Lighter turbomachine blade and process for manufacturing the...

Details Lighter turbomachine blade and process for manufacturing the... Lighter turbomachine blade and process for manufacturing the...

B - Operations, Transporting

23

P

B23P 15/04 (2006.01) B23K 20/12 (2006.01) F01D 5/14 (2006.01) F01D 5/18 (2006.01)

Patent

CA 2461519

The invention relates to a turbomachine blade (10) includes a metal alloy airfoil (40) having a cavity (70) closed off by a cover (80) on a hollowed side (70), the cover (80) providing aerodynamic continuity of the hollowed side (50a) and being bonded via an edge (85) thereof to the rest of the airfoil (40) by a weld bead (100). The weld bead (100) emerges on the hollowed side (50a) and penetrates into the airfoil (40) to a depth P at least equal to the thickness EC of the edge of the cover (85) so as to provide continuity of material between the edge of the cover (85) and the rest of the airfoil (40) over a depth at least equal to the thickness EC of the edge of the cover (85). A process for manufacturing such a blade (10) is also disclosed.

L'invention propose une aube allégée de turbomachine (10) comportant une pale (40) en alliage métallique, cette pale (40) comportant elle-même une cavité (70) obturée par un couvercle (80) sur l'un des deux flancs (50) appelé flanc creusé (50a), ce couvercle (80) assurant la continuité aérodynamique du flanc (50a), ce couvercle (80) étant lié par le bord (85) au reste de la pale (40) par un cordon de soudure (100). Une telle aube est remarquable en ce que le cordon de soudure (100) débouche sur le flanc creusé (50a) et pénètre dans la pale (40) avec une profondeur P au moins égale à l'épaisseur EC du bord du couvercle (85) afin d'assurer la continuité de la matière entre le bord du couvercle (85) et le reste de la pale (40) sur une profondeur au moins égale à l'épaisseur EC du bord du couvercle (85). L'invention propose également un procédé de fabrication d'une telle aube (10).

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