Safran Aircraft Engines

Christophe Gleize

Alexandre Gimel

Jérôme Salmon

Jean François Richard

Axel Pereira

Jean-François Richard

The invention relates to a method for producing a turbomachine compressor blade, comprising the following steps:—installing primary pins () comprising a material other than a titanium-based alloy in primary bores () of a core, the primary bores forming at least one polygon, and installing a secondary pin made of titanium-based alloy in a secondary bore of the core; —producing a stack () of a suction-face sheet (), a core () and a pressure-face sheet (); —compacting the stack; —removing the primary pins () from the primary bores (); —removing the secondary pin from the secondary bore; and—taking the core () away from the stack.

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MOISSY-CRAMAYEL, France

Christophe Gleize