Snecma

Aurelien Rene-Pierre Massot

Sebastien Jean Laurent Prestel

Xavier Firmin Camille Jean Lescure

Jean-Luc Soupizon

Patrick Joseph Marie Girard

Philippe Jean-Pierre Pabion

Wilfried Lionel Schweblen

Christian Rene Schnell

Audrey Charrie

Arthur Cohin

Florent Gant

Sebastien Jean Prestel

Xavier Firmin Lescure

Philippe Gerard Hazevis

Eric Schwartz

An interface device between first and second turbomachine elements is provided. The interface device includes an annular air inlet structure including opposite first and second parts, designed to come into contact with the first and second turbomachine elements respectively, in which the first part is configured to be in swivel contact with the first element; and an elastic return device that can be placed around the air inlet structure and designed to come into contact with at least the first turbomachine element.

Interface device between two turbomachine elements

The present invention relates to a two-spool gas turbine engine including an HP turbine stator ring and an exterior wall of the transition channel between the HP and LP stages, a first enclosure for controlling the stator ring, and a second enclosure for distributing air for blowing the exterior wall of the transition channel. The engine is characterized in that the two enclosures are placed in communication via an orifice controlled by a valve adapted to be open when the pressure Pin the first enclosure is greater than the pressure Pin the second enclosure, and closed when P&#x3c;P

Gas turbine engine with valve for establishing communication between two enclosures

The exhaust casing of a turbomachine includes a cylindrical jacket for guiding a flow of exhaust gas and for defining a hub cavity inside the casing, the jacket including at its ends an annular flange and a radial annular portion extending inwards and formed with an annular rim that is designed to be received in an annular groove of the inner wall of the exhaust casing to close the hub cavity in substantially sealed manner.

Sealing a hub cavity of an exhaust casing in a turbomachine

A sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors and comprising two annular platforms interconnected by substantially radial vanes, together with an annular rail for supporting elements of abradable material, each inner platform having longitudinally-extending edges that are V-shaped, and each rail sector having, on at least one of its sides, means for bearing axially on corresponding means provided on an adjacent nozzle sector.

Sectorized nozzle for a turbomachine

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Vaux Le Penil, France

Aurelien Rene-Pierre Massot