There is provided a method for controlling a shape measuring apparatus that relatively moves a probe and a workpiece with a translation movement mechanism and a rotary drive mechanism to perform scanning measurement on the workpiece by moving the probe along a scanning path set in advance.

The method includes setting, by an operator, a scanning path and a rotation angle command for the rotary drive mechanism, dividing data about the scanning path into a plurality of segments and setting a translational velocity pattern of the translation movement mechanism for each segment, calculating for each segment, based on the rotation angle command, a rotation angle value at a start of the segment and a rotation angle value at an end of the segment and generating an angular velocity pattern for each segment, correcting the translational velocity pattern to reduce a rotation amount of the rotation command given by the angular velocity pattern and generating a corrected translational velocity pattern, and driving and controlling, based on a resultant velocity vector based on the corrected translational velocity pattern, the translation movement mechanism and simultaneously driving and controlling, based on an angular velocity command based on the angular velocity pattern, the rotary drive mechanism.

Disclosed is a device for the inspection or maintenance of devices, for example rotor blades of wind power plants. A frame structure can encompass the device, e.g. a rotor blade, and be used for the inspection or examination or cleaning of the rotor blade or other object. The frame structure has, for example, an inner opening which encloses the object during use. Propellers allow a horizontal movement of the frame structure and thus, for example, of a robot for examining the object. A vertical movement of the robot can be controlled by a cable suspension so that the vertical position of the examination device can be changed. A detection, cleaning, or monitoring system can be provided on the frame structure for detecting the condition of the object, cleaning, monitoring or treatment. A control station can be provided on the ground or on a transporter or other device.

Disclosed is an apparatus for inspecting an airfoil, the apparatus having: a pair of opposing walls connected by a base; a pair of chucks, wherein one of the pair of chucks is secured to one of the pair of opposing walls and the other one of the chucks is secured to the other one of the pair of opposing walls; and a profile gauge supported by the pair of opposing walls and configured to move between the pair of chucks.

A method and system for measuring a turbine shape is provided in which an appropriate measurement accuracy can be achieved that is sufficient to prevent a failure to recognize features of shape of a measurement object, with extension of a measurement time suppressed. In a turbine including casings, recesses and protrusions on flange surfaces of the casings are measured at measurement intervals M set on the basis of the entire length L of flange portions in an axial direction, the number of bolts N joining the flange portions, and intervals between the bolts in the axial direction of the flange portions.

The invention relates to a method for controlling the conformity of a profile of a section of a curved surface of a turbomachine element, comprising the following step: (100) acquiring coordinates of a plurality of measurement points of the section in a frame of reference defined for said section; characterised in that the method comprises the following steps: (200) calculating, based on the coordinates of these measurement points, the radius of curvature of the section at each of these points, in order to obtain a measured evolution curve of the radius of curvature according to the position of the measurement points along said section; (300) comparing the measured evolution curve of the radius of curvature, obtained in the preceding step, with a theoretical evolution curve of the radius of curvature of the predetermined section; (400) evaluating the conformity of the section based on the comparison carried out in the preceding step.

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 of measuring the perimetric width of a hollow component. The hollow component comprises a first panel and a second panel, with the first and second panels being bonded to one another around their respective perimeters, and a perimetric width being defined as the width of the bonded portion joining the first panel to the second panel.

A turbine blade has a blade geometry defined in a coordinate system and at least one cavity which is open to the outside and which has a blade internal surface. At least one planar detection surface, which is accessible for the measuring head of a coordinate measuring device, is formed in the blade internal surface, wherein the at least one planar detection surface is assigned a defined design position and/or a defined design orientation with respect to the coordinate system in which the blade geometry is defined.

A tool to measure the radial stacking angle of a cylindrical blade comprises a base configured to indicate a radial direction of the hub, a component slidable over the blade and configured to indicate the stacking direction of the cylindrical blade, reference elements to provide a reference scale, a setting element configured to set the position of the component with respect to the base, a marker element configured to indicate the magnitude of the angle between the stacking direction and the radial direction using the reference elements; the angle corresponds to the radial stacking angle.

A method of measuring the perimetric width of a hollow component. The hollow component comprises a first panel and a second panel, with the first and second panels being bonded to one another around their respective perimeters, and a perimetric width being defined as the width of the bonded portion joining the first panel to the second panel.