robotic polishing device is different than the first operating parameter.

The present invention provides an apparatus and method for processing a component surface by abrading the component surface using an abrasive surface. The apparatus comprises an abrasive surface which is rotatable about an axis extending parallel to said component surface. A support is provided for moving the abrasive surface or the component surface along a computer-generated toolpath and for applying a force between the abrasive surface and the component surface. The support increases the force between the abrasive surface and the component surface from a minimum force to a maximum force as the distance along the toolpath increases to maintain constant material removal from the component surface.

A device and method for the setup, alignment and calibration of grinding machines is disclosed. A tool (42c) is described, comprising a bar (44) and a first location feature (48) located on the bar (44) and configured to engage with a first location of a machine. The tool also provides a datum (66) located at a known but variable distance parallel to the bar (44) from the first location feature (48). A method for calibrating a grinding machine using the tool (42c) is also described.

A device for recontouring a gas turbine blade includes: a holding device having at least one cutting tool; and a guide configured to guide the cutting tool along a leading edge of the gas turbine blade. The cutting tool is configured to remove material from the gas turbine blade using a rotational movement about an axis of rotation. The axis of rotation forms an angle together with a chord of the gas turbine blade in a profile section plane, which extends perpendicularly to a radial extent of the gas turbine blade, and the angle is less than 45?.