The invention provides a method of inspecting a wind turbine blade. The method includes providing a defect inspection tool having an array of pins, the pins being displaceable in an axial direction relative to one another. The method includes positioning the defect inspection tool against a defect on the wind turbine blade to cause displacement of at least some of the pins in the axial direction, the displaced pins describing a contour representative of a contour of the defect. The method includes determining dimensions f the defect by inspecting the contour described by the displaced pins. Advantageously, the invention provides for a more accurate determination as to whether a defect needs to be repaired.

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.

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.

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.

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.

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.

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.

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.

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.

An inspection device is disclosed herein. In various embodiments, the inspection system device comprises: a support structure; a motor; a shaft operably coupled to the motor, the shaft extending from a first side of the support structure to a second side of the support structure, the shaft configured to couple to a bladed rotor; and a scanner moveably coupled to the support structure, the scanner configured to generate a three-dimensional model for the bladed rotor.