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

501 Societe Nationale D'etude Et De Construction De Meteur

Gerard J Bayle-Laboure

Michel A Desaulty

Gerard Y Barbier

Rodolphe Martinez

Jerome Perigne

Denis J Sandelis

Marcel R Soligny

Jean G Bouiller

Marc F Buisson

Pierre A Bouillot

Jean-Claude Pachot

Roger B Linstrumelle

Mark F Buisson

Michael A Desaulty

An improved swirler system for a turbojet engine combustion chamber is disclosed in which stationary first vanes and moveable second vanes are oriented at different angles with respect to a radius of the fuel injector system. The different angles allow the angle of the incoming air to be adjusted between full power and idle conditions so as to vary the conial shape of the atomized air-fuel mixture according to the operating conditions of the engine. Radial and axial inlet duct portions serve to attenuate the wakes of the air flow generated by the vanes prior to the air passing into the combustion chamber.

Air-fuel injection system for a turbojet engine

A fuel system for a turbojet engine is disclosed in which the operating parameters of the engine are improved throughout the range of engine operating conditions. The fuel system includes an enlarged intermediate bowl for the combustion chamber which increases the reactive volume, while at the same time provides sufficient cooling of the bowl to avoid burn-through or uneven engine operating characteristics. The bowl extends radially outwardly beyond an opening in the base of the combustion chamber and defines a row of air inlet orifices which serves to more completely atomize the fuel prior to its ignition. A diaphragm control system may also be utilized to control the amount of air flowing into the bowl as the engine speed changes.

Enlarged bowl member for a turbojet engine combustion chamber

A swirler for a gas turbine fuel injection apparatus is disclosed in which the intake air is directed both axially and radially to maximize the efficiency of the gas turbine during all modes of operation. Circumferentially alternating axial and radial passages are defined by the swirler member surrounding the fuel injection nozzle. A diaphragm control is provided to selectively control the amount of air passing through the axial and radial passages, depending upon the operational mode of the gas turbine.

Axial-centripetal swirler injection apparatus

A system is disclosed for controlling the flow of air through the air-fuel mixing device for a turbojet engine. The system simultaneously controls the amount of air passing through turbulence generating baffles and that passing into the combustion chamber depending upon the operating conditions of the turbojet engine.

Variable flow air-fuel mixing device for a turbojet engine

The invention relates to a variable area nozzle for a turbo-jet engine. This nozzle comprises a convergent portion, formed by a fixed semi-shell (2) and a semi-shell (3) pivotal about a diametral axis (4a-4b); the fluid-tightness of the convergent portion is ensured by a substantially semi-circular seal (6) and by two longitudinal seals (7a, 7b). The nozzle can be used for example with an engine comprising a partial re-heat system of moderate output.

Variable section nozzle for a turbo-jet engine and an aircraft

An open ended enclosure has a tubular conduit extending axially within it d is provided with both an electric spark plug and a catalytic ignition member in the annular region of the enclosure outside the tubular conduit.

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Avon, France

Gerard J Bayle-Laboure