Safran Aircraft Engines

Jérôme Salmon

Alexandre Gimel

Mickael Rancic

Christophe Gleize

Axel Pereira

Jean François Richard

Pierre Marcel Emilien Navar

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.

Method for manufacturing a turbomachine compressor blade by compacting

A method for deburring an aeronautical part with an articulated tooling including a plurality of axes of rotation, the aeronautical part including at least one edge to be deburred, the articulated tooling including a tool holder, holding a calibration tool and a machining tool, the calibration tool and the machining tool being fixed to the tool holder and being immovable relative to one another, the method including steps of calibrating the calibration tool and the machining tool, of parameterizing the aeronautical part, of deburring the at least one edge to be deburred with the machining tool moving along a predetermined trajectory, on the basis of the parameters obtained during the parameterization step.

Method for improved deburring of an aeronautical part

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Moissy-Cramayel, France

Jérôme Salmon