A method of producing a component having an in use gas washed surface, including: obtaining a reference-component having a reference shape with in use gas washed surface; determining performance-sensitivity-distribution for the reference-component, the performance-sensitivity-distribution having plurality of points, each point indicative of a performance factor for the reference-component; identifying plurality of zones on the reference-component performance-sensitivity-distribution, each zone including at least one plurality of points; setting geometric-tolerance for each zone; manufacturing a component according to the reference-component; machining the manufactured-component outer surface so the manufactured-component surface is within predetermined geometric-tolerance for each reference-component corresponding zone; additionally/alternatively; measuring the manufactured-component geometry to determine whether the manufactured-component is within geometric-tolerance for each corresponding plurality of reference shape zones, and accepting production-component for use if geometry of the production-component is within the geometric-tolerance for each plurality of zones, or rejecting the production-component if the geometry is outside the geometric-tolerance for plurality of zones.

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 (Δ1 and Δ2 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 (Δ1 and Δ2), a correction of the machining allowance (Δ2) on one of the vanes being applied when the calculated value of the cross section of flow (SP) is outside predefined tolerances.

In some examples, an adaptive machining system may include a model comparison unit, a compromise shape determination unit, and a program modification unit. The model comparison unit can be configured to compare electronic measured dimensional surface data of a component with an electronic surface model of the component. The compromise shape determination unit can be configured to determine a compromise shape for the component based on the comparison. The program modification unit can be configured to modify a machine tool program code based on the compromise shape.

Apparatuses for measuring parameters of an object may include an apparatus frame. A rotary table assembly may include a rotary table having a diameter or width and carried by the apparatus frame. The rotary table may be configured to support the object for rotation. A rotary table motor may operably engage the rotary table for rotation. A carriage rail may be carried by the apparatus frame. The carriage rail may be disposed in fixed position relative to the rotary table. A sensor carriage may be carried by and configured to traverse the carriage rail. A carriage drive motor may engage the sensor carriage. The carriage drive motor may be operable to displace the sensor carriage along the carriage rail. At least one displacement sensor may be carried by the sensor carriage. The displacement sensor may have a displacement sensor travel path which passes over and traverses the diameter or width of the rotary table as the sensor carriage traverses the carriage rail. The displacement sensor may be configured to measure distances between the displacement sensor and surfaces on the object. Alternative embodiments of the apparatuses are also disclosed.

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 system for use in performing maintenance on a turbine rotor. The system includes a rotor mount configured to receive the turbine rotor, a robotic device, a visual inspection device removably coupleable to the robotic device, and a computing device. The computing device is configured to direct the robotic device to evaluate, with the visual inspection device, the turbine rotor at different circumferential locations thereof to obtain rotor axis data, determine a centerline of the turbine rotor based on the rotor axis data, generate a coordinate system including the centerline of the turbine rotor, direct the robotic device to evaluate, with the visual inspection device, each blade on at least one stage of the turbine rotor to obtain blade position data relative to the centerline, and populate the coordinate system with the blade position data.

Producing a component having an in use gas washed surface includes: obtaining a reference component having a reference shape with an in use gas washed surface; setting one or more performance threshold for the reference shape, the threshold defining an acceptable performance for the reference shape; obtaining a manufactured component made to the reference shape; measuring the manufactured component and determining a displacement distribution indicative of the geometric deviation of the manufactured component from the reference shape; determining a performance sensitivity distribution for the reference component, the sensitivity distribution having a plurality of points, each point indicative of a performance factor for the reference component; combining the sensitivity distribution and displacement distribution to determine a performance prediction for the manufactured component; determining whether the performance prediction is within the performance threshold; accepting or rejecting the component for use if the predicted performance is within or outside the performance threshold, respectively.

A method is provided to assist adjustment for a movement path of a probe. A coordinate measuring machine includes a probe having a tip for detecting a surface of an object, and a movement mechanism for moving the probe, and measures a shape of the object by allowing the probe tip to scan the surface. A controller controls operation of the coordinate measuring machine by calculating a scanning path for allowing the probe tip to perform scanning movement and the movement path followed by the probe when the probe tip moves along the scanning path, setting control points on a line connecting each position of the probe tip and each corresponding position of the probe accepting a change in position of the control points by a user, and changing the movement path accordingly. An adjustment guide unit in the controller allows the control points to move collectively.

A method of sentencing, accepting or rejecting, a cast component is disclosed. Initially, scanning the component to determine a number of datum points; this can be done using optical scanning techniques. The datum points from the scanned results are then aligned with an ideal design computer aided design (CAD) model of the component. A comparison of the scanned datum points of the component is performed against the data from the ideal design CAD model of the component, and any geometric deviations between the scan and the ideal design CAD model are determined. Using the datum points from the scan of the component an assessment is performed of at least one performance prediction factor for the component. Finally, using dimensional data extracted from the scan and/or the performance prediction factor the component is sentenced for either acceptance or rejection. Additionally, if the component is determined to have a deviation that lies within a pre-determined limit for the dimensional data and/or the performance factor a determination may be made as to whether the component can be reoriented.

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.