Annular combustion chamber for a turbine engine

1. An annular combustion chamber for a turbine engine, the chamber comprising:

coaxial annular inner wall and outer wall connected together at upstream ends thereof by an annular wall forming a chamber end wall; and

an annular row of fuel injectors including heads engaged in fuel injection systems mounted in openings in the chamber end wall, each injector head having a longitudinal axis and including at least one fuel-passing helical channel which has an axial component parallel to said longitudinal axis for causing fuel to rotate about said longitudinal axis of the injector head, and each injection system including at least one swirler located on a same longitudinal axis as the injector head and including substantially radial air-passing channels having respective longitudinal axes along which each air-passing channel has a longitudinal section,

wherein the longitudinal axes of longitudinal sections of the air-passing channels have each an axial component parallel to said longitudinal axis and are inclined relative to said longitudinal axis of the at least one swirler at an angle that is substantially equal to within ±10° of a helix angle of the helical channel of the injector head, and the longitudinal axes of the longitudinal sections, which longitudinal axes have each an axial component parallel to said longitudinal axis, are oriented in a same direction as said at least one fuel-passing helical channel about the longitudinal axis of the at least one swirler, and

wherein the air-passing channels are formed by slots closed by an upstream radial face of a venturi and leading axially downstream, and said air-passing channels are separated from one another by substantially radial vanes comprising purge orifices.

2. The annular combustion chamber according to claim 1 , wherein each fuel injector includes a first fuel circuit feeding a first helical channel and a second fuel circuit that is independent and that feeds a second helical channel of diameter greater than diameter of the first helical channel, the axes of the sections of the swirler channels being inclined at a same angle and in a same direction as the second helical channel.

3. The annular combustion chamber according to claim 1 , wherein, perpendicularly to said longitudinal axis, each channel of the swirler includes a transverse section of a shape that is square or rectangular.

4. The annular combustion chamber according to claim 1 , wherein the swirler includes a cylindrical peripheral rim at its downstream end for attaching to the venturi.

5. The annular combustion chamber according to claim 1 , wherein the channels of the swirler are separated from one another by vanes, each of the vanes including at least one air-passing through orifice that is inclined relative to the longitudinal axis of the swirler by a same angle and the through orifice is in a same direction as the axes of the sections of the channels situated on either side of the vane.

6. The annular combustion chamber according to claim 1 , wherein:

said at least one swirler comprises an upstream swirler and a downstream swirler, the upstream swirler being disposed upstream of the downstream swirler on said longitudinal axis, and

each injection system includes a mixer bowl including at least one annular row of air-passing orifices for passing air that is to mix with the fuel, axes of the sections of the upstream swirler channels being inclined at a same angle and in a same direction as the helical channel of the injector head, and axes of the sections of the downstream swirler channels being oriented about the longitudinal axis of the swirler in a same direction as the helical channel of the injector head.

7. The annular combustion chamber according to claim 1 , wherein the channels are separated from one another by vanes and are contained in a radial plane, trailing edges or radially inner ends of the vanes extending over a frustoconical surface flaring downstream around the longitudinal axis of the injection system.

8. The annular combustion chamber according to claim 1 , wherein each injection system comprises the venturi and a mixer bowl situated downstream from the swirler, the swirler configured to ventilate the venturi by guiding a stream of air leaving the swirler along an inner surface of the venturi.

9. The annular combustion chamber according to claim 1 , wherein each injection system comprises support and centering means for an injector head, the support and centering means comprising an inner cylindrical surface that is to surround the head of the injector and that is connected at a downstream end thereof to a smaller-diameter upstream end of a frustoconical surface.

10. A turbine engine comprising an annular combustion chamber according to claim 1 .

11. The annular combustion chamber according to claim 1 , wherein the air-passing channels include lateral walls parallel to the longitudinal axes of the longitudinal sections, and the lateral walls of each of the air-passing channels are connected together at an upstream end thereof by an upstream wall perpendicular to the longitudinal axis of the swirler.

12. The annular combustion chamber according to claim 11 , wherein the air-passing channels are closed at a downstream end thereof by an upstream racial face of the venturi that defines downstream walls of the air-passing channels.

13. An annular combustion chamber for a turbine engine, the chamber comprising:

coaxial annular inner wall and outer wall connected together at upstream ends thereof by an annular wall forming a chamber end wall; and

an annular row of fuel injectors including heads engaged in fuel injection systems mounted in openings in the chamber end wall, each injector head having a longitudinal axis and including at least one fuel-passing helical channel which has an axial component parallel to said longitudinal axis for causing fuel to rotate about said longitudinal axis of the injector head, and each injection system including at least one swirler located on a same longitudinal axis as the injector head and including substantially radial air-passing channels having respective longitudinal axes along which each air-passing channel has a longitudinal section,

wherein the longitudinal axes of longitudinal sections of the air-passing channels have each an axial component parallel to said longitudinal axis and are inclined relative to said longitudinal axis of the at least one swirler at an angle that is substantially equal to within ±10° of a helix angle of the helical channel of the injector head, and the longitudinal axes of the longitudinal sections, which longitudinal axes have each an axial component parallel to said longitudinal axis, are oriented in a same direction as said at least one fuel-passing helical channel about the longitudinal axis of the at least one swirler,

wherein the air-passing channels are formed by slots closed by an upstream radial face of a venturi and leading axially downstream, and said air-passing channels are separated from one another by substantially radial vanes, and

wherein said swirler is free of purge orifice.

14. An annular combustion chamber for a turbine engine, the chamber comprising:

coaxial annular inner wall and outer wall connected together at upstream ends thereof by an annular wall forming a chamber end wall; and

an annular row of fuel injectors including heads engaged in fuel injection systems mounted in openings in the chamber end wall, each injector head having a longitudinal axis and including at least one fuel-passing helical channel which has an axial component parallel to said longitudinal axis for causing fuel to rotate about said longitudinal axis of the injector head, and each injection system including at least one swirler located on a same longitudinal axis as the injector head and including substantially radial air-passing channels having respective longitudinal axes along which each air-passing channel has a longitudinal section,

wherein the longitudinal axes of longitudinal sections of the air-passing channels have each an axial component parallel to said longitudinal axis and are inclined relative to said longitudinal axis of the at least one swirler at an angle that is substantially equal to within ±10° of a helix angle of the helical channel of the injector head, and the longitudinal axes of the longitudinal sections, which longitudinal axes have each an axial component parallel to said longitudinal axis, are oriented in a same direction as said at least one fuel-passing helical channel about the longitudinal axis of the at least one swirler, so as to limit a recirculation of air and fuel mixture downstream from the swirler.