Lightened turbomachine blade and its manufacturing process
AssigneeSnecma Moteurs
InventorsJean-Pierre Ferte, Jean-Luc Bour, Denis Larrouquere
Life of this patent
Estimating the term…
Abstract
A turbomachine blade includes a metal alloy airfoil having a cavity closed off by a cover on a hollowed side, the cover providing aerodynamic continuity of the hollowed side and being bonded via an edge thereof to the rest of the airfoil by a weld bead. The weld bead emerges on the hollowed side and penetrates into the airfoil to a depth P at least equal to the thickness EC of the edge of the cover so as to provide continuity of material between the edge of the cover and the rest of the airfoil over a depth at least equal to the thickness EC of the edge of the cover. A process for manufacturing such a blade is also disclosed.
Claims20
A process for producing a lightened turbomachine blade, comprising the following operations:
- a) production of a blank of an airfoil;
- b) cutting of a cavity into one side, called the hollowed side;
- c) cutting of a socket in the hollowed side, the socket bordering the cavity and having a bearing surface and a lateral surface;
- d) production of a cover having an external surface with the shape of the hollowed side and an internal surface opposite the external surface, the socket and the cover being dimensioned so that the cover can be inserted into the socket and bear the internal surface against the bearing surface so that the external surface lies in an extension of the hollowed side, a lateral surface of the socket surrounding the cover and positioning the latter above the cavity in order to cover the cavity in the hollowed side;
- e) insertion of the cover into the socket and welding edges of the cover to the rest of the airfoil on the hollowed side, the welding being carried out by a rotation of a welding tool, having a finger and a shoulder, penetrating from the hollowed side between the cover and the rest of the airfoil until contact of the shoulder with the hollowed side and the cover, the welding tool then being moved along a welding path, and a weld bead penetrates into the airfoil to a depth P at least equal to a thickness EC of the edges of the cover so as to provide continuity of material between the edges of the cover and the rest of the airfoil over a depth at least equal to the thickness EC of the edges of the cover;
- and
- f) finishing of the blade.
A process for producing a turbomachine blade, comprising:
- producing an airfoil blank;
- cutting a cavity on a hollowed side of the airfoil blank;
- cutting a socket bordering the cavity in the hollowed side, the socket having a bearing surface and a lateral surface;
- producing a cover having opposite internal and external surfaces, a portion of the internal surface being shaped so as to match a portion of the hollowed side, the socket and the cover being dimensioned so as to allow the cover to be inserted into the socket with the internal surface placed against the bearing surface so that the external surface lies in an extension of the hollowed side, a lateral surface of the socket surrounding the cover and the latter being positioned so as to cover the cavity in the hollowed side;
- inserting the cover into the socket and welding edges thereof to the airfoil on the hollowed side, the welding being carried out by a welding tool penetrating from the hollowed side between the cover and the airfoil until contact is made of the welding tool with the hollowed side and the cover, moving the welding tool along a welding path, and forming a weld bead penetrating into the airfoil to a depth P at least equal to a thickness EC of the edges of the cover so as to provide continuity of material between the edges of the cover and the airfoil over a depth at least equal to the thickness EC;
- and
- finishing the blade.
Dependencies are inferred from the claim text.