Configuration of dilution openings in a turbomachine combustion chamber wall
An annular combustion chamber of a turbomachine is provided. The combustion chamber includes an end wall provided at an upstream end of the chamber and side walls extending longitudinally from the end wall to an orifice for discharging a stream of combustion gases provided at a downstream end of the chamber. The side walls includes at least one row of openings for the intake of air for diluting the stream of combustion gases. At least one dilution opening has an upstream edge which projects toward the inside of the chamber and a downstream edge which projects toward the outside of the chamber and is asymmetric to the upstream edge with respect to a plane extending transversely to the wall. An aperture of the opening having an axis oriented in an oblique direction with respect to the wall. This direction being oriented toward the inside and toward the downstream end of the chamber.
1. An annular combustion chamber of a turbomachine comprising:
an end wall extending transversely to a longitudinal axis along which axis the chamber extends, the end wall being provided at an upstream end of the chamber;
side walls extending longitudinally from the end wall to an orifice which discharges a stream of combustion gases, the orifice being provided at a downstream end of the chamber; and
at least one row of openings disposed in the side walls for the intake of air for diluting a stream of combustion gases,
wherein at least one dilution opening includes an upstream edge which projects in the longitudinal direction upstream to downstream toward an inside of the chamber and a downstream edge which projects in the longitudinal direction downstream to upstream toward an outside of the chamber and is asymmetric to the upstream edge with respect to a plane extending transversely to the side wall, and
wherein an aperture of the opening includes an axis oriented in an oblique direction at an angle with respect to a longitudinal plane of the side wall, the axis of the aperture of the opening extends toward the inside of the chamber and toward the downstream end of the chamber.
2. The combustion chamber as claimed in claim 1 , wherein the downstream edge projects less than the upstream edge.
3. The combustion chamber as claimed in claim 1 , wherein the upstream edge is folded in an oblique direction with respect to the side wall and oriented toward the inside and toward the downstream end of the chamber.
4. The combustion chamber as claimed in claim 1 , wherein the downstream edge is folded in an oblique direction with respect to the side wall and oriented toward the outside and toward the upstream end of the chamber.
5. The combustion chamber as claimed in claim 1 , wherein a bore of the opening includes substantially cylindrical walls.
6. The combustion chamber as claimed in claim 1 , wherein the opening includes an elliptical cross section at the surface of the side wall.
7. The combustion chamber as claimed in claim 6 , wherein the elliptical cross section of the opening includes a major axis directed in the longitudinal direction of the chamber from the upstream end toward the downstream end.
8. The combustion chamber as claimed in claim 6 , wherein a major axis of the ellipse of the opening is directed substantially in a transverse direction.
9. The combustion chamber as claimed in claim 1 , wherein the projecting edge of the opening extends and smooths out transversely.
10. The combustion chamber as claimed in claim 1 , wherein the protrusion of the upstream projecting edge decreases progressively from the upstream end toward the downstream end.
11. The combustion chamber as claimed in claim 1 , wherein at least one of the upstream or downstream edge has an arch shape.
12. The combustion chamber as claimed in claim 1 , wherein at least one of the upstream or downstream edge forms an arch projecting toward the inside and toward the downstream end of the chamber.
13. The combustion chamber as claimed in claim 1 , wherein the downstream edge forms an arch projecting toward the outside and toward the upstream end of the chamber.
14. The combustion chamber as claimed in claim 12 , wherein the arch of the opening is elongated transversely.
15. The combustion chamber as claimed in claim 1 , wherein the side wall comprises a plurality of perforations for the passage of cooling air.
16. The combustion chamber as claimed in claim 15 , wherein the cooling perforations are provided in a region around the edge of the dilution opening.
17. The combustion chamber as claimed in claim 15 , wherein cooling perforations are provided around the downstream periphery of the dilution opening.
18. The combustion chamber as claimed in claim 15 , wherein the periphery of the opening has a density of cooling perforations greater than the remainder of the side wall of the chamber.
19. The combustion chamber as claimed in claim 16 , wherein the cooling perforations are directed obliquely with respect to the surface of the side wall.
20. The combustion chamber as claimed in claim 19 , wherein the cooling perforations are oriented obliquely in the direction going from the upstream end toward the downstream end when following the passage of air from the outside toward the inside of the chamber.
21. A turbomachine which comprises a combustion chamber as claimed in claim 1 .
22. A side wall element for forming a combustion chamber as claimed in claim 1 , wherein the wall element comprises at least one dilution opening having an upstream edge which projects in a longitudinal direction toward the inner side of the wall and a downstream edge which projects in the longitudinal direction toward the outside of the chamber and is asymmetric to the upstream edge with respect to a plane extending transversely to the wall, the aperture of the opening includes an oblique axis with respect to the wall which is oriented toward the inside and toward the downstream end.