Turbomachine combustion chamber with helical air flow
View Patent ↗The invention relates to a turbomachine combustion chamber having an inner wall, an outer wall surrounding the inner wall so as to co-operate therewith to define a space forming a combustion area, a transverse wall interconnecting the inner and outer walls, and fuel injection systems. The inner wall has a plurality of inner steps each extending radially towards the outside of the inner wall, the circumferential spacing between two adjacent inner steps defining an inner cavity. The outer wall includes a plurality of outer steps each extending radially towards the inside of the outer wall, the circumferential spacing between two adjacent inner steps defining an outer cavity. At least some of the inner and outer cavities are fed with air from outside the combustion chamber in a common direction that is circumferential, and with fuel in a direction that is radial.
1. A turbomachine combustion chamber comprising:
an inner annular wall of 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;
a transverse annular wall transversely interconnecting an upstream longitudinal end of the inner wall and an upstream longitudinal end of the outer wall; and
a plurality of fuel injection systems;
wherein:
the inner wall includes a plurality of inner steps that are regularly distributed around the longitudinal axis, each inner step extending longitudinally between the upstream longitudinal end and a downstream longitudinal end of the inner wall and radially towards the outside thereof, the circumferential spacing between two adjacent inner steps defining an inner cavity;
the outer wall includes a plurality of outer steps that are regularly distributed around the longitudinal axis, each outer step extending longitudinally between the upstream longitudinal end and a downstream longitudinal end of the outer wall and radially towards the inside thereof, the circumferential spacing between two adjacent inner steps defining an outer cavity; and
the combustion chamber is configured to feed air external to the combustion chamber to at least one of the inner cavities and at least one of the outer cavities in a common direction that is substantially circumferential, and the fuel injection systems are configured to feed fuel to at least one of the inner cavities and at least one of the outer cavities in a direction that is substantially radial.
2. A combustion chamber according to claim 1 , in which at least one of the inner steps and at least one of the outer steps include respective substantially radial walls, each substantially radial wall provided with a plurality of air injection orifices opening to the outside of the combustion chamber and into the adjacent inner or outer cavity.
3. A combustion chamber according to claim 2 , in which each of the inner and outer steps includes a respective other wall that includes, in cross-section, a section that is substantially curvilinear.
4. A combustion chamber according to claim 1 , in which the fuel injection systems comprise pilot injectors alternating circumferentially with full-throttle injectors.
5. A combustion chamber according to claim 4 , 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 the fuel injection systems do not include associated air systems.
7. A turbomachine that includes a combustion chamber according to claim 1 .
8. A combustion chamber according to claim 1 , in which the fuel injection systems are configured to feed all of the outer cavities with fuel.
9. A combustion chamber according to claim 8 , in which the fuel injection systems are configured to feed all of the inner cavities with fuel.
10. A combustion chamber according to claim 8 , in which the fuel injection systems are configured to feed every other inner cavity with fuel.
11. A combustion chamber according to claim 1 , in which all of the inner cavities are fed with air external to the combustion chamber.
12. A combustion chamber according to claim 1 , in which all of the outer cavities are fed with air external to the combustion chamber.
13. A combustion chamber according to claim 1 , in which the air fed to at least one of the inner cavities and at least one of the outer cavities rotates in the same direction as compressed air coming from a compression section of the turbomachine.
14. A combustion chamber according to claim 1 , in which an annular flange is disposed at the downstream longitudinal end of the inner wall.
15. A combustion chamber according to claim 14 , in which the flange is provided with a plurality of holes regularly distributed around the longitudinal axis, said holes configured to feed cooling air to a turbine section of the turbomachine.
16. A combustion chamber according to claim 1 , in which an annular flange is disposed at the downstream longitudinal end of the outer wall.
17. A combustion chamber according to claim 16 , in which the flange is provided with a plurality of holes regularly distributed around the longitudinal axis, said holes configured to feed cooling air to a turbine section of the turbomachine.