Methods, systems, and apparatus, including medium-encoded computer program products, for computer aided design and manufacture of physical structures using subtractive manufacturing systems and techniques and a determined stock allowance include, in one aspect, a method including: obtaining a finishing toolpath specification for three dimensional (3D) geometry of a part; generating 3D geometry of a model of a semi-finished structure in accordance with a computer simulation of deflections experienced by a workpiece as stock material is cut from the workpiece using the finishing toolpath specification; creating a semi-finishing toolpath specification for the semi-finished structure; and providing the semi-finishing toolpath specification for use in machining the part by cutting away a first portion of the stock material using the semi-finishing toolpath specification to form the semi-finished structure, followed by performing a finishing operation of the semi-finished structure by cutting away a second portion of the stock material to form the part.

A method of machining a surface of a component. The method comprises scanning the surface of the component to obtain scanned electronic 3D data representing the scanned surface of the component locating a surface defect of the scanned surface and identifying a defect region that surrounds and includes the surface defect, and providing electronic 3D data representing a patch having the desired shape of the defect region. The method also comprises transforming the patch to generate a tooling path for repairing the surface defect. The transformation comprising translating a plurality of nodes of the patch. The translation distance of each node based on the distance of that node from an origin node of the patch. The method further comprises machining the surface of the component according to the generated tooling path.

A system for automated adaptive manufacturing of airfoil castings is disclosed. The system may receive a three dimensional scan of a work piece. The system may compare the three dimensional scan to a digital model of the work piece. The system may identify an area of dimensional abnormality on the work piece based on the comparison. The system may alter the area of dimensional abnormality on the work piece.

Provided is a bilateral ultrasonic rolling processing track coordination method for a blade surface, the method comprising: step S1, performing layering processing on a blade to acquire a contour curve of A-shaped and n-shaped blade edges of a blade model at different heights; step S2: determining the endpoints of a blade processing track; and step S3: planning the thickness and the rotation angle of the blade, comprising: step S31, solving a main direction angle .sub.main of the contour curve; step S32, solving the thickness d of the blade; step S33, solving a rotation angle required by blade processing when the blade edge is A-shaped; and step S34, solving the rotation angle required by blade processing when the blade edge is n-shaped. According to the method, blade deformation generated by an ultrasonic rolling force is reduced, the processing efficiency is improved, and the blade processing precision is also improved.

Provided is a method of manufacturing wind turbine rotor blades, wherein each rotor blade includes an inboard section and an outboard section, and wherein an inboard blade section including a root end and a transition region is manufactured using a first casting process; and an outboard blade section including an airfoil region is manufactured using a second casting process, which second casting process is different from the first casting process. The invention further describes a wind turbine rotor blade manufactured using such a method.

The present relates to a method for automatically determining a finishing recipe of a manufactured component. A non-finished 3D model, consisting in a 3D representation of the manufactured component at a non-finished stage, is received at a computer. And a finished 3D model, consisting in a 3D representation of the manufactured component at a finished stage, is received. The non-finished 3D model and the finished 3D model are further processed, to calculate a finishing recipe of one or more tool(s), The tool performs a finishing operation according to the finishing recipe on the manufactured component at the non-finished stage, to obtain the manufactured component at the finished stage. The finishing recipe may include a trajectory of the tool(s), an operational parameter(s) of the tool(s). The manufactured component may consist in a blade. The finishing operation may consist in profiling, polishing, tri-blending, weld blending, twist and bow.

This disclosure concerns an adaptive repair method, for example for aerofoil blade components. The method generates a digitized model of a physical component and uses data from the digitized model to align a part of the physical component with a nominal CAD model of the component. A combination of the digitized data and data from the nominal CAD model are then used to create an adapted model for repair of the component.

The present invention relates to a method for machine finishing the shape of a blank casting for a multi-vane, in particular bi-vane, nozzle of a turbine engine, comprising a first vane and a second vane extending substantially in a radial direction between two walls that are radially inner and radially outer, respectively, the suction face of the first vane defining, together with the pressure face of the trailing edge of the second vane, a cross section of flow (SP), the method comprising measuring, by means of probing, the position of predefined points on said respectively radially inner and radially outer walls on the surface of the vanes and calculating the machining allowances (1 and 2 respectively) on the first and second vanes with respect to the theoretical profile at said points, wherein the method comprises calculating said cross section of flow (SP) from the height of the duct between said radially inner and radially outer walls, and values of the machining allowances (1 and 2), a correction of the machining allowance (2) on one of the vanes being applied when the calculated value of the cross section of flow (SP) is outside predefined tolerances.

An automated airflow inspection system for airfoil blades or vanes includes an operator station for mounting the airfoil and a robotic station for pressure tapping the airfoil. The robotic station uses a robotic arm with a mounted vision system and pressure tapper. The system is monitored and controlled by a human to machine interface.

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.