Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber

Abstract

A gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber with a combustion chamber casing 2, 3 and several combustion chamber segments arranged in the combustion chamber casing 2, 3 and forming a combustion chamber wall 10. Each of the combustion chamber segments is supplied with cooling air with film cooling via axial and/or radial cooling holes 16, 17, with the cooling holes 16, 17 being axially spaced from each other and with dampening openings 19a being provided in this area for the introduction of cooling air.

Description

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

FIG. 1 is a schematic representation of a gas turbine with a gas turbine combustion chamber in accordance with the state of the art,

FIG. 2 is a schematic representation of the combustion chamber casing as well as of the damper wall and the combustion chamber wall in accordance with the state of the art,

FIG. 3 is a schematic representation of a first embodiment, analogically to the representation of FIG. 2,

FIG. 4 is a schematic representation of a second embodiment, analogically to FIG. 3,

FIG. 5 is another schematic representation of a further embodiment,

FIG. 6 shows forms of representation of different cross-sections of damper openings,

FIG. 7 is a schematic representation of a further embodiment with double-skin design of the combustion chamber wall,

FIG. 8 is another embodiment, analogically to FIG. 7,

FIG. 9 is another embodiment, analogically to FIGS. 7 and 8,

FIG. 10 is a schematic representation of a gas turbine combustion chamber, analogically to FIG. 1 with arrangement of the combustion chamber segments in single-skin design, and

FIG. 11 is a schematic representation, analogically to FIG. 10 with arrangement of the combustion chamber segments in double-skin design.

In the embodiments shown, identical parts are identified by the same reference numerals.

FIG. 1 schematically shows a cross-section of a gas-turbine combustion chamber according to the state of the art. Here, compressor exit vanes 1, a combustion chamber outer casing 2 and a combustion chamber inner casing 3 are shown in schematic representation. Reference numeral 4 indicates a burner with arm and head (diffusion flame). A combustion chamber head 5 is associated with a combustion chamber wall 6 with cooling rings 6a. Turbine inlet vanes are designated with the reference numeral 7.

FIG. 2 schematically shows, in detail view, a damper in accordance with the state of the art, with a combustion chamber wall 10 being provided with dampening and cooling holes 11 of which each extends perpendicularly to the combustion chamber wall 10. The compressor exit air is designated with reference numeral 12, while the flame and the smoke gas from the lean burner are indicated by the arrowhead 13. Disposed between damper wall 9 and combustion chamber wall 10 is a damper interspace 14. Cooling air is supplied into this damper interspace 14 via supply holes 8.

In the embodiment shown in FIG. 3, the individual combustion chamber segments, which form a single-skin combustion chamber wall, are slightly inclined towards the longitudinal axis, resulting in a tile-style, offset design. A laminar inflow of compressor exit air 12 is provided via essentially axial cooling holes 16. In addition, essentially radial cooling holes 17 can be provided. The respective fore combustion chamber segment is provided with a lip 18 on the cooling ring.

For dampening, air is introduced via additional dampening openings 19a, with the dampening volume being formed by the distance 19b to the casing 2 or 3.

The embodiment in FIG. 4 differs in that no radial cooling holes 17 are provided, but several rows of essentially axial cooling holes 16 are disposed in radially staggered arrangement.

The embodiment in FIG. 5 (in connection with the variants of FIG. 6) shows non-cylindrical dampening openings which can have the greatest variety of cross-sections along their axial length as well as altogether.

The embodiments of FIGS. 7 to 9 each show a double-skin design of the combustion chamber wall. Here, a damper casing 20 is additionally provided which encloses a dampening volume 21. The dampening volume 21 can be circumferentially subdivided and/or provided with additional filler material (see above). The embodiments in FIGS. 8 and 9 each show that one end of the damper casing is firmly attached (22), while the other area has a sliding or slideable joint 23. This enables thermal longitudinal expansion to be compensated.

FIGS. 10 and 11 show two embodiments with single and double-skin design, with the dampers being arranged closely to the heat release zone of the combustion chamber.

LIST OF REFERENCE NUMERALS

1 Compressor exit vanes

2 Combustion chamber outer casing

3 Combustion chamber inner casing

4 Burner with arm and head (diffusion flame)

5 Combustion chamber head

6 Combustion chamber wall with cooling rings 6a

7 Turbine inlet vanes

8 Supply hole

9 Damper wall

10 Combustion chamber wall

11 Dampening and cooling holes

12 Compressor exit air

13 Flame and smoke gas from lean burner

14 Damper interspace between damper wall 9 and combustion chamber wall 10

15

16 Essentially axial cooling holes

17 Essentially radial cooling holes

18 Lip on cooling ring

19 a Dampening openings

19 b Damper space

19 c Non-cylindrical dampening openings

20 Damper casing between two cooling rings

21 Dampening volume (circumferentially subdivided, if necessary)

22 Firm attachment (e.g. welded or bolted flange)

23 Slideable joint (sliding seat with or without sealing)

24 Lean burner

Claims

1. A gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber, comprising: a combustion chamber casing;several combustion chamber segments arranged in the combustion chamber casing and forming a combustion chamber wall, each of the combustion chamber segments being supplied with cooling air with film cooling via at least one of axial cooling holes and radial cooling holes, with the cooling holes being axially spaced from each other; anddampening openings being provided in the combustion chamber wall for the introduction of air.

2. A gas-turbine combustion chamber wall in accordance with claim 1, wherein each of the combustion chamber elements is annular and conical.

3. A gas-turbine combustion chamber wall in accordance with claim 2, wherein the combustion chamber elements overlap each other in their edge zones.

4. A gas-turbine combustion chamber wall in accordance with claim 3, wherein the combustion chamber segments are arranged closely to a zone of maximum heat release of the gas turbine combustion chamber.

5. A gas-turbine combustion chamber wall in accordance with claim 3, wherein the combustion chamber segments are arranged centrally between burners and turbine inlet vanes.

6. A gas-turbine combustion chamber wall in accordance with claim 5, wherein the combustion chamber segments are of a single-wall design.

7. A gas-turbine combustion chamber wall in accordance with claim 5, wherein the combustion chamber segments are of a double-wall design and at least one include a damper casing arranged radially outward and forming a circumferential dampening volume.

8. A gas-turbine combustion chamber wall in accordance with claim 7, wherein the damper casing is firmly attached to the combustion chamber segment.

9. A gas-turbine combustion chamber wall in accordance with claim 7, wherein one end of the damper casing is firmly attached to the combustion chamber segment and an other end is slideably connected to the combustion chamber segment.

10. A gas-turbine combustion chamber wall in accordance with claim 7, wherein the circumferential dampening volume of the damper casing is subdivided into individual chambers.

11. A gas-turbine combustion chamber wall in accordance with claim 7, wherein the circumferential dampening volume of the damper casing is at least partly filled with air-permeable material.

12. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber wall is made of metal.

13. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber wall is made of ceramics.

14. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber wall is made of CMC.

15. A gas-turbine combustion chamber wall in accordance with claim 1, and further comprising effusion cooling holes arranged between the dampening openings, which essentially extend perpendicularly through the combustion chamber wall, with the effusion cooling holes being oriented at a shallow angle to a surface of the combustion chamber wall.

16. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber elements overlap each other in their edge zones.

17. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber segments are arranged closely to a zone of maximum heat release of the gas turbine combustion chamber.

18. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber segments are of a single-wall design.

19. A gas-turbine combustion chamber wall in accordance with claim 1, wherein the combustion chamber segments are of a double-wall design and at least one include a damper casing arranged radially outward and forming a circumferential dampening volume.

20. A gas-turbine combustion chamber wall in accordance with claim 19, wherein one end of the damper casing is firmly attached to the combustion chamber segment and an other end is slideably connected to the combustion chamber segment.