Safran Aircraft Engines

Jeremy Paul Gonzalez

Marc Versaevel

Jacky Novi Mardjono

Norman Bruno Andre Jodet

Philippe Gerard Chanez

Laurent Louis Robert Baudoin

Henri Yesilcimen

Maxime Koenig

Franck Zaganelli

Device for perforating an acoustic annular panel for a turbine engine, wherein it includes a perforation needle support ring, the ring having an axis A of revolution and being intended to be inserted substantially coaxially inside the panel, the ring being sectored and including ring sectors regularly distributed around the axis and each one radially mobile opposite the axis from a radially inner rest position up to a perforation position of the radially outer panel, and at least one rotating actuator of rotation axis A and mechanically connected to the ring sectors such that a rotation of the actuator leads to a radial movement of the ring sectors.

Device for perforating an acoustic annular panel for a turbine engine

A device for reducing the jet noise of a turbine engine includes an outer cover having an inside wall defining the outside of an annular passage for passing a bypass stream from the engine, the wall of the outer cover including a plurality of microjet circuits, each including intakes for taking a gas stream from the bypass stream flow passage and leading to a single feed duct, which in turn opens out into the trailing edge of the outer cover via at least one ejection grating suitable for splitting the intake gas stream into a plurality of gas streams of right sections of dimensions less than a right section of the feed duct.

Device with gratings for ejecting microjets in order to reduce the jet noise of a turbine engine

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La Chapelle Rablais, France

Jeremy Paul Gonzalez