Snecma Moteurs

Societe Nationale D'etude Et De Construction De Moteurs D'aviation-snecma

Scnema Moteurs

Snecma

Didier Georges Feder

Guy Jean-Louis Lapergue

Bertrand Pierre Renaud Monville

Guy Lapergue

Laurent Claude Patrick Salperwyck

Jacky S Naudet

Alain Tiepel

Marion Michau

Daniel Germain Kettler

Jos&eacute; Rodrigues

Gw&eacute;na&euml;lle Calvez

Jose Roland Rodrigues

Jackie Prouteau

Christophe Viguier

Raphael Curtelin

Raphaël Curtelin

Fr&eacute;d&eacute;ric Ravet

Alain Schuler

Laurent Claude Patrick Salperwick

Frederic Ravet

Gwenaelle Calvez

A device for supplying cooling air to a hollow flap of an exhaust nozzle in a turbojet engine. The device includes a tube connecting the hollow flap to a cooling air source. The tube comprises at least one telescopic portion and at least one ball-joint connection.

Device for supplying cooling air to exhaust nozzle flaps

The present invention relates to a convergent-divergent turbojet nozzle () comprising driven divergent flaps (), follower divergent flaps () interposed between the driven flaps, and means () for supplying cooling air to the follower flaps (), said follower flaps () having a box structure and having lateral openings for delivering cooling air towards the inner face of said driven flaps (), in such a way as to limit the heating up of these flaps when the turbojet is in operation.

Convergent-divergent turbojet nozzle

The invention provides an injection system for injecting an air/fuel mixture into a combustion chamber of a gas turbine engine, the injection system having a longitudinal axis and comprising fuel injection means, interposed between first and second air injection means, the fuel injection means being disposed in an annular internal cavity of a Venturi, the fuel injection means comprising at least a first fuel admission circuit provided with at least one fuel injection orifice, and a plurality of second fuel admission circuits independent from the first fuel admission circuit(s), each being provided with at least one fuel injection orifice so as to define a plurality of independent modes of injecting the air/fuel mixture depending on determined operating speeds of the engine, the fuel injection orifice of the first fuel admission circuit being formed in the upstream wall of the Venturi so as to inject fuel towards the combustion chamber in a general direction that is substantially perpendicular to a flow of air coming from the first air injection means, and the fuel injection orifices of the second fuel admission circuits being formed in the downstream wall of the Venturi so as to inject fuel towards the combustion chamber in a general direction that is substantially perpendicular to a flow of air coming from the second air injection means.

Multimode system for injecting an air/fuel mixture into a combustion chamber

An axisymmetric, converging-diverging and swiveling exhaust nozzle includes converging flaps ( ) driven by an axially displaceable drive ring ( ). The diverging flaps ( ) are connected by linkrods ( ) to a pivoting ring ( ). The pivoting ring ( ) is mounted in swiveling manner on a spherical segment ( ) fixedly joined to the structure ( ). In an embodiment variation, the spherical segment ( ) is mounted by a sliding connection on the stationary structure. A rotation-blocking system ( ) precludes the rotation of the spherical segment ( ) about the axis X of the turbojet engine.

Swiveling, converging-diverging, axisymmetric exhaust nozzle

An axisymmetric, converging-diverging exhaust nozzle swiveled by a guided vectoring ring ( ). The guides comprise three axial apertures ( ) which are each located in a base firmly joined to relatively fixed structure and of which the center planes intersect along the longitudinal axis of the turbojet-engine. The side walls ( ) of the apertures ( ) guide three mutually equidistant spherical rollers ( ) fastened to radial stubs ( ) firmly affixed to the vectoring ring ( ).

Axisymmetric, converging-diverging exhaust nozzle swiveled by a guided ring

An axisymmetric, converging-diverging turbojet-engine exhaust nozzle for jet deflection. The diverging flaps are connected by linkrods to a vectoring ring ( ). The vectoring ring ( ) is driven by linear actuators ( ) anchored in the stationary structure ( ). The linear actuators ( ) are connected by a swivel ( ) to the vectoring ring ( ) and are affixed to the stationary structure ( ) to absorb the tangential loads applied by the exhaust gases on the diverging flaps and to allow positioning the vectoring ring ( ). Preferably the linear actuator ( ) is connected by a sheath ( ) to the vectoring ring ( ), the sheath ( ) slidable on the actuator case ( ) and being displaceable in a radial plane passing through the turbojet-engine's axis.

Axisymmetric, converging-diverging, jet-deflecting turbojet-engine exhaust-nozzle

The invention relates to a wide-vectoring, axisymmetric turbojet-engine exhaust nozzle including vectoring structure (,) supporting a plurality of converging flaps (,). The vectoring structure is mounted on the downstream end of an exhaust housing (,) by means of an intermediate ring (,) which is pivotable about a first axis relative to the exhaust housing (,) and further about a second axis perpendicular to the first axis and relative to the vectoring structure (,). The converging flaps (,) hinge on the downstream end of the vectoring structure (,). A single drive ring (,) controlled by three linear actuators (,) and linked by linkrods (,) to the converging flaps (,) controls the tipping of the vectoring structure (,) and the kinematics of the flaps (,).

Universal-joint vectoring system for a turbojet-engine exhaust nozzle

Growing community of inventors

Savigny-Le-Temple, France

Didier Georges Feder