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

Michael A Desaulty

Gerard Y Barbier

Rodolphe Martinez

Gerard J Bayle-Laboure

Jerome Perigne

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.

Growing community of inventors

Vert St Denis, France

Michael A Desaulty