Snecma

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Snecma Moteurs

Alain Marie Joseph Lardellier

Guy Franck Paul Dusserre-Telmon

A twin-spool turbine engine includes a low-pressure rotor and a high-pressure rotor, an alternator, including an inductor winding and an armature, the high-pressure rotor rotating the inductor winding of the alternator. The armature is mounted so as to rotate and the low-pressure rotor is connected to a clutch arranged so that the low-pressure rotor drives the armature in a manner that is contrarotational to the inductor winding when the clutch are engaged.

Turbine engine with an alternator and method for transmitting movement to an alternator

The braking method for an aircraft propelled by at least one ducted fan jet engine, the latter comprising a fan, a jet engine core in which the primary flow circulates, a secondary flow exhaust nozzle, encased in a nacelle, comprises the step, in low-power operation, of unloading at least part of the secondary flow so as to reduce the residual thrust of the jet engine without producing any thrust. With the method of the invention, aircraft braking can be achieved without any thrust reverser device using the braking force generated by the drag of the jet engine or engines completed by reduction of residual thrust by unloading the secondary flow.

Aircraft braking method and ducted fan jet engine for implementing the method

The invention relates to a turbomachine () for an aircraft comprising a gas generator () designed such that hot gases are ejected from a combustion chamber () towards the upstream side of the turbomachine, and also comprising a plurality of hollow mixer struts () connected to an output () from the gas generator through which hot gases can pass, each mixer strut comprising an output mixer portion () located inside the annular fan duct () so as to mix the secondary air and the hot gases ejected by these output mixer portions towards the downstream side of the turbomachine.

Turbomachine with low noise emissions for aircraft

The drive system of a propeller driven transport aircraft has first and second propeller doublets mounted in the plane of the aircraft wings, each propeller doublet including two propellers disposed symmetrically on opposite sides of the central longitudinal axis of the aircraft. The first and second propeller doublets are driven independently of one another by first and second engine units via first and second independent drive trains respectively, the first and second engine units being disposed side by side in the aircraft fuselage.

Growing community of inventors

Melun, France

Alain Marie Joseph Lardellier