RESONATOR RING FOR COMBUSTION CHAMBER SYSTEMS

Abstract

A resonator formed as a ring for a gas turbine combustion chamber, includes an outer shell and an inner shell, wherein one part of a hot gas channel of the gas turbine combustion chamber is delimited by the inner shell, wherein at least one Helmholtz resonator is arranged between the outer shell and the inner shell.

Claims

1. A resonator, comprising: an outer shell and an inner shell, wherein one part of a hot gas channel of the tubular combustion chamber is delimited by the inner shell, wherein at least one Helmholtz resonator is present between the outer shell and the inner shell.

2. The resonator as claimed in claim 1, comprising a large number of Helmholtz resonators.

3. The resonator as claimed in claim 1, wherein there is a single Helmholtz resonator having only one cavity.

4. The resonator as claimed in claim 1, wherein there is a single Helmholtz resonator having a plurality of resonator volumes due to partition walls.

5. The resonator as claimed in claim 1, wherein, for each resonator, there is one web as a connection to the outer shell.

6. The resonator as claimed in claim 1, wherein respective resonator volumes have one or more channels toward the inner shell and thus have connections to a hot gas channel of a tubular combustion chamber.

7. The resonator as claimed in claim 1, wherein there is only one channel per cavity and only one neck per Helmholtz resonator to a hot gas channel of a tubular combustion chamber.

8. The resonator as claimed in claim 1, wherein there is a plurality of channels per cavity to a hot gas channel of a tubular combustion chamber.

9. The resonator as claimed in claim 1, wherein there is only one neck per Helmholtz resonator.

10. The resonator as claimed in claim 1, wherein there is a plurality of necks for a cavity.

11. The resonator as claimed in claim 1, wherein there is a plurality of channels and only one neck for a cavity.

12. The resonator as claimed in claim 1, which is produced by an additive method.

13. The resonator as claimed in claim 1, further comprising dimples on inner surfaces of the inner and outer shells.

14. A tubular combustion chamber, comprising: a resonator as claimed in claim 1.

15. The resonator as claimed in claim 1, wherein the resonator is designed as a ring.

16. The resonator as claimed in claim 1, wherein the resonator is designed for a tubular combustion chamber.

17. The resonator as claimed in claim 16, wherein the resonator is designed for a gas turbine.

18. The resonator as claimed in claim 5, wherein, for each resonator, there is only one web.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In the drawings:

[0023] FIGS. 1 and 8 show a tubular combustion chamber,

[0024] FIG. 2 shows a resonator ring,

[0025] FIGS. 3-7 show resonator volumes.

DETAILED DESCRIPTION OF INVENTION

[0026] The figures and the description represent only exemplary embodiments of the invention.

[0027] FIGS. 1 and 8 schematically illustrate part of a tubular combustion chamber 1.

[0028] In the interior of the tubular combustion chamber 1, that is to say in the hot gas channel 16 of the tubular combustion chamber 1, hot gas flows in the chamber flow direction 15 to the turbine.

[0029] The tubular combustion chamber 1 has, along and around the hot gas channel 16 of the tubular combustion chamber 1, in an axial section, a resonator 6, in which cooling air 19 (FIG. 6), in particular from the compressor, advantageously flows counter to the direction of flow of the chamber 15.

[0030] The resonator 6 is advantageously of annular design. In this case, the cooling air flows around resonators (FIGS. 2-8), as illustrated in the figures below.

[0031] FIG. 2 shows an illustrative resonator 6 according to FIG. 1. The resonator 6 in the form of a ring can be of one-piece or segmental construction.

[0032] Between an outer shell 20 and an inner shell 30, the resonator 6 has a closed cooling system with Helmholtz resonators 25′, 25″, . . . (FIG. 3ff).

[0033] It is also possible to see openings 13 of the Helmholtz resonators 25′ to the hot gas channel 16 of the tubular combustion chamber 1.

[0034] The hot air from the burner 40 (FIG. 8) flows in the chamber flow direction 15 to the turbine, whereas the cooling air 19 (FIG. 6) flows in the cooling air flow direction 18 (FIG. 6) in the resonator 6, counter to the chamber flow direction 15.

[0035] FIG. 3 shows a first further detail of FIG. 2 and discloses a cross section through an illustrative resonator 6′ and a first exemplary embodiment of Helmholtz resonators 25′, which is or are present between the outer shell 20′ and the inner shell 30′, between which the cooling air 19 flows. The Helmholtz resonators 25′ are present between the outer shell 20′ and the inner shell 30′.

[0036] The cooling air 19 flows around the individual Helmholtz resonators 25′ from all sides.

[0037] The hollow body 26′ of the Helmholtz resonator 25′, formed by a wall 4′, is here spaced apart from the outer shell 20′ and the inner shell 30′.

[0038] Preferably round, disk-shaped hollow bodies 26′ form the Helmholtz resonator 25′.

[0039] The Helmholtz resonator 25′ is connected to the outer shell 20′ via a web 10′, which is, in particular, solid.

[0040] The cavity 26′ of the Helmholtz resonator 25′ is furthermore connected by a channel 27′, in particular a channel 27′ of annular cross section, of a neck 28′ to the hot gas channel 16 of the tubular combustion chamber 1, which is formed by the inner shell 30′, via an opening 13′.

[0041] The diameters of the web 10′ and/or of the neck 28′ to which the Helmholtz resonators 25′ are connected between the two shells 20′, 30′ are clearly different from the diameter of the hollow body 26′. The ratio of the diameters is advantageously at least 3:1 for diameters of hollow body 26′ to neck 28′ or web 10′.

[0042] A large number of individual Helmholtz resonators 25′ is arranged in the circumferential direction of the resonator 6′.

[0043] As also illustrated in FIG. 3, there is always a sufficient gap between individual Helmholtz resonators 25′ in an axial direction, parallel to the chamber flow direction 15, and the distance is advantageously greater than the diameter of the Helmholtz resonator 25′. For this purpose, advantageously radially offset, further Helmholtz resonators 25′ are then arranged so as to be axially offset.

[0044] Other arrangements of the individual Helmholtz resonators 25′ are possible.

[0045] FIG. 4 shows a further exemplary embodiment having a resonator 6″, here advantageously designed as a ring, which has a single common cavity 26″ as a Helmholtz resonator 25″.

[0046] Between the outer shell 20″ and the inner shell 30″, there is, as it were, an intermediate shell 22, which represents the large common cavity 26″ over the width of the resonator 6″.

[0047] Starting from the one cavity 26″ of the resonator 6″, there are a large number of channels 27″ to the hot gas channel 16 of the tubular combustion chamber 1, which in turn are each formed by necks 28″, advantageously like the necks 28′ of the Helmholtz resonators 25′ in FIG. 3.

[0048] A single, large cavity 26′″ is thus connected to the hot gas channel 16 by means of a large number of necks 28″.

[0049] The necks 28″ can be constructed and distributed like the necks 28′ according to FIG. 3.

[0050] FIG. 5 shows a further exemplary embodiment of a resonator 6′″, in which there are segmented cavities 26′″, which are formed, as it were, on the basis of FIG. 4, by partition walls 33 inside the cavity 26′″ (FIG. 4). A plurality of annular cavities 26′″ is, as it were, arranged in series in the axial direction 15.

[0051] The necks 28′″ can be distributed like the necks 28′ according to FIG. 3 or 4.

[0052] Likewise, there is a plurality of channels 27′″ per cavity 26′″.

[0053] FIG. 7 shows a cavity 26.sup.V which has two channels 2D in a neck 28.sup.V.

[0054] Such Helmholtz resonators 25.sup.V can be used singly, in multiples or completely for the resonator 6.sup.V.

[0055] In comparison with FIG. 3, the neck 28.sup.V has two or more channels 2′7.sup.V.

[0056] It is clear that further exemplary embodiments are encompassed by the invention since the description, figures and exemplary embodiments represent the invention.

[0057] This geometry is advantageously produced by an additive production method such as a powder bed method, in particular a laser sintering method and a laser melting method. Restriction to these specific additive manufacturing methods is not specified and are conceivable.

[0058] FIG. 8 shows the installation situation of a resonator 6′″ according to FIG. 5 in a tubular combustion chamber.