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

Hispano Suiza

Herve Alain Quillevere

Jacques E Caruel

Philippe M Gastebois

Roland Robert Beyler

Jacques Eloi Pidebois

Joseph Plotkowiak

Michel Bernard Schenher

A compressor which compresses a principal flow at low pressure and recompses a secondary flow at medium pressure to deliver a common flow at high pressure. The compressor includes, in addition to compression devices for the principal flow, static devices forming an induction nozzle housed in the scatterer and devices to introduce therein the secondary flow, the principal flow constituting the drive flow.

Compressor with pump recycling for isotopic separation through gaseous

Combustion chamber comprising a first combustion zone opening into a wider second combustion zone into which the combustion air is admitted through a practically frontal air entry comprising obstacles which impart a coefficient of blocking of about 60% to 80% to it. The first zone is supplied with air and fuel in substantially stoichiometric proportion in idling. At the other running rates, a supplementary fuel flow is injected into the chamber and burns in the second zone in the wake of the obstacles.

Gas turbine combustion chambers

A device for injecting and igniting a fuel in a flow of air, comprising a bular duct in which are generated an internal flow of rotating air and an intermediate flow containing fuel which is sandwiched between the internal flow and an external flow of rotating air, in which ignition is effected by a central electrode placed in the axis of the tubular duct and defining within the latter an annular channel which narrows around the downstream end of the central electrode to form an annular gap of uniform width along the entire extent of its circumference, in such a way that a difference in electrical potential applied between the electrode and the tubular duct causes sparks to jump between the free end of the electrode and the tubular duct across the internal flow and the intermediate flow.

Injecting and igniting device

A combustion chamber for a gas turbine engine, comprising an upstream porn divided longitudinally into a first chamber and a second chamber supplied with air in parallel, and a downstream portion in which the flows issuing from these two chambers mix, the first chamber comprising a primary combustion zone into which fuel is injected at an idling rating forming a substantially stoichiometric air - fuel mixture, and a secondary combustion zone supplied with secondary combustion air, and the second chamber, of the premixed burning type, being formed by a simple conduit upstream of which, for driving the gas turbine at the maximum rating, supplementary fuel is injected which burns on contact with a flame synchronizer.

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Issy-les-Moulineaux, France

Herve Alain Quillevere