Safran Aircraft Engines

Joseph Jean Marie Burguburu

Julien Marc Matthieu Leparoux

Patrick François-Regis Lutz

David Pascal Smagghe

Jérémy Peinado

A system for supplying the combustion chamber in an aircraft turboshaft engine with fuel, comprising injectors comprising a first pilot stage, a second pilot stage, and a main stage. The pilot stages being configured to deliver a permanent flow rate of fuel and the main stage being configured to deliver an intermittent flow rate of fuel. A device for distributing fuel into the injectors comprising a primary circuit, a secondary circuit, and a valve configured to distribute the fuel between the primary circuit and the secondary circuit. The primary circuit being connected to the first pilot stage and the main stage, the secondary circuit being connected to the second pilot stage, and a member for controlling the valve.

Fuel system and method for supplying a combustion chamber in an aircraft turboshaft engine with fuel

The invention relates to a combustion chamber comprising: The duct is crossed by openings () which, parallel to the axis of the duct, are staggered in a plurality of rows (. . . ) over the height (H) of the duct, with at least some of the openings individually having a diameter of 0.2 to 0.6 mm.

Turbine engine combustion chamber with fixed duct geometry

A turbine engine including a combustion chamber having an inner annular shroud and an outer annular shroud that are coaxial with each other and that are connected at their downstream ends respectively to an inner annular link wall and to an outer annular link wall, for linking respectively to an inner casing and to an outer casing. At least a first one of the inner and outer annular link walls includes at least one coolant fluid circuit extending between the radially inner and outer ends of said first annular link wall.

Combustion chamber coolant fluid path

A combustion chamber for an aircraft turbomachine includes an annular chamber end wall and an annular row of injection systems mounted in the annular chamber end wall. Each injection system includes at least one air inlet swirler and a main fuel injection nozzle to output a fuel stream centered on an injection axis and including a central recirculation zone and a corner recirculation zone extending as an annulus around the central recirculation zone chamber. The combustion chamber also includes a plurality of additional fuel injection devices mounted in the chamber end wall to inject fuel directly into the corresponding corner recirculation zones produced by the corresponding injection systems at an operating speed less than or equal to the idling speed.

Combustion chamber comprising additional injection devices opening up directly into corner recirculation zones, turbomachine comprising such a chamber and fuel supply method for such a chamber

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Moissy-Cramayel, France

Joseph Jean Marie Burguburu