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This invention relates to a combustion chamber arrangement for a gas turbine, with a number of individual combustion chambers which open into an annular gap, leading to a turbine chamber, whereby burners are arranged before the individual combustion chambers, connected to the individual combustion c

This invention relates to a combustion chamber arrangement for a gas turbine, with a number of individual combustion chambers which open into an annular gap, leading to a turbine chamber, whereby burners are arranged before the individual combustion chambers, connected to the individual combustion chambers through a turbine housing. According to the invention, said combustion chamber arrangement may be further developed, such that the cooling efficiency of the individual combustion chambers may be significantly improved, with an embodiment of simple construction, whereby at least one collar, arranged on one side of the turbine housing, facing the turbine chamber, running radially in the direction of the turbine chamber, at least partly surrounds a section of at least one individual combustion chamber whilst leaving a gap space.

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1. A combustion chamber arrangement for a gas turbine, comprising:a plurality of individual combustion chambers that open into a common annular gap transitioning into a turbine chamber;a plurality of burners arranged ahead of the individual combustion chambers, each burner connected to an individual

1. A combustion chamber arrangement for a gas turbine, comprising:a plurality of individual combustion chambers that open into a common annular gap transitioning into a turbine chamber;a plurality of burners arranged ahead of the individual combustion chambers, each burner connected to an individual combustion chamber through a turbine outer housing;a collar extending in the direction of the turbine chamber arranged on the side of the turbine outer housing toward the turbine chamber and enclosing a section of at least one of the individual combustion chambers and at least partially leaving a gap space and having a lateral recess in an area between two adjacent collars and arranged around adjacent individual combustion chambers,wherein the recesses of the adjacent collars are in contact with each other in an essentially sealing manner; anda tongue-like extension configured on the collar, that projects beyond a flattened side of a transition section and is tangential with respect to the common annular gap and providing a gap.2. The combustion chamber arrangement according to claim 1, wherein at least one collar is configured in a closed manner in the circumferential direction of the individual combustion chamber.3. The combustion chamber arrangement according to claim 1, wherein the individual combustion chamber comprises an essentially cylindrical inlet section arranged after the burner and a transition section merging into a ring-sector-shaped cross-section, whereby the collar at least partially encloses at least the inlet section.4. The combustion chamber arrangement according to claim 3, wherein the inlet section is configured cylindrically and the collar has a circular cross-sectional area and is arranged concentrically around the inlet section.5. The combustion chamber arrangement according to claim 1, wherein the tongue-like extension is configured to taper toward the annular gap.6. The combustion chamber arrangement according to claim 1, wherein the adjacent collars are connected together along the edges of the recess.7. The combustion chamber arrangement according to claim 1, wherein the combustion chamber is arranged in a gas turbine.8. A turbo-machine combustion chamber, comprising:a plurality of combustion chambers;a combustion cylinder surrounding the plurality of combustion chambers;a collar that surrounds each combustion chamber and having a lateral recess in an area between two adjacent collars and arranged around adjacent individual combustion chambers,wherein the recesses of the adjacent collars are in contact with each other in an essentially sealing manner; anda cooling medium adapted to flow within a gap formed between the combustion chamber and the collar.9. The combustion chamber as claimed in claim 8, wherein a plurality of individual combustion chambers are arranged circumferentially around a turbine rotor supported by a turbine outer housing to form a combustion chamber arrangement.10. The combustion chamber claimed in claim 9, wherein the combustion chamber opens into a common annular gap transitioning into a turbine chamber and a burner is arranged upstream of the combustion chamber and is connected to the combustion chamber through an outer housing of the turbine.11. The combustion chamber as claimed in claim 8, wherein the combustion chamber comprises an essentially cylindrical inlet section arranged downstream of the burner and a transition section merges into a ring-sector-shaped cross-section, and the collar at least partially encloses the inlet section.12. The combustion chamber as claimed in claim 11, wherein the inlet section is configured cylindrically and the collar has a circular cross-sectional area and is arranged concentrically around the inlet section.13. The combustion chamber as claimed in claim 8, wherein the combustion chamber arrangement is used in a gas turbine.14. The combustion chamber as claimed in claim 8, wherein the collar fits completely around the combustion chamber wall.