Method of producing a composite component

Details Method of producing a composite component Method of producing a composite component

B - Operations, Transporting

23

H

B23H 9/00 (2006.01) B23H 9/10 (2006.01) B23H 9/14 (2006.01) B23K 26/38 (2006.01) B23K 26/40 (2006.01)

Patent

CA 2487913

A composite component (1), such as a turbine airfoil, comprises a conductive portion (2), and a non-conductive portion (5), such as a thermal barrier coating or a wear protection coating, or both. In machining the component, a laser machining step is applied for machining the non-conductive portion, and an electro-machining step is applied for machining the conductive portion. The laser machining step is performed by applying preferably a high-frequency pulsed laser. The focussed laser beam working diameter (DL) is essentially smaller than the size of the contour (16) to be machined. The contour is scanned by the laser beam (9) along a pre-defined trace (17) thus literally inscribing the desired contour into the workpiece.

L'invention concerne un composant composite (1), de type profil de turbine, qui comprend une partie conductrice (2), et une partie non conductrice (5), par exemple un revêtement de protection thermique ou un revêtement de protection contre l'usure, ou les deux. Lors de l'usinage du composant, une étape d'usinage laser est appliquée pour l'usinage de la partie non conductrice, et une étape usinage électrique est appliquée pour l'usinage de la partie conductrice. L'étape d'usinage laser est de préférence réalisée par application d'un laser pulsé à haute fréquence. Le diamètre (D<SB>L</SB>) du faisceau laser mis au point est sensiblement inférieur à la taille du contour (16) à usiner. Ce contour est balayé par le faisceau laser (9) le long d'un tracé (17) prédéfini, ce qui permet d'inscrire littéralement le contour désiré dans la pièce à usiner.

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