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 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 inlet body for a fluid injector for a turbomachine. The inlet body includes a casing defined by an internal surface and a seal valve housed inside the casing. The valve includes a sealing member including an intake duct, and internal duct into which the intake duct opens, and a seat for the sealing member. The seat defines an opening over a fluid path towards the internal duct. The internal surface includes a recess which defines at least partially a chamber communicating with the opening and with the intake duct.

Abstract: The invention concerns a connection device (14) for connecting a turbomachine member such as an injector, to a system for supplying a fluid such as fuel, the connection device (14) comprising several concentric tubes (26, 28, 30) delimiting conduits (20, 22, 24) 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 (26, 28, 30).

Abstract: The invention relates to a combustion chamber for a turbomachine. The combustion chamber comprises at least one spark plug, at least one fuel injector of a first type of injector that is located facing the spark plug, and at least one fuel injector of a second type. Each fuel injector comprises a mobile sealing member that is configured to open when the fuel pressure exceeds an opening threshold. The opening threshold of the mobile sealing member of the injector of the first type is strictly less than the opening threshold of the mobile sealing member of the injector of the second type.

Abstract: An inlet body is for a fluid injector for a turbomachine. The inlet body includes a casing and an inlet nozzle, housed inside the casing, that serves as a seat for a mobile sealing member. The inlet nozzle includes a central duct for the fluid and an annular rim surrounding the central duct. The annular rim includes a housing for a gasket. The housing is defined by a bottom wall, an opening opposite the bottom wall, and two opposite walls which each extend between the bottom wall and the opening. The walls are tilted towards each other in the direction of the opening.

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 (10) such as an injector for an annular combustion chamber of a turbine engine, comprising a downstream head (16) having a central outlet (22) and an annular peripheral outlet (24) surrounding the central outlet (22), and an injector arm (12) upstream of the head (16) comprising coaxial central channel (18) and annular channel (20), characterised in that the central channel (18) is in fluid communication with the peripheral outlet (24) and the annular channel (20) is in fluid communication with the central outlet (22).

Abstract: An arrangement for an aircraft turbine engine combustion chamber including an injection system and a fuel injector is provided. The injection system includes an injector nozzle guide, the inner surface of which delimits an opening for centering the nozzle, which includes an outer casing. The arrangement further includes a sealing device between the inner surface of the guide and the outer casing. The sealing device includes a first part accommodated in a groove of the outer casing, the groove being delimited, in part, by a downstream delimiting surface, the first part having a first sealing surface and bearing axially against the downstream delimiting surface; and a second part having a second sealing surface bearing radially against the inner surface of the guide.

Abstract: An inlet body is for a fluid injector for a turbomachine. The inlet body includes a casing and an inlet nozzle, housed inside the casing, that serves as a seat for a mobile sealing member. The inlet nozzle includes a central duct for the fluid and an annular rim surrounding the central duct. The annular rim includes a housing for a gasket. The housing is defined by a bottom wall, an opening opposite the bottom wall, and two opposite walls which each extend between the bottom wall and the opening. The walls are tilted towards each other in the direction of the opening.

Abstract: An inlet body for a fluid injector for a turbomachine. The inlet body includes a casing defined by an internal surface and a seal valve housed inside the casing. The valve includes a sealing member including an intake duct, and internal duct into which the intake duct opens, and a seat for the sealing member. The seat defines an opening over a fluid path towards the internal duct. The internal surface includes a recess which defines at least partially a chamber communicating with the opening and with the intake duct.

Abstract: The invention relates to a combustion chamber for a turbomachine. The combustion chamber comprises at least one spark plug, at least one fuel injector of a first type of injector that is located facing the spark plug, and at least one fuel injector of a second type. Each fuel injector comprises a mobile sealing member that is configured to open when the fuel pressure exceeds an opening threshold. The opening threshold of the mobile sealing member of the injector of the first type is strictly less than the opening threshold of the mobile sealing member of the injector of the second type.

Abstract: A fuel dosing device for a fuel injector of an aircraft turbomachine, including an opening, a movable member for sealing the opening, and elastic return, with the member able to be displaced under the effect of the fuel pressure. The device includes a first outlet communicating with a primary circuit of the injector as well as a second outlet communicating with a secondary circuit. In addition, it is designed such that up to a defined level of displacement of the sealing member, the latter allows the fuel coming from the opening to reach the first outlet and, only beyond the defined level of displacement, the member allows the fuel coming from the opening to reach the second outlet.

Abstract: An arrangement for an aircraft turbine engine combustion chamber including an injection system and a fuel injector is provided. The injection system includes an injector nozzle guide, the inner surface of which delimits an opening for centering the nozzle, which includes an outer casing. The arrangement further includes a sealing device between the inner surface of the guide and the outer casing. The sealing device includes a first part accommodated in a groove of the outer casing, the groove being delimited, in part, by a downstream delimiting surface, the first part having a first sealing surface and bearing axially against the downstream delimiting surface; and a second part having a second sealing surface bearing radially against the inner surface of the guide.

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 concerns a connection device (14) for connecting a turbomachine member such as an injector, to a system for supplying a fluid such as fuel, the connection device (14) comprising several concentric tubes (26, 28, 30) delimiting conduits (20, 22, 24) 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 (26, 28, 30).

Abstract: A fuel injector (10) such as an injector for an annular combustion chamber of a turbine engine, comprising a downstream head (16) having a central outlet (22) and an annular peripheral outlet (24) surrounding the central outlet (22), and an injector arm (12) upstream of the head (16) comprising coaxial central channel (18) and annular channel (20), characterised in that the central channel (18) is in fluid communication with the peripheral outlet (24) and the annular channel (20) is in fluid communication with the central outlet (22).

Abstract: A fuel dosing device for a fuel injector of an aircraft turbomachine, including an opening, a movable member for sealing the opening, and elastic return, with the member able to be displaced under the effect of the fuel pressure. The device includes a first outlet communicating with a primary circuit of the injector as well as a second outlet communicating with a secondary circuit. In addition, it is designed such that up to a defined level of displacement of the sealing member, the latter allows the fuel coming from the opening to reach the first outlet and, only beyond the defined level of displacement, the member allows the fuel coming from the opening to reach the second outlet.

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).