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

Jerome Perigne

Michel A Desaulty

Gerard Y Barbier

Rodolphe Martinez

Gerard J Bayle-Laboure

Denis J Sandelis

Gerald J Leboure

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 fuel and air injection system for a turbojet engine is disclosed wherein a bowl-shaped member surrounding the fuel injection nozzle defines an impact cooling chamber divided into four sectors. A pair of diametrically opposite sectors have openings to permit air to pass through the cooling chamber into the combustion chamber, while opposite diametrically opposed sectors have openings of larger diameter which also allow communication between the cooling chamber and the combustion chamber. A diaphragm control system allows the air passing into the sectors having the larger diameter openings to be modulated depending upon the throttle setting of the turbojet engine.

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Vaux Le Penil, France

Jerome Perigne