Snecma

Snecma Moteurs

Gilles Louis Rollin

Gilles Alain Charier

Thomas Olivier Marie Noel

Robert Kervistin

Jose Roland Rodrigues

José Roland Rodrigues

Xavier Jean-Michel Andr&eacute; Guyonnet

Marion De Giacomoni

Igor Mantchenkov

Victor Ivanovich Furletov

Thomas Noel

Alexander Novikov

Alexander Jurevich Vasilev

Vladimir Orlov

Victor Ivanovich Yagodkin

Valery Pikalov

A fuel injector for an aero-mechanical injection system for injecting an air/fuel mixture into a turbomachine combustion chamber, the injector comprising a main tubular structure of axis XX' opening out at a downstream end for delivering the air/fuel mixture, a tubular fuel duct that is disposed inside the main structure and that opens out into the main structure via a fuel atomizer plug so as to introduce fuel into the main structure at a pressure Pinto the main structure, at least one air feed channel that opens out into the main structure so as to introduce air at a pressure Ptherein, and means for injecting into the fuel duct a gas at a pressure Pthat is greater than Pand greater than or equal to Pso as to create effervescence in the fuel on being introduced into the main structure.

Effervescence injector for an aero-mechanical system for injecting air/fuel mixture into a turbomachine combustion chamber

The invention relates to a method and a device for protecting fuel injectors in a turboshaft engine. The protection is carried out by injecting compressed air directly into the injectors. The air thus directly purges the injectors and evacuates the fuel present in them into the combustion chamber.

Method and system for protecting gas turbine fuel injectors

An aerodynamic injection system for injecting an air/fuel mixture into a turbomachine combustion chamber comprises a tubular structure of axis XX' that opens out at a downstream end for delivering the air/fuel mixture, at least one air feed channel that opens out into the structure so as to introduce air at a pressure Ptherein, an annular fuel passage that is formed in the structure around its axis XX&#x2032;, that is connected to at least one fuel feed channel in which there flows fuel at a pressure P, and that opens out at a downstream end into the structure, and means for injecting gas into the at least one fuel feed channel, said gas being at a pressure Pthat is greater than Pand greater than or equal to Pso as to create effervescence in the fuel on being introduced into the structure.

Effervescent aerodynamic system for injecting an air/fuel mixture into a turbomachine combustion chamber

An integrated exhaust nozzle and thrust reverser for a turbojet engine is provided. The exhaust nozzle comprises an exhaust duct situated within a fairing (,), a set of hot flaps (,) at a downstream end of the duct, a set of cold flaps (,) at a downsteam end of the fairing (,), and a thrust reverser (,). The thrust reverser comprises two eyelids (,) which are movable between a thrust reversal position wherein they project into the duct and a forward-thrust position. In a takeoff mode, the eyelids (,) are moved away from each other by one or more actuators (,) acting on arms (,) pivotably connected to the eyelids (,). Movement of the eyelids (,) from the reverse-thrust position to the forward-thrust position, or vice-versa, is implemented by control actuators (,).

Turbojet engine thrust reverser and exhaust nozzle

Growing community of inventors

Blandy les Tours, France

Gilles Louis Rollin