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°.

The invention refers to a method for machining a blade and a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade. The shroud has an outer surface with at least one circumferential fin arranged thereon, whereby at least one section of the outer surface beside the at least one fin is processed in at least two manufacturing steps. At least one first section of the outer surface is processed to have a first shape and at least one second section of the outer surface is processed to have a second shape.

A method for manufacturing a thin-walled part having curved surfaces, in particular a turbine blade by a machine tool comprising roughing process and semi-finishing process. At least one of the roughing process and the semi-finishing process is accomplished by flank milling.

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 method of manufacturing an aerodynamic element with an edge is provided. The method includes producing the aerodynamic element with an initial condition, cooling the aerodynamic element, generating a predefined number of data points sufficient to characterize contours of the edge and comparing the data points to a nominal condition to derive transformation parameters applicable to cutting toolpaths to adapt the cutting toolpaths to the initial condition.

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 processed article is manufactured with a tool including a cutting blade. The cutting blade is arranged to be in contact with two machined segment surfaces so that two contact points are defined between the two machined segment surfaces and the cutting blade in a corner. A machining pitch is set in a pick feed direction of the tool at the corner to a first machining pitch for when a part of the cutting blade corresponding to a projected shape of a side surface of the cutting blade having a first curvature radius is a cutting point. A cut is performed along a feed direction in the two adjacent machined segment surfaces successively at the corner so that the tool proceeds toward the corner in one of the machined segment surfaces and away from the corner in the other one of the machined segment surfaces.

A method for milling a workpiece by way of at least one substantially polygonal cutting insert, which is arranged in a tool holder. A spindle axis of the tool holder encloses an angle of more than 0 with a plane normal to a machined workpiece surface. An effective lead angle between a main cutting edge of the cutting insert and the machined workpiece surface lies between 0 and 20.

After a free-form surface is machined on an elongated material 1 with a projection 3 and a blade root 4 held, the holding of the projection 3 is released to release strain generated during machining. Upon release of the holding, the entire elongated material 1 deforms, and the projection 3 moves from a holding position A to a strain-released position B. A re-holding position C obtained by correcting the position B by the deformation amount of the elongated material 1 due to the weight of the elongated material 1 is determined, and the projection 3 is held again at the re-holding position C for further machining the free-form surface on the elongated material 1.

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.