TRANSVERSE WALL OF A COMBUSTION CHAMBER PROVIDED WITH MULTI-PERFORATION HOLES

Abstract

The invention relates to an annular wall (10) intended to connect transversely longitudinal walls of an annular combustion chamber of a turbine engine. The wall (10) is essentially flat, inclined in relation to a longitudinal axis of the turbine engine, and comprises a plurality of deflectors (16), each formed by an essentially rectangular flat sheet. The deflectors are mounted on the wall and each comprise an aperture for the installation of a fuel injection system, a plurality of multi-perforation holes (18) formed in relation to the deflectors (16) around their aperture so as to allow a passage of air intended for the cooling of the deflectors, and means (20) to force the flow of air for cooling the deflectors to flow radially around the fuel injection systems.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

Other characteristics and advantages of the present invention can be derived from the description provided hereinafter, by reference to the appended drawings, which illustrate an embodiment of the invention in a non-limitative manner. In the Figures:

FIG. 1 is a longitudinal section of a combustion chamber of a turbine engine in its surroundings;

FIG. 2 is a partial view of the transverse wall according to an embodiment of the invention;

FIG. 3 represents curves showing the development of the gap between the deflectors and a transverse wall;

FIG. 4 is a sectional view according to IV-IV of FIG. 3; and

FIGS. 5 and 6 are partial views of transverse walls according to another embodiment of the invention.

Claims

1. Annular wall (10) intended to connect transversely longitudinal walls (6, 8) of an annular combustion chamber (4) of a turbine engine, said wall (10) being essentially flat, inclined in relation to a longitudinal axis (X-X) of the turbine engine, and comprising: a plurality of deflectors (16), each formed by an essentially rectangular flat sheet, said deflectors being mounted on the annular wall (10) and each comprising an aperture (17) for the installation of a fuel injection system (14); anda plurality of multi-perforation holes (18) formed in relation to the deflectors (16) around their aperture (17) so as to allow a passage of air intended for the cooling of the said deflectors;characterised in that each deflector (16) comprises means to force the flow of air for cooling the deflectors to flow radially in relation to the longitudinal axis (X-X) of the turbine engine around the fuel injection systems.

2. Wall according to claim 1, in which each deflector (16) comprises at least two deformations (20) forming chicanes for the movement of the flow of cooling air, said deformations (20) extending radially in relation to the longitudinal axis (X-X) of the turbine engine on both sides of the aperture (17) of the said deflector.

3. Wall according to claim 2, in which the deformations of the deflector are in the form of throats (20).

4. Wall according to claim 3, in which the throats (20) each have a thickness (e) of between 1 and 2 mm.

5. Wall according to claim 1, in which the distance (g) between the respective external radial ends (10c, 16c) of the wall (10) and the deflectors (16) at the level of a radial plane of symmetry (P) of the deflectors is less than that (h) at the level of the lateral ends of the said deflectors.

6. Wall according to claim 1, in which the distance (g) between the respective external radial ends (10c, 16c) of the wall (10) and the deflectors (16) at the level of a radial plane of symmetry (P) of the deflectors is greater than that (h) at the level of the lateral ends of the said deflectors.

7. Combustion chamber (4) of a turbine engine, comprising at least one annular wall (10) according to any one of claims 1 to 6.

8. Turbine engine comprising a combustion chamber (4) having at least one annular wall (10) according to any one of claims 1 to 6.