A method for cutting machining of turbine blades (1) on a multi-axis machine tool, the turbine blade (1) is held by a rotatable blade-root clamping device and a rotatable blade-tip clamping device (2) and is machined by means of a tool which is chucked in a tool spindle. A first profile section (4) which is adjacent to the blade tip is first of all machined by the tool and the tool is then removed. The tool spindle then grabs an already horizontal additional clamping device (5) which has clamping jaws (6.1, 6.2) adapted to the first profile section (4). The additional clamping device (5) is positioned on the blade-tip clamping device (2) in such a way that the clamping jaws (6.1, 6.2) rest in the first profile section (4). The tool spindle then grabs a tool and machines the remaining profile section with it.

A double-row slot plunge milling processing method for integral impellers, which comprises planning a double-row plunge milling cutter path along two side blades of an impeller flow channel; a cutter arrangement sequence of the cutter path following the direction of an inlet and outlet of the flow channel; determining cutter diameter according to the width of a bottom portion of a cross-section of the flow channel and segmenting the flow channel, the width of a bottom portion of the cross-section of each segmented flow channel being greater than one times the cutter diameter and smaller than two times the cutter diameter. Compared with existing methods for layer cutting of high feed, the present invention can increase rough-processing efficiency of integral impellers by more than 50%, while facilitating the elimination of plunge milling cutter bumping, and effectively reducing redundant cutter paths; the implementation process being simple and facilitating CAM software integration.

A double-row slot plunge milling processing method for integral impellers, which comprises planning a double-row plunge milling cutter path along two side blades of an impeller flow channel; a cutter arrangement sequence of the cutter path following the direction of an inlet and outlet of the flow channel; determining cutter diameter according to the width of a bottom portion of a cross-section of the flow channel and segmenting the flow channel, the width of a bottom portion of the cross-section of each segmented flow channel being greater than one times the cutter diameter and smaller than two times the cutter diameter. Compared with existing methods for layer cutting of high feed, the present invention can increase rough-processing efficiency of integral impellers by more than 50%, while facilitating the elimination of plunge milling cutter bumping, and effectively reducing redundant cutter paths; the implementation process being simple and facilitating CAM software integration.

A method for the in-situ reconditioning of a heavy workpiece mounted on the floor. The method comprises assembling a jig mounted on the floor so as to be arranged around the workpiece to be reconditioned, that is also mounted on the floor, the jig supporting a gantry at the two ends of same, on which there is mounted a precision robotic arm carrying at least one machining apparatus. The method also comprises the alignment of the workpiece and the jig using a precision laser alignment tool in order to allow the jig, the gantry and the robotic arm to form a precision machining apparatus. The method also comprises the reconditioning of the workpiece using the precision machining apparatus.

A method for the in-situ reconditioning of a heavy workpiece mounted on the floor. The method comprises assembling a jig mounted on the floor so as to be arranged around the workpiece to be reconditioned, that is also mounted on the floor, the jig supporting a gantry at the two ends of same, on which there is mounted a precision robotic arm carrying at least one machining apparatus. The method also comprises the alignment of the workpiece and the jig using a precision laser alignment tool in order to allow the jig, the gantry and the robotic arm to form a precision machining apparatus. The method also comprises the reconditioning of the workpiece using the precision machining apparatus.

A rotor disk includes a web that extends in a radial direction from a rim on a radially outer end to a bore on a radially inner end. The web includes a mismatch protrusion on a first axially facing surface of the web. A balancing protrusion is on a second axially facing surface of the web.

A rotor disk includes a web that extends in a radial direction from a rim on a radially outer end to a bore on a radially inner end. The web includes a mismatch protrusion on a first axially facing surface of the web. A balancing protrusion is on a second axially facing surface of the web.

The invention relates to a method and to system for producing blades (1) of a machine interacting with a fluid, in particular a fluid-driven machine, in particular a wind turbine, comprising an examination device (19) for determining geometric deviations (A, B, C, D, E, F) from a target shape for one or more shaped blades (1), a device (21) for determining a deviation evaluation of one or more determined geometric deviations from the target shape for each blade with respect to the aerodynamic and/or mechanical consequences thereof, a device (23) for assigning one or more corrective measures (100, 101, 102), each including an expenditure evaluation (100, 101, 102), to one or more determined geometric deviations (A, B, C, D, E, F) from the target shape for each blade, and a linking device (24) for linking a deviation evaluation that was determined for one or more of the determined geometric deviations to the expenditure evaluation for one or more determined corrective measures and for determining the corrective measures to be carried out from the result of the linkage.

The invention relates to a method and to system for producing blades (1) of a machine interacting with a fluid, in particular a fluid-driven machine, in particular a wind turbine, comprising an examination device (19) for determining geometric deviations (A, B, C, D, E, F) from a target shape for one or more shaped blades (1), a device (21) for determining a deviation evaluation of one or more determined geometric deviations from the target shape for each blade with respect to the aerodynamic and/or mechanical consequences thereof, a device (23) for assigning one or more corrective measures (100, 101, 102), each including an expenditure evaluation (100, 101, 102), to one or more determined geometric deviations (A, B, C, D, E, F) from the target shape for each blade, and a linking device (24) for linking a deviation evaluation that was determined for one or more of the determined geometric deviations to the expenditure evaluation for one or more determined corrective measures and for determining the corrective measures to be carried out from the result of the linkage.

A turbocharger impeller is provided with a hub portion with a plurality of vane portions extending outwardly thereof. The hub portion is substantially shaped as a truncated cone with a diameter that gradually increases along a rotation axis. The vane portions are formed on a surface of the hub portion and guide a fluid flowing along the rotation axis radially outward relative to the hub portion. Grooves are formed in and/or on surfaces of the vane portions along a direction of the fluid flowing radially outward during rotation of the impeller. Protruding crest portions are formed between adjacent grooves. Crest portions in a central region near the rotation axis are lower in height than crest portions in an outer region further away from the rotation axis.