At least one coordinate value (z1, z2, α1, α2) of a cutting body (35) can be acquired by means of an acquisition device (27) and transferred to the control device (25). This at least one coordinate value (z1, z2, α1, α2) of each cutting body (35) can be used for the rest of the method in the control device (25). This at least one coordinate value (z1, z2, α1, α2) which is determined on the basis of the at least one image (B) can be directly taken into account during the processing of the rotational tool (13). Alternatively or additionally, this at least one coordinate value (z1, z2, α1, α2) which is determined on the basis of the at least one image (B) can be used to determine at least one further coordinate value, in particular using a sensing device (29).

An initial customized electronic work scope is created for an individual industrial asset. The initial electronic work scope is created according to the set of rules defined in the tree-like data structure and uses the determined condition of the asset. The initial customized electronic work scope is not necessarily the same as other work scopes of other industrial assets the same asset type. The initial customized electronic work scope defines an ordered sequence for removing a plurality of individual mechanical parts of the individual asset.

The invention relates to a device (15) and a method (V) for machining a tool (16) by removing material. The tool (16) is first of all measured in three dimensions using a measuring unit (17) and a three-dimensional virtual tool model (M) is produced therefrom. This virtual tool model (M) is compared with a reference contour (R) from a particular tool data record (WD). If a match was determined, a machining program (PR) assigned to the tool data record (WD) is selected and a desired contour (SK) is determined by fitting the reference contour (R) into the three-dimensional virtual tool model (M). The tool (16) can then be machined on the basis of this desired contour (SK).

The invention relates to a device (15) and a method (V) for machining a tool (16) by removing material. The tool is first of all measured in three dimensions using a measuring unit (17) and a three-dimensional virtual tool model (M) is produced therefrom. This virtual tool model (M) is compared with a reference contour (R) from a particular tool data record (WD). If a match was determined, a machining program (PR) assigned to the tool data record (WD) is selected and a desired contour (SK) is determined by fitting the reference contour (R) into the three-dimensional virtual tool model (M). The tool (16) can then be machined on the basis of this desired contour (SK).

The invention relates to a method for repairing an aircraft or gas turbine component, wherein the method comprises the following automated steps: a) checking the component for cracks by means of an optical measurement method, wherein determined geometry and/or damage data are stored with reference to the component, b) generating an adaptive processing strategy on the basis of the determined geometry and/or damage data in a data processing unit, c) machining the component, d) determining the changed geometry data of the component, e) performing repair welding, f) checking the component for cracks by means of an optical measurement method.

Certain embodiments of the disclosure may include systems, methods, and apparatus for locating and drilling closed holes of a gas turbine component. According to an example embodiment, the method can include receiving position data associated with one or more holes in a gas turbine component; receiving predefined hole position data from manufacturing data associated with the gas turbine component; determining at least one missing hole, based at least in part on comparing the received position data to the predefined hole position data; and drilling at least one hole in the gas turbine component corresponding to the determined at least one missing hole.