Safran Aircraft Engines

Sébastien Christophe Loval

Christophe Chabaille

Clément Yves Emile Bernard

Pierre Jean-Baptiste Metge

Loïc Pora

Petar Tomov

Alexandre Corsaut

Bénédicte Leleu

Kevin Auber

Marc Serrau

Sébastien Jahin

Petar Dimitrov Tomov

A fuel distribution assembly for a turbomachine extends between a first interface plane and a second interface plane substantially parallel to the first interface plane, the distribution assembly including a plurality of distribution ducts, each duct having at least one inlet portion that is open to the first interface plane or to the second interface plane, at least one outlet portion that is open to the first interface plane or to the second interface plane, and a middle portion fluidly connecting each inlet portion of the duct and each outlet portion of the duct. The middle portion of each duct has an internal cross-section of substantially elliptical shape.

Fuel distribution assembly for a turbomachine

Fuel pump for an aircraft engine, comprising an inducer and a centrifugal impeller fixed together and having an axis of rotation, an annular space spacing axially the inducer and the impeller, and two contact portions between the inducer and the impeller disposed radially outside the annular space, a first plenum chamber and a second plenum chamber, in which the inducer and the impeller are spaced axially from each other, each being disposed between the two contact portions, the plenum chambers being symmetrical to each other with respect to the axis of rotation and in fluid communication with the annular space, the centrifugal impeller comprising a plurality of axial balancing holes distributed about the axis of rotation and opening out into the annular space at one end, and into a downstream space of the impeller at the other end.

Aircraft engine fuel pump

An injector nose for a turbomachine includes a primary fuel circuit ending in a fuel-ejection nozzle, and a secondary fuel circuit including an annular-shaped terminal fuel-ejection part arranged around the fuel-ejection nozzle. An upstream part of the primary fuel circuit includes an annular channel, which extends around the secondary fuel circuit and is defined by an external wall of the injector nose. The injector nose includes air intake channels extending through the annular channel and having inlets opening into the external wall and outlets opening into an annular air injection channel arranged radially to the inside in relation to the terminal fuel-ejection part, around the fuel-ejection nozzle, and cooperating with the terminal fuel-ejection part in order to form an aerodynamic secondary injector.

Injector nose for turbomachine comprising a primary fuel circuit arranged around a secondary fuel circuit

An injector nose for a turbomachine includes a primary fuel circuit terminated by a fuel ejection nozzle defining an injection axis (), and a secondary fuel circuit () comprising a secondary fuel swirler () formed of swirler channels () opening into a terminal fuel ejection portion () of annular shape arranged around the fuel ejection nozzle. Each swirler channel () has a passage section which decreases in a direction going from an upstream end () to a downstream end () of the swirler channel (). The reduction of the passage section of the swirler channels () makes it possible to increase the head loss between the inlet and the outlet of the secondary fuel swirler () and thus notably to accelerate the fuel within the secondary fuel swirler, while allowing lower fuel flow rates.

Injector nose for turbomachine including a secondary fuel swirler with changing section

The invention concerns a connection device () for connecting a turbomachine member such as an injector, to a system for supplying a fluid such as fuel, the connection device () comprising several concentric tubes () delimiting conduits () for supplying the member, which are curved in at least one direction, characterised in that it is made from a single part comprising at least the tubes ().

Connection device comprising several curved concentric tubes

A fuel injector () such as an injector for an annular combustion chamber of a turbine engine, comprising a downstream head () having a central outlet () and an annular peripheral outlet () surrounding the central outlet (), and an injector arm () upstream of the head () comprising coaxial central channel () and annular channel (), characterised in that the central channel () is in fluid communication with the peripheral outlet () and the annular channel () is in fluid communication with the central outlet ().

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Paris, France

Sébastien Christophe Loval