Methods for manufacturing a tandem guide vane segment that includes an outer platform, a front guide vane, and a rear guide vane, wherein the front guide vane and the rear guide vane are arranged in a firmly fixated manner with respect to one another. One method includes manufacturing an integral front segment section that includes the front guide vane and a front section of the outer platform, manufacturing an integral rear segment section that includes the rear guide vane and a rear section of the outer platform, and connecting the two segment sections to each other.

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.

A method and apparatus for the refurbishment and repowering of wind turbines through the extension of existing installed blades so that they can catch more wind energy and therefore enable an increase in the overall average power output of the wind turbine.

An exemplary shroud milling method includes milling a convex side of a shroud, milling a concave side of the shroud, and holding a shroud within a common fixture when milling the convex side and when milling the concave side.

A forming tool for forming leading edges of turbine blades is disclosed. In various embodiments, a forming tool may comprise a cylindrically-shaped body having a notch around the circumference of the cylindrically-shaped body. The notch may be positioned perpendicularly to a center axis of the cylindrically-shaped body. Further, the notch may have a notch contour with an upper notch contour and a lower notch contour, and where the notch contour is a relief of a selected turbine blade leading edge. The forming tool may be a grinding tool or a cutting tool. Moreover, a forming process may comprise forming, by a forming tool, a first portion of a turbine blade leading edge with a rough edge result, and forming, by a milling cutter, a second portion of the turbine blade leading edge with a rough edge result.

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 method for the construction of bladed rings for radial turbomachines, including: preparing an annular block; roughing the annular block by removing material to define a first, second, third and fourth axial section, wherein the first axial section defines a reinforcement ring, wherein the third axial section defines a base ring; roughing the second axial section by removing material to delimit a plurality of separate elements, wherein the separate elements axially connect the base ring to the reinforcement ring; finishing each of the separate elements by removing material to provide the separate element with the shape of an airfoil blade, wherein a leading edge of the blade and a trailing edge of the blade develop substantially parallel to a central axis of the bladed ring; roughing the fourth axial section by removing material for delimiting an annular anchoring appendage of the base ring to a radial turbomachine.

A forming tool for forming leading edges of turbine blades is disclosed. In various embodiments, a forming tool may comprise a cylindrically-shaped body having a notch around the circumference of the cylindrically-shaped body. The notch may be positioned perpendicularly to a center axis of the cylindrically-shaped body. Further, the notch may have a notch contour with an upper notch contour and a lower notch contour, and where the notch contour is a relief of a selected turbine blade leading edge. The forming tool may be a grinding tool or a cutting tool. Moreover, a forming process may comprise forming, by a forming tool, a first portion of a turbine blade leading edge with a rough edge result, and forming, by a milling cutter, a second portion of the turbine blade leading edge with a rough edge result.

A guide 2 for a burr cutter 34, the guide 2 comprising: a body portion 4 having first and second guide surfaces 12a, 12b which are spaced from one another to define a slot 14 between the first and second guide surfaces 12a, 12b; a bearing 32a, 32b for rotatably mounting the body portion 4 to a shank 38 of the burr cutter 34 with a cutting head 36 of the burr cutter 34 adjacent the slot 14; wherein the first and second guide surfaces 12a, 12b and the bearing 32a, 32b are positioned relative to one another such that the first and second guide surfaces 12a, 12b are tangential to the cutting head 36 of the burr cutter 34.

A method of removing material from an airfoil includes engaging a root of the airfoil within a root-securing fixture, engaging a tip of the airfoil within a tip-securing fixture, and removing material from the airfoil. The method further includes disengaging the tip of the airfoil from the tip-securing fixture to allow movement of the tip from a clamped state position to a free-state position. The method further includes reengaging the tip of the airfoil within the tip-securing fixture in the free-state position, and removing additional material from the airfoil.