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

Jean Robert Bedue

Jacques E Caruel

Philippe M Gastebois

Jean-Paul R Gaillac

Bernard Andre Cantaloube

Bruno Deroide

A fuel injection nozzle for a turbo engine is mounted at the base of a costion chamber, either tubular or annular, by means of an intermediate inwardly flared member having openings through its sides for admitting cooling air. An annular flange structure around the intermediate member supports the same and defines an annular space with the base of the chamber for a layer of cooling air admitted to that space through holes in the base. Several forms are disclosed in each of which the various holes and air inlets are dimensioned and positioned to provide a stoichiometric mixture of air and fuel under substantially all conditions of operation.

Combustion chamber for turbo engines

A fuel injector in which, an annular intermediate flow containing fuel is ndwiched between an inner and an outer flow of air caused to rotate by swirl-promoting bladed devices called 'swirlers,' the inner flow being generated in a tubular duct which is closed at its upstream end with a bottom plate, and the 'swirler' associated with said inner flow being a centripetal bladed device that opens to the tubular duct upstream of an annular duct supplied with fuel and itself opening at its downstream end to the tubular duct, thus forming a sharp enlargement within the tubular duct.

Growing community of inventors

Creteil, France

Jean Robert Bedue