When a closed type impeller is manufactured from one block, a rough cutting process of cutting a flow path region of a block using a rough cutting tool, and a residue-cutting process of cutting a cutting residue in the cutting process using a residue-cutting tool are executed. The residue-cutting tool has a tool main body having a blade formed on an outer periphery thereof, and a handle having the tool main body fixed to a distal end thereof. A maximum outer diameter of the tool main body is larger than a minimum outer diameter of the handle. Further, the tool main body has a rear blade directed in a direction including a tool rear side component.

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 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 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 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 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 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 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.