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

Marc G Loubet

Gerard E Jourdain

Georges Mazeaud

Marcel R Soligny

Jean G Bouiller

Philippe M Gastebois

Pascal Noel Brossier

Guy J-l Lapergue

Jean-Michel Payen

Claudine L Planquet

The rotor of a fan disposed in the annular noncombusted air flow duct of a urbojet propulsion engine of the bypass type is carried by a rotary body which includes the rotor assembly of a multi-stage turbine driven by noncombusted air supplied thereto by an axisymmetrical auxiliary duct which diverts noncombusted air from the primary duct of the engine just downstream of the compressor.

Propulsion engine

A heat protective lining for the afterburner or transition duct of a turbojet engine comprises an assembly of tiles overlapping laterally and longitudinally to form overlapping rings of tiles in which the tiles of each ring are offset laterally from those of each adjacent ring by half a tile width. The tiles are held together by eyelets projecting from the overlapped downstream portions of the tiles through apertures in the overlapping upstream portions, and locking members engaging through the eyelets. Fastening yokes for fixing the assembly to the duct casing are secured to the outside of the tiles.

Heat protective lining for an afterburner or transition duct of a

A transition pipe for location between an afterburner pipe and a jet nozzle in a jet pipe assembly for a turbojet engine comprises a funnel shaped inner casing tapering downstream from a circular section at its upstream end to a quadrangular section at its downstream end, a horn shaped outer casing surrounding the inner casing and flared downstream from a circular upstream end section to a downstream end section formed of four joined segments of generally parabolic shape, and a plurality of peripherally spaced, longitudinally extending stiffeners interconnecting the inner and outer casings in the space therebetween.

Transition pipe for a jet pipe assembly of a turbojet engine

Two coaxial bodies of revolution made of materials having distinctly different expansion coefficients are joined together to form an assembly by fixing means comprising at least three resilient brackets of trapezoidal shape, the larger end of each bracket having a flanged edge secured at at least two points by hollow rivets to a metal ring and by bolts extending through the rivets to the body with the higher expansion coefficient, and the smaller end of each bracket being secured by at least one bolt to the body with the lower expansion coefficient in a manner which imposes a cold prestress on the bracket.

Assembly of two bodies having distinctly different coefficients of

An adjustable two-dimensional nozzle is disclosed in which simplified control means are located away from the flow of gasses through the nozzle. The nozzle includes a movable frame located outside of fixed sidewalls and has pivotally attached thereto a pair of upstream or converging nozzle flaps. Upstream edges of the upstream flaps are attached to the movable frame such that the flaps pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. Downstream or diverging flaps are attached to the downstream edges of the upstream flaps such that these flaps also pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. A cam member extends between each of the movable frames and each downstream flap to control the angular variations of the flaps during movement of the frame. The flap arrangements are symmetrically arranged with respect to a plane passing through the longitudinal axis of the nozzle, such that translational movement of the frames will alter the cross-section of the nozzle in a symmetrical manner with respect to the plane. If the frame is rotated about its pivot attachment, the nozzle flaps will be asymmetrically adjusted and may be utilized to vector the thrust of the gasses emanating from the nozzle.

Adjustable two dimensional nozzle for aircraft jet engines

A connection device is disclosed for connecting a burner ring or flame holder made of a composite material and having a 'V'-shaped cross-section, to an afterburner chamber duct of a turbojet engine. The connecting device has a cylindrical portion and a trapezoidal portion. The cylindrical portion extends through hollow projections formed from the composite ring material and extending from the ring in an upstream direction. The converging, opposite sides of the trapezoidal portion bear against inner surfaces of the converging flanges forming the 'V' cross-section of the ring. The cylindrical portion is then attached to the afterburner duct via a link-bar mechanism.

Growing community of inventors

Nandy, France

Marc G Loubet