Safran Aircraft Engines

Snecma

Jacques Abousefian

Gilles Charles Casimir Klein

Antoine Bosselut

Bertrand Lamaison

Christine Hottier

A shaping method making use of shaper tooling suitable for high-temperature shaping of a preformed metal part having two side fins extending from a nose, the method including putting the preformed metal part into place in a first bottom die of the tooling, holding the preformed metal part in a first determined position with a first movable central insert, forming one of the side fins of the preformed metal part into its final shape in alignment with the nose by moving with a first movable top die, turning over the preformed metal part, putting the preformed metal part into place in a second bottom die of the tooling, holding the preformed metal part in a second determined position with a second movable central insert, and shaping the other side fin into its final shape in alignment with the nose by moving with a second movable top die.

Method for the high-temperature shaping of a metal blade reinforcement

A method for producing a solid component which in succession includes deforming a metal bar by forging using two dies in order to obtain an intermediate component including two fins one on each side of a solid part capable of forming the base of the metal reinforcement, the two fins being at a divergent angle &#x3b1;; deforming the two fins of the intermediate component, altering the divergent angle &#x3b1;, so as to obtain the final shape of the turbomachine blade leading edge or trailing edge metal reinforcement.

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Achères, France

Jacques Abousefian