Abstract: An annular wall of a combustion chamber of a turbine engine including: a cold side and a hot side; plural dilution holes to allow circulating air of the cold side to enter the hot side for dilution of an air/fuel mixture; plural cooling orifices to allow the circulating air of the cold side to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices distributed spaced axially from one another and with geometric axes inclined, in an axial direction of flow of combustion gases, by an inclination angle relative to a normal to the annular wall; plural additional cooling orifices arranged directly downstream of the dilution holes and distributed spaced axially from one another, with geometric axes arranged in a plane perpendicular to the axial direction and inclined by an angle of inclination relative to a normal to the annular wall.

Abstract: A turbine engine combustion assembly including a casing, a combustion chamber, and at least one fuel injector. The combustion chamber includes an internal wall and an external wall extending one inside the other and connected by an annular chamber base wall. The external wall of the chamber is secured to an annular external wall of the casing. The injector is attached to the annular external wall of the casing and includes a fuel ignition enclosure extending inside the casing successively through openings in the casing wall and in the external wall before opening into the chamber. At least one wall of the ignition enclosure extending between the casing wall and the combustion chamber wall includes at least one air intake port. The external wall of the combustion chamber is solidly connected to a device for plugging the air intake port according to a thermal expansion state of the combustion chamber.

Abstract: A device for a turbomachine chamber injector, including a conduit having at least a first opening, and a second opening (4), a blocking system for blocking the conduit, making it possible to regulate the passage of fluids into the conduit, the blocking system being configured to allow fuel to flow from the first opening to the second opening only from a first pressure of the fuel, for the passage of a supply of fuel, and allow air to flow from the second opening to the first opening only from a second pressure of the air, for the passage of purge air, the second pressure being greater than the first pressure.

Abstract: A combustion chamber, for example for a turbine engine, presenting an inner annular wall, an outer annular wall, and a pierced annular chamber end wall extending around an axis, the chamber end wall including at least one opening receiving a fuel injector, the opening being substantially centered on a circular line defining a first chamber end wall portion extending radially between the circular line and the inner annular wall, and a second chamber end wall portion extending radially between the circular line and the outer annular wall. First and second channels are inclined relative to a normal vector normal to the chamber end wall while extending tangentially, the first channels arranged to provide a flow of air in a first rotary direction, the second channels arranged to provide a flow of air in a second rotary direction opposite to the first rotary direction.

Abstract: A starting injector usable in all flight modes without additional cost or weight. The starting injector includes a dual fuel circuit and an air circuit. An injector for a combustion chamber of a gas turbine includes a dual fuel injection circuit including a starting fuel circuit for ignition and then for all the flight modes, and a main fuel circuit for all the flight modes after starting. The circuits include parallel pipes in a common tube having an axis. The pipe of the starting circuit is substantially in communication with a center of a spherical injector body. At the end, the pipe accommodates an injection manifold coupled to a central channel passing through a central wall of a swirler. The pipe of the main circuit is in communication with an annular channel opposite jet channels. An air circuit is guided between two portions shaped as concentric spheres.

Abstract: A low-cost combustion chamber injector device that has sturdier construction and is safer for use. Parts are configured specifically to be nested, to dispense with welding between the cellular parts. The device for injecting a fuel-air mix includes, centered on a single axis, a swirl chamber including at least two annular air suction parts, a centering guide, and a retainer ring. The annular parts have cellular conduits connecting to axial inner and outer Venturi tubes. The parts are coaxially mounted, the inner part being configured to be self-centered in the outer part by engagement of the axial and radial walls and then, after assembly, the outer part is welded to the retainer ring and to the inner part in a single radial plane.

Abstract: A device for a turbomachine chamber injector, including a conduit having at least a first opening, and a second opening (4), a blocking system for blocking the conduit, making it possible to regulate the passage of fluids into the conduit, the blocking system being configured to allow fuel to flow from the first opening to the second opening only from a first pressure of the fuel, for the passage of a supply of fuel, and allow air to flow from the second opening to the first opening only from a second pressure of the air, for the passage of purge air, the second pressure being greater than the first pressure.

Abstract: A turbine engine combustion assembly including a casing, a combustion chamber, and at least one fuel injector. The combustion chamber includes an internal wall and an external wall extending one inside the other and connected by an annular chamber base wall. The external wall of the chamber is secured to an annular external wall of the casing. The injector is attached to the annular external wall of the casing and includes a fuel ignition enclosure extending inside the casing successively through openings in the casing wall and in the external wall before opening into the chamber. At least one wall of the ignition enclosure extending between the casing wall and the combustion chamber wall includes at least one air intake port. The external wall of the combustion chamber is solidly connected to a device for plugging the air intake port according to a thermal expansion state of the combustion chamber.

Abstract: An annular wall of a combustion chamber of a turbine engine including: a cold side and a hot side; plural dilution holes to allow circulating air of the cold side to enter the hot side for dilution of an air/fuel mixture; plural cooling orifices to allow the circulating air of the cold side to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices distributed spaced axially from one another and with geometric axes inclined, in an axial direction of flow of combustion gases, by an inclination angle relative to a normal to the annular wall; plural additional cooling orifices arranged directly downstream of the dilution holes and distributed spaced axially from one another, with geometric axes arranged in a plane perpendicular to the axial direction and inclined by an angle of inclination relative to a normal to the annular wall.

Abstract: A starting injector usable in all flight modes without additional cost or weight. The starting injector includes a dual fuel circuit and an air circuit. An injector for a combustion chamber of a gas turbine includes a dual fuel injection circuit including a starting fuel circuit for ignition and then for all the flight modes, and a main fuel circuit for all the flight modes after starting. The circuits include parallel pipes in a common tube having an axis. The pipe of the starting circuit is substantially in communication with a center of a spherical injector body. At the end, the pipe accommodates an injection manifold coupled to a central channel passing through a central wall of a swirler. The pipe of the main circuit is in communication with an annular channel opposite jet channels. An air circuit is guided between two portions shaped as concentric spheres.

Abstract: A combustion chamber, for example for a turbine engine, presenting an inner annular wall, an outer annular wall, and a pierced annular chamber end wall extending around an axis, the chamber end wall including at least one opening receiving a fuel injector, the opening being substantially centered on a circular line defining a first chamber end wall portion extending radially between the circular line and the inner annular wall, and a second chamber end wall portion extending radially between the circular line and the outer annular wall. First and second channels are inclined relative to a normal vector normal to the chamber end wall while extending tangentially, the first channels arranged to provide a flow of air in a first rotary direction, the second channels arranged to provide a flow of air in a second rotary direction opposite to the first rotary direction.

Abstract: A low-cost combustion chamber injector device that has sturdier construction and is safer for use. Parts are configured specifically to be nested, to dispense with welding between the cellular parts. The device for injecting a fuel-air mix includes, centered on a single axis, a swirl chamber including at least two annular air suction parts, a centering guide, and a retainer ring. The annular parts have cellular conduits connecting to axial inner and outer Venturi tubes. The parts are coaxially mounted, the inner part being configured to be self-centered in the outer part by engagement of the axial and radial walls and then, after assembly, the outer part is welded to the retainer ring and to the inner part in a single radial plane.