摘要:
The invention relates to a method for repairing by machining a workpiece (1) such as the vane of a turbomachine, from a known process of the part (B), wherein said method includes the step of deforming (32) the profile (B) by a morphing process so that the deformed profile interpolates a cloud of points (A) measured on the part. The deformation of the profile (B) includes a comparison of each having an excessive or non-sufficient thickness (20) on the part to be machined (1) with elementary deformation configurations (CED) (5) each in the form of a mapping and points portion, the elementary deformation configurations (CED) (5) being stored in a database (100), and the database (100) associating for each elementary deformation configurations (CED) (102) the parameters of the morphing function (101).
摘要:
The invention relates to an automated method for the non-destructive inspection of a mechanical part (14), comprising comparing images of the surface of the part with reference images stored in a database using a device (10) for acquiring digital images which comprises an image sensor (24), an illuminating light source (26), and means (18, 22) for the relative movement of the image sensor (24), the light source (26) and the mechanical part (14).
摘要:
The invention relates to an automated method for the non-destructive testing of a woven preform (22), intended for the manufacture of a turbine engine part and including a plurality of first marker threads (30) intertwined with second marker threads (32), the first and second threads (30, 32) having light-reflecting properties that are different from those of the threads of the preform and being woven with the threads of the preform so as to form a surface grid on a given area of the preform (22). The method comprises determining, by means of a plurality of consecutive steps, the spatial coordinates of the intersections between the first and second marker threads (30, 32).
摘要:
The invention relates to a method for repairing by machining a workpiece (1) such as the vane of a turbomachine, from a known process of the part (B), wherein said method includes the step of deforming (32) the profile (B) by a morphing process so that the deformed profile interpolates a cloud of points (A) measured on the part. The deformation of the profile (B) includes a comparison of each having an excessive or non-sufficient thickness (20) on the part to be machined (1) with elementary deformation configurations (CED) (5) each in the form of a mapping and points portion, the elementary deformation configurations (CED) (5) being stored in a database (100), and the database (100) associating for each elementary deformation configurations (CED) (102) the parameters of the morphing function (101).