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A device for a combustion chamber of a gas turbine for controlling the intake of gas into the combustion zone of the combustion chamber. The device includes a control element that is arranged outside the combustion chamber. This control element has a first covering for at least a first inlet to the

A device for a combustion chamber of a gas turbine for controlling the intake of gas into the combustion zone of the combustion chamber. The device includes a control element that is arranged outside the combustion chamber. This control element has a first covering for at least a first inlet to the combustion zone and is displaceable in relation to the combustion chamber. There is also a support for the control element that is connected to the cover. The cover is displaceable relative to the combustion chamber and a support (16) for the control element (12, 12') is connected to the cover. The support (16) is accommodated in a structure (4) at a rear of the combustion chamber.

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The invention claimed is: 1. A device for controlling the intake of gas into a combustion zone (10, 11) of the combustion chamber (1 ) of a gas turbine having a combustion chamber cover (4), said device comprising: a control element (12, 12') arranged outside the combustion chamber (1); said contro

The invention claimed is: 1. A device for controlling the intake of gas into a combustion zone (10, 11) of the combustion chamber (1 ) of a gas turbine having a combustion chamber cover (4), said device comprising: a control element (12, 12') arranged outside the combustion chamber (1); said control element (12, 12') further comprising a first cover means (13) for covering at least a first inlet to the combustion zone, said First cover means being displaceable relative to the combustion chamber (1); and a support means (16) connected to the first cover means (13) for providing support to the control element (12, 12'), said support means (16) being accommodated interiorly within the combustion chamber cover (4) rearwardly located with respect to the combustion chamber (1) and said support means (16) being substantially concentrically oriented relative to a centerline of the combustion chamber (1). 2. The device as recited in claim 1, wherein said control element (12, 12') is exclusively supported on said support means (16) in an operating configuration, without contact with the combustion chamber (1). 3. The device as recited in claim 1, wherein the structure (4) within which the support means (16) is accommodated is thermally insulated from the combustion chamber (1). 4. The device as recited in claim 1, wherein the support means (16) extends through the combustion chamber cover (4). 5. The device as recited in claim 1, wherein the support means (16), when accommodated in combustion chamber cover (4 ), is radially oriented outside a pilot distributor (2) to the combustion chamber. 6. The device as recited in claim 5, wherein the support means (16) extends around the pilot distributor (2) and the support means (16) is supported against the structure (4) at an outer surface (20) of the support means (16). 7. The device as recited in claim 1, wherein the support means (16) has a circular cross-sectional shape. 8. The device as recited in claim 1, wherein the first cover means (13) has at least one recess (14, 15) extending through a wall (13) thereof in a substantially radial direction of the control element (12, 12'). 9. The device as recited in claim 8, wherein said at least one recess (14, 15) in the first cover means (13) and first inlet to the combustion chamber, when in registration with one another, are configured to form a through-duct for gas passing from outside the combustion chamber to inside the combustion chamber. 10. The device as recited in claim 9, wherein the first cover means (13) further comprises at least two sets of recesses, a first set of recesses being arranged at a distance from a second set of recesses with respect to a longitudinal direction of the combustion chamber. 11. The device as recited in claim 8, wherein the control element (12, 12') comprises an annular cover section ( 18) configured to cover at least one inlet to the combustion zone of the combustion chamber (1) different from the first inlet, the cover section (18) being arranged at a lesser distance from a centerline of the control element (12, 12') than the first cover means (13), and the annular cover section (18) having at least one recess (19) therein. 12. The device as recited in claim 8, wherein the wall of the first cover means (13) is ring-shaped and said at least one recess (14, 15) extends therethrough. 13. The device as recited in claim 1, wherein the first cover means (13) is rotatable relative to the combustion chamber ( 1). 14. The device as recited in claim 1, wherein the support means (16) and the first cover means (13) are integral with one another. 15. The device as recited in claim 1, wherein the control element (12, 12') is rotatable relative to the combustion chamber cover (4) within which the support means (16) is accommodated. 16. The device as recited in claim 1, wherein the first cover means (13) is arranged at a greater radial distance from a central axis through the control element (12, 12') than the support means (16). 17. The device as recited in claim 1, wherein the first inlet extends through a combustion chamber wall and forms a gas inlet into at least one swirl (8, 9) arranged in the combustion chamber (1). 18. The device as recited in claim 1, wherein the control element (12, 12') further comprises a second cover means (30) configured to cover at least a second inlet (33) to the combustion zone, the at least one second inlet being arranged at a distance from the at least one first inlet in a longitudinal direction of the combustion chamber (1). 19. The device as recited in claim 18, wherein the second cover means (30) has at least one recess (32) that extends in a substantially radial direction through a wall thereof. 20. The device as recited in claim 19, wherein said at least one recess (32) in the second cover means (30) and the second inlet (33) to the combustion chamber, when in registration with one another, are configured to form a through-duct for gas passing from outside the combustion chamber to inside the combustion chamber. 21. The device as recited in claim 19, wherein the second cover means (30) is in the shape of a ring with said at least one recess (32) extending through a wall thereof. 22. The device as recited in claim 18, wherein the second cover means (30) is rotatable relative to the combustion chamber (1). 23. The device as recited in claim 22, wherein the second cover means (30) is connected to the first cover means (13) by at least one arm (31, 34. 35). 24. A device for controlling the intake of gas into a combustion zone (10, 11) of the combustion chamber (1 ) of a gas turbine, said device comprising: a control element (12, 12') arranged outside the combustion chamber (1); said control element (12, 12') further comprising a first cover means (13) for covering at least a first inlet to the combustion zone, said first cover means being displaceable relative to the combustion chamber (1); and a support means (16) connected to the first cover means (13) for providing support to the control element (12, 12'), said support means (16) being accommodated interiorly within a structure (4) rearwardly located with respect to the combustion chamber (1) and said support means (16) being substantially concentrically oriented relative to a centerline of the combustion chamber (1) and wherein the structure (4) within which the support means (16) is accommodated is thermally insulated from the combustion chamber (1). 25. A device for controlling the intake of gas into a combustion zone (10, 11) of the combustion chamber (1 ) of a gas turbine, said device comprising: a control element (12, 12') arranged outside the combustion chamber (1); said control element (12, 12') further comprising a first cover means (13) for covering at least a first inlet to the combustion zone, said first cover means being displaceable relative to the combustion chamber (1); and a support means (16) connected to the first cover means (13) for providing support to the control element (12, 12'), said support means (16) being accommodated interiorly within a structure (4) rearwardly located with respect to the combustion chamber (1) and said support means (16) being substantially concentrically oriented relative to a centerline of the combustion chamber (1) and wherein the support means (16 ), when accommodated in the structure (4), is radially oriented outside a pilot distributor (2) to the combustion chamber, extends around the pilot distributor (2), and is supported against the structure (4) at an outer surface (20) of the support means (16). 26. A device for controlling the intake of gas into a combustion zone (10, 11) of the combustion chamber (1 ) of a gas turbine, said device comprising: a control element (12, 12') arranged outside the combustion chamber (1); said control element (12, 12') further comprising a first cover means (13) for covering at least a first inlet to the combustion zone, said first cover means being displaceable relative to the combustion chamber (1) and comprising at least two sets of recesses, a first set of recesses being arranged at a distance from a second set of recesses with respect to a longitudinal direction of the combustion chamber; and a support means (16) connected to the first cover means (13) for providing support to the control element (12, 12'), said support means (16) being accommodated interiorly within a structure (4) rearwardly located with respect to the combustion chamber (1) and said support means (16) being substantially concentrically oriented relative to a centerline of the combustion chamber (1) and wherein the first cover means ( 13) has at least one recess (14, 15) extending through a wall (13) thereof in a substantially radial direction of the control element (12, 12'), such that when in registration with the first inlet to the combustion chamber, are configured to form a through-duct for gas passing from outside the combustion chamber to inside the combustion chamber. 27. A device for controlling the intake of gas into a combustion zone (10, 11) of the combustion chamber (1 ) of a gas turbine having a combustion chamber cover (4), said device comprising: a control element (12, 12') arranged outside the combustion chamber (1); said control element (12, 12') further comprising a first cover means (13) for covering at least a first inlet to the combustion zone, said first cover means being displaceable relative to the combustion chamber (1); and a support means (16) connected to the first cover means (13) for providing support to the control element (12, 12'), said support means (16) being accommodated interiorly within a structure (4) rearwardly located with respect to the combustion chamber (1) and said support means (16) being substantially concentrically oriented relative to a centerline of the combustion chamber (1), wherein the first cover means ( 13) has at least one recess (14, 15) extending through a wall (13) thereof in a substantially radial direction of the control element (12, 12') and wherein the control element (12, 12') comprises an annular cover section (18) configured to cover at least one inlet to the combustion zone of the combustion chamber (1) different from the first inlet, the cover section (18) being arranged at a lesser distance from a centerline of the control element (12, 12') than the first cover means (13), and the annular cover section (18) having at least one recess (19) therein.