Turbomachine combustion chamber with helical air flow
View Patent ↗A turbomachine combustion chamber includes an inner annular wall, an outer annular wall surrounding the inner wall so as to co-operate therewith to define an annular space forming a combustion area, a plurality of fuel injector systems including pilot injectors alternating circumferentially with full-throttle injectors, and at least one air admission opening out into the upstream end of the combustion area in a substantially longitudinal direction. The outer wall has a plurality of pilot cavities extending between the two longitudinal ends of the outer wall and extending radially towards thereof, the pilot cavities being fed with air from outside the combustion chamber in a common substantially circumferential direction. Each pilot injector opens out radially into a pilot cavity, and each full-throttle injector opens out radially between two adjacent pilot cavities.
1. A turbomachine combustion chamber comprising:
an inner annular wall about a longitudinal axis;
an outer annular wall centered on the longitudinal axis and surrounding the inner wall so as to co-operate therewith to define an annular space forming a combustion area; and
a plurality of fuel injector systems comprising pilot injectors alternating circumferentially with full-throttle injectors;
the combustion chamber further comprising at least one air admission opening opening out into the upstream end of the combustion area in a direction that is substantially longitudinal;
wherein the outer wall includes a plurality of pilot cavities that are regularly distributed around the longitudinal axis, each pilot cavity extending longitudinally between the two longitudinal ends of the outer wall and radially towards the outside thereof, the pilot cavities being fed with air from outside the combustion chamber in a common substantially circumferential direction; and
wherein each pilot injector opens out radially into a pilot cavity, and each full-throttle injector opens out radially between said adjacent pilot cavities.
2. A combustion chamber according to claim 1 , in which each pilot cavity is closed at its upstream end and open at its downstream end.
3. A combustion chamber according to claim 1 , in which each pilot cavity is defined circumferentially by two substantially radial partitions, one of the partitions including a plurality of air injection orifices open to the outside of the combustion chamber and leading to said pilot cavity.
4. A combustion chamber according to claim 3 , in which the other partition of each pilot cavity presents in cross-section, a section that is substantially curvilinear.
5. A combustion chamber according to claim 1 , in which the full-throttle injectors are offset axially downstream relative to the pilot injectors.
6. A combustion chamber according to claim 1 , in which it does not have a wall transversely interconnecting the upstream longitudinal ends of the inner and outer walls.
7. A combustion chamber according to claim 1 , in which the fuel injector systems do not have associated air systems.
8. A combustion chamber according to claim 1 , further including an inner annular fairing mounted on the inner wall extending the upstream end thereof, and an outer annular fairing mounted on the outer wall and extending the upstream end thereof.
9. A turbomachine, including a combustion chamber according to claim 1 .
10. A combustion chamber according to claim 1 , in which the pilot fuel injectors and the full-throttle injectors open out into the combustion area in a substantially radial direction.
11. A combustion chamber according to claim 10 , in which the pilot fuel injectors and the full-throttle injectors extend through the outer annular wall.
12. A combustion chamber according to claim 10 , in which the pilot fuel injectors are arranged relative to said pilot cavities to mix and burn air in the pilot cavities with fuel injected from said pilot fuel injectors.