Snecma Moteurs

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

Bertrand Pierre Renaud Monville

Didier Georges Feder

Guy Jean-Louis Lapergue

Laurent Claude Patrick Salperwyck

Jacky S Naudet

Daniel Germain Kettler

Laurent Claude Patrick Salperwick

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

Growing community of inventors

Moissy Cramayel, France

Bertrand Pierre Renaud Monville