Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: An injector nose for a turbomachine includes a primary fuel circuit terminated by a fuel ejection nozzle defining an injection axis (44), and a secondary fuel circuit (64) comprising a secondary fuel swirler (114) formed of swirler channels (112) opening into a terminal fuel ejection portion (68) of annular shape arranged around the fuel ejection nozzle. Each swirler channel (112) has a passage section which decreases in a direction going from an upstream end (111) to a downstream end (115) of the swirler channel (112). The reduction of the passage section of the swirler channels (112) makes it possible to increase the head loss between the inlet and the outlet of the secondary fuel swirler (114) and thus notably to accelerate the fuel within the secondary fuel swirler, while allowing lower fuel flow rates.

Abstract: An injector nose for a turbomachine includes a primary fuel circuit terminated by a fuel ejection nozzle defining an injection axis (44), and a secondary fuel circuit (64) comprising a secondary fuel swirler (114) formed of swirler channels (112) opening into a terminal fuel ejection portion (68) of annular shape arranged around the fuel ejection nozzle. Each swirler channel (112) has a passage section which decreases in a direction going from an upstream end (111) to a downstream end (115) of the swirler channel (112). The reduction of the passage section of the swirler channels (112) makes it possible to increase the head loss between the inlet and the outlet of the secondary fuel swirler (114) and thus notably to accelerate the fuel within the secondary fuel swirler, while allowing lower fuel flow rates.

Abstract: A fuel injector for a turbine engine is provided. The fuel injector includes a body including an admissions chamber for admitting fuel under pressure, a stop valve mounted in the body downstream from the admission chamber and designed to open at a first determined fuel pressure and to remain open beyond that first pressure in order to feed a primary fuel circuit, and a metering valve mounted in the body downstream from the stop valve and designed to open above a second determined fuel pressure, greater than the first pressure, and to remain open above the second pressure in order to feed a secondary fuel circuit. The stop valve and the metering valve form a common movable assembly.

Abstract: The invention relates to a fuel injector (101) for a turbine engine such as an airplane turboprop or turbojet, the injector comprising a body (102) including admission means (104) for admitting fuel under pressure, a stop valve (107) mounted in the body (102) downstream from the admission means (104) and designed to open at a first determined fuel pressure and to remain open beyond that first pressure in order to feed a primary fuel circuit (136), and a metering valve (115) mounted in the body (102) downstream from the stop valve (107) and designed to open above a second determined fuel pressure, greater than the first pressure, and to remain open above the second pressure in order to feed a secondary fuel circuit (117). The stop valve (107) and the metering valve (115) form a common movable assembly (133).