CONFIGURATION OF DILUTION OPENINGS IN A TURBOMACHINE COMBUSTION CHAMBER WALL

Abstract

The invention relates to an annular combustion chamber of a turbomachine having an end wall and side walls (3) extending longitudinally from the end wall, situated at the upstream end (M) of the chamber (1), to an orifice for discharging a stream of combustion gases, situated at the downstream end (V) of the chamber (1), the side walls (3) comprising at least one row of openings (30) for the intake of air for diluting the stream of combustion gases.

Description

3—KEY TO THE FIGURES

Other distinguishing features or advantages of the invention will become clearly apparent from the remainder of the description given by way of nonlimiting example and with reference to the appended figures, in which:

FIG. 1B, described above, shows a turbomachine combustion chamber, viewed in axial section along the axis of the turbomachine, accompanied by detailed sectional views 1A, 1C and 1D showing various configurations of dilution air intake openings with symmetrical edges according to the prior art;

FIG. 2 is a schematic view in longitudinal section of a first embodiment of a dilution opening provided with asymmetric edges (projecting upstream edge, square downstream edge) according to the invention;

FIG. 3 is a schematic sectional view of a second embodiment of a dilution opening with an upstream edge projecting strongly toward the inside and a downstream edge projecting gently toward the outside, according to the invention;

FIG. 4 is a schematic sectional view of a third embodiment of a dilution opening with an upstream edge projecting toward the inside and a downstream edge likewise projecting, but toward the outside, according to the invention;

FIG. 5 shows, from various angles of view, an example of the shape of the dilution opening according to the first embodiment of the invention (inside view 5A, outside view 5B, profile view 5C and shallow-angle view 5D);

FIG. 6 shows, from various points of view, a combustion chamber wall provided with dilution openings with an upstream edge projecting toward the inside and a downstream edge projecting toward the outside, according to the third embodiment of the invention;

FIGS. 7A and 7B show an inside view and a shallow-angle outside view along the longitudinal axis of a combustion chamber wall provided with dilution openings with an upstream edge projecting toward the inside and a downstream edge projecting toward the outside, according to the third embodiment of the invention, the opening having the shape of a transversely extending ellipse;

FIGS. 8B and 8A show an overall view and a detail view of the outside of a combustion chamber wall provided with a plurality of dilution air intake openings and with a multitude of cooling air injection perforations arranged around the opening, according to the invention; and

FIG. 9 shows a turbomachine comprising a combustion chamber according to the invention.

Claims

1. An annular combustion chamber of a turbomachine having an end wall extending transversely to a longitudinal axis along which the chamber extends, and side walls extending longitudinally from the end wall, situated at the upstream end of the chamber, to an orifice for discharging the stream of combustion gases, situated at the downstream end of the chamber, the side walls comprising at least one row of openings for the intake of air for diluting a stream of combustion gases, wherein 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, the aperture of the opening having an axis oriented in an oblique direction at an angle with respect to the wall, this direction being oriented toward the inside and toward the downstream end of the chamber.

2. The combustion chamber as claimed in claim 1, in which the downstream edge projects less than the upstream edge.

3. The combustion chamber as claimed in claim 1 or 2, in which 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 one of claims 1 to 3, in which 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 one of claims 1 to 4, in which the bore of the opening has substantially cylindrical walls.

6. The combustion chamber as claimed in one of claims 1 to 5, in which the opening has an elliptical cross section at the surface of the side wall.

7. The combustion chamber as claimed in claim 6, in which the elliptical cross section of the opening has a major axis directed in a longitudinal direction of the chamber going from the upstream end toward the downstream end.

8. The combustion chamber as claimed in claim 6, in which the major axis of the ellipse of the opening is directed substantially transversely.

9. The combustion chamber as claimed in one of claims 1 to 8, in which the projecting edge of the opening extends and smooths out transversely.

10. The combustion chamber as claimed in one of claims 1 to 9, in which the protrusion of the upstream projecting edge decreases progressively from the upstream end toward the downstream end.

11. The combustion chamber as claimed in one of claims 1 to 10, in which at least one projecting edge has an arch shape.

12. The combustion chamber as claimed in one of claims 1 to 11, in which the upstream edge forms an arch projecting toward the inside and toward the downstream end of the chamber.

13. The combustion chamber as claimed in one of claims 1 to 12, in which 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 or 13, in which the arch or arches of the opening is or are elongated transversely.

15. The combustion chamber as claimed in one of claims 1 to 14, wherein the side wall additionally comprises a plurality of perforations for the passage of cooling air.

16. The combustion chamber as claimed in claim 15, in which the cooling perforations are formed in a region around the edge of the dilution opening.

17. The combustion chamber as claimed in claim 15 or 16, in which cooling perforations are formed around the downstream periphery of the dilution opening.

18. The combustion chamber as claimed in one of claims 15 to 17, in which 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 one of claims 16 to 18, in which the cooling perforations are directed obliquely with respect to the surface of the side wall.

20. The combustion chamber as claimed in claim 19, in which 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 one of the preceding claims.

22. A side wall element for forming a combustion chamber as claimed in one of claims 1 to 20, wherein the wall element comprises at least one dilution opening having an upstream edge which projects toward the inner side of the wall 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, the aperture of the opening having an oblique axis with respect to the wall, this axis being oriented toward the inside and toward the downstream end.