Safran Aircraft Engines

Léon Tham

Gilles Charles Casimir Klein

Mohamed Walid Khous

A forging method serving to use shaping tooling suitable for high temperature forging of a preformed metal part having angular twist undercuts () in its final shape, the method comprising placing the preformed metal part on a movable central insert () of the tooling and blocking it in the tooling (), and forming side fins of the preformed metal part () in their final shape by moving a movable top first die and the movable central insert in a common direction towards a stationary bottom die, the movable central insert including at least two cutaway zones () for eliminating the angular twist undercuts and thus enabling the preformed metal part in its final shape to be dislodged in a single extraction direction.

Method for high temperature forging of a preformed metal part, and shaping equipment suitable for forging

A method of fabricating a reinforcing edge (') of a turbine engine blade () in which there is provided a blank () of the reinforcing edge and an indentation is imprinted in said blank so as to form a rough surface (S). A reinforcing edge (&#x2032;) obtained by such a method.

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Saint Denis, France

Léon Tham