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

Roger A Vandenbroucke

Andre A Camboulives

Jacques E Caruel

Claude C Hallinger

Roland Robert Beyler

Marc F Buisson

Rene A Benoist

Gerard J Bayle Laboure

Jacques Serge Rejzner

Theophile F Le Maout

Buisson, Marc F B

Michel R Clauzel

Theophile Francois Le Maout

Ernest J Barou

An annular burner has an annular flame stabilizer of substantially V shaped cross-section containing a circular fuel injection manifold discharging in counterflow. The annular flame stabilizer is formed by two independent parts, each of these parts constituting one blade of the V cross-section. Pivotal support means are provided at the end of the separation wall of the flows in order to mount each of the parts of the annular stabilizer. The injection manifold is secured to the outer blade of the ring.

Turbo-jet engine afterburner system

A sealing device disposed between two turbomachine elements traversed by gases, particularly between a combustion chamber and a high pressure turbine nozzle support. The device includes an independent collar supported by first and second bearing surfaces on the elements which are to be connected in leaktight manner, the collar being constructed of a material having a thermal expansion coefficient which is different from that of the elements which it interconnects so as to ensure a leaktight connection between the elements.

Sealing device between two elements of a turbomachine

A flame holder device of the type having a flame holder ring with a contius cross section of revolution in the shape of a U or V, and a plurality of flame holder arms having a continuous cross section in the shape of a U or V and radiating from one of the flanks of the ring. According to the invention, each arm is attached to the ring by means of gussets which provide for a slight spacing of the arm from the ring in order to prevent local overheating of the ring due to the recirculation of combustion gases.

Flame holder devices for combustion chambers of turbojet engine

An auxiliary chamber or ignition 'prechamber' for afterburners of aeronautical turbine engines draws in, through a perforated plate, a carbureted mixture produced by fuel projected against an anvil by an injection manifold, and the injection manifold also issues a jet of fuel into a tube which discharges into the chamber downstream of a spark plug. The produced flame is guided into a flame stabilizer.

Device for igniting fuel injected into a rapidly flowing gaseous medium

An exhaust duct for a thrust jet engine, such as a rocket or gas turbine, which an acoustic and/or thermal protection lining is situated coaxially within a support element of the duct and is deformable radially relative to the support member, and preferably also adapted for relieving axial differential expansion stresses between the lining and the support element.

Thermal responsive noise suppressor for exhaust duct

A variable section exhaust nozzle for jet engines which has two sets of fs at the edge of the nozzle opening, one set spanning the spaces between the flaps of the other set. Both sets of flaps are hinged to the nozzle on tangential axes. Fluid-operated jacks are serially connected to define a polygon around and outwardly of the flaps. Levers connect the jacks to the outer set of flaps so that radial expansion or contraction of the polygon, by actuation of the jacks, causes the outer set of flaps to swing outwardly or inwardly to thereby vary the effective area of the nozzle opening. The flaps of the inner set are held outwardly against the outer flaps by the pressure of gases issuing from the nozzle. In another embodiment two additional sets of flaps are hinged to the free edges of the first set and additional fluid-operated jacks are provided for them to thus increase the range of nozzle opening adjustments.

Growing community of inventors

Antony, France

Roger A Vandenbroucke