Snecma

Snecma Moteurs

Philippe Jean-Pierre Pabion

Jean-Luc Soupizon

Sebastien Jean Laurent Prestel

Jean-Michel Guimbard

Renaud James Martet

Eric Roger Schwartz

Stephanie Dominique Roger

Patrick Joseph Girard

Alain Dominique Gendraud

Patrick Joseph Marie Girard

Sébastien Jean Laurent Prestel

Alexandre Nicolas Dervaux

Sebastien Alain Imbourg

Jean-Claude Marcel Auguste Hanny

Aurelien Rene-Pierre Massot

Godefroy Francis Frederic Drelon

Philippe Gérard Marie Hazevis

Fabrice Michel Olivier Cot

Philippe Hazevis

Olivier Charles Henri Massy

Renaud Martet

Sebastien Jean Prestel

Jean-Michel Bernard Guimbard

Jean-Claude Marcel Hanny

Olivier Charles Massy

Godefroy Francis Frédéric Drelon

Stéphanie Dominique Roger

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

A cooled blade forming an upstream guide vane element for a turbomachine is disclosed. The airfoil includes a longitudinal cavity with a first opening at one end and a second opening at the other end, a tubular sleeve being housed in the cavity with a first end in the first opening and a second end in the second opening, first spacers on the side of the first end, and second spacers on the side of the second end of the sleeve making a space between the outer face of the sleeve and the wall of the cavity. The blade is arranged so that the sleeve is inserted into the cavity through the first opening. The first spacers are secured to the sleeve and the second spacers are secured to the wall of the cavity of the airfoil. The invention makes it possible to mount the sleeve despite an accentuated curvature of the profile of the airfoil.

Cooled blade for a turbomachine

An inter-turbine casing for a turbofan is disclosed. The casing includes an outer ring, an inner ring, and an intermediate ring between the inner ring and the outer ring. The inner and intermediate rings have respective openings for the passage of cooling air. The casing includes at least one sealing device, arranged between the outer ring and the intermediate ring, with a base, provided with at least one orifice for the passage of cooling air, and a peripheral skirt which is able to be compressed and expanded elastically. The base bears against the outer ring and the peripheral skirt bears against the intermediate ring.

Inter-turbine casing with cooling circuit, and turbofan comprising it

The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, is disclosed. The blade includes an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element; an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ; and a connection zone between the airfoil and the airfoil end face. The connection zone forms a fattening of the airfoil. The connection zone extends about the leading edge between a point Psituated on the suction face of the airfoil upstream of the suction face neck and a point Psituated on the pressure face of the airfoil upstream of the pressure face neck.

Turbomachine blade that is cast with a local fattening of the section of the airfoil

A transition channel between a first turbine section and a second turbine section for a gas turbine engine is disclosed. The channel includes a first radially external annular wall including ring sector elements housed inside an annular ring and orifices for injecting a fluid into the channel in order to re-energize the boundary layer thereof, a second radially internal annular wall, and a fluid supply device arranged between the space outside the ring and the injection orifices.

Transition channel between two turbine stages

A device for cooling a turbine casing in a turbomachine including a turbine is disclosed. The turbine includes several stages, at least one of the stages includes a nozzle assembly formed of an annular row of fixed vanes and an impeller mounted to rotate in a cylindrical shroud formed of ring sectors fixed to the casing, a cooling circuit including ducts carrying cooling air into cavities formed in the vanes of the nozzle assembly, and an air-carrying arrangement which carries air to casing upstream hooks for suspending the ring sectors.

Device for cooling a turbomachine turbine casing

A joining device including a clevis and a connecting member is disclosed. The connecting member includes a through hole which is housed between a first and a second lug of the clevis. These lugs respectively have a first clevis hole and a second clevis hole. The device further includes a shear pin system passing through each of the holes and includes a threaded end collaborating with a nut system which abuts against the second lug. The shear pin system includes a widened portion passing through the first hole and forming a shoulder situated between the two lugs. The member is situated away from the first lug. A first side of the member is pressed against the shoulder and a second side of the member is pressed against the second lug.

Joining device for joining two assemblies, for example for a stator of a turbomachine

A strut ( ) fixed to a main portion of turbojet stator carries a ring ( ) by a pair of hooks ( ) on one side and joining lips ( and ) on the other side. In accordance with the invention, the seal is made on the flat sides ( ) adjacent to the lips by elastic deflection of the tabs ( ) pushing back one of the lips ( ). The tabs ( ) can also determine the tangential positioning of the ring ( ).

Linking arrangement of a turbine stator ring to a support strut

Growing community of inventors

Vaux Le Penil, France

Philippe Jean-Pierre Pabion