Gas turbine combustion chamber wall with dampening effect on combustion chamber vibrations

Abstract

A gas turbine combustion chamber wall has an outer wall skin and an inner wall skin, with the outer wall skin (9) and the inner wall skin (10) being arranged essentially parallel to each other and spaced apart from each other by a gap (14). The outer wall skin (9) is provided with inlet openings (8) for the supply of cooling air. The inner wall skin (10) is provided with dampening openings (17), whose center axes are perpendicular to the inner wall skin (10), and with cooling openings (18), whose center axes are inclined at a certain angle to the inner wall skin (10).

Description

The invention is more fully described in the light of the accompanying drawings showing preferred embodiments. In the drawings,

FIG. 1 is a schematic sectional side view of a gas turbine combustion chamber in accordance with the present invention,

FIG. 2 is a partial sectional view of an embodiment of the gas turbine combustion chamber wall according to the present invention,

FIG. 3 is a view of an embodiment of the combustion chamber wall according to the present invention in the radial direction,

FIG. 4 is a partial sectional view of another embodiment of the gas turbine combustion chamber wall according to the present invention,

FIG. 5 is a top view of a first dampening section type as per FIG. 4,

FIG. 6 is a top view of a second dampening section type as per FIG. 4, and

FIG. 7 is a view of a combustion chamber wall according to the present invention as per FIGS. 4 to 6 in the radial direction.

Claims

1. A gas turbine combustion chamber wall comprising: an outer wall skin;an inner wall skin, with the outer wall skin and the inner wall skin being arranged essentially parallel to each other and spaced apart from each other by a gap; the outer wall skin including inlet openings for the supply of cooling air, and the inner wall skin including dampening openings having center axes that are perpendicular to the inner wall skin and cooling openings having center axes that are inclined at a certain angle to the inner wall skin.

2. A gas turbine combustion chamber wall in accordance with claim 1, wherein the cooling openings center axes are inclined at an angle of 15° to 30° to the inner wall skin.

3. A gas turbine combustion chamber wall in accordance with claim 1, and further comprising parting walls positioned in the gap between the outer wall skin and the inner wall skin to form chambers essentially in a flow direction.

4. A gas turbine combustion chamber wall in accordance with claim 1, and further comprising parting walls positioned in the gap between the outer wall skin and the inner wall skin to form chambers essentially in a circumferential direction.

5. A gas turbine combustion chamber wall in accordance with claim 1, and further comprising parting walls positioned in the gap between the outer wall skin and the inner wall skin to subdivide the gap into chambers with at least three angles.

6. A gas turbine combustion chamber wall in accordance with claim 5, wherein certain chambers each include at least one cooling opening

7. A gas turbine combustion chamber wall in accordance with claim 5, wherein certain chambers each include at least one dampening opening.

8. A gas turbine combustion chamber wall in accordance with claim 7, wherein the certain chambers each include several dampening openings.

9. A gas turbine combustion chamber wall in accordance with one of the claims 1 to 6, wherein certain chambers each include no dampening openings.

10. A gas turbine combustion chamber wall in accordance with claim 1, wherein the gap between the outer wall skin and the inner wall skin is subdivided into sections, with at least one dampening opening being arranged in a first type of section, and at least one cooling opening being arranged in a second type of section.

11. A gas turbine combustion chamber wall in accordance with claim 10, wherein all of the types of sections have a same polygonal geometrical shape.

12. A gas turbine combustion chamber wall in accordance with claim 10, wherein at least some of the sections have different geometrical shapes.

13. A gas turbine combustion chamber wall in accordance with claim 10, wherein the dampening openings are perpendicular to a plane of the combustion chamber wall skin.

14. A gas turbine combustion chamber wall in accordance with claim 10, wherein the cooling openings center axes are inclined at an angle of 15° to 30° to the inner wall skin.

15. A gas turbine combustion chamber wall in accordance with claim 10, wherein at least one cooling opening or one dampening opening, respectively, is arranged in each section.

16. A gas turbine combustion chamber wall in accordance with claim 5, wherein certain chambers each include at least one cooling opening and at least one dampening opening.

17. A gas turbine combustion chamber wall in accordance with claim 16, wherein at least one of the certain chambers includes a plurality of cooling openings.

18. A gas turbine combustion chamber wall in accordance with claim 16, wherein at least one of the certain chambers includes a plurality of dampening openings.

19. A gas turbine combustion chamber wall in accordance with claim 4, wherein certain chambers each includes at least one cooling opening.

20. A gas turbine combustion chamber wall in accordance with claim 4, wherein certain chambers each includes at least one dampening opening.