Safran Aircraft Engines

Valentine Lucette Bader

Stéphane Rousselin

Erwan Pierre Antoine Perse

Jérémy Giordan

Margaux Justine Emma Dubois

André Pierre Jean Xavier Leroux

Jean-Pierre Trzebski

An annular air flow passage, particularly for a turbine engine, comprising two radially internal and external annular walls. A measuring element is elongated in a direction between the internal and external annular walls, and a first of the internal or external ends of the element is fixed rigidly to a first of the internal or external walls. The element includes at least one tubular cavity extending along the element and supplied with pressurized fluid.

Instrumented flow passage of a turbine engine

The invention relates to a method for manufacturing a turbine engine casing (), characterized in that said method includes the steps of: manufacturing (E) a plurality of sectors (), at least one portion of the sectors () being manufactured by casting and including, on the surface thereof, fastening elements () produced during the casting step, assembly bands () being produced at the ends of the sectors () during the step of manufacturing the sectors () by casting, by means of which the sectors () can be assembled; and assembling (E) the sectors () end-to-end such as to form a ring () of the casing (). The invention also relates to a turbine engine casing ().

Turbine engine casing and manufacturing method

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Moissy Cramayel, France

Valentine Lucette Bader