Combustor cooling structure

1. A combustor of a gas turbine, comprising:

a combustor air plenum;

a transition piece including an impingement cooling zone having an impingement plate including a plurality of impingement cooling holes and attached to a sidewall of the transition piece in the impingement cooling zone wherein the impingement cooling holes open to the combustor air plenum;

a chamber between the impingement plate and the sidewall;

a sequential disposed liner having at least one cooling arrangement; and

a closing plate including an annular space arranged at a single axial location of the combustor, wherein the sequential disposed liner has cooling channels, wherein the cooling channels are operatively connected to a cooling medium to cool at least one part of the sequential disposed liner, wherein the cooling channels extend through a thickness of the sequential disposed liner of the transition piece, and into the annular space on a side of the closing plate, wherein the cooling channels run in a serpentine manner, are connected to the annular space and are configured to redistribute the cooling medium among one another, wherein the cooling channels are arranged in a wall of the sequential disposed liner in at least one circumferentially disposed section and wherein the cooling channels are connected to redistribute the cooling medium among one another by being connected to the annular space formed in the closing plate, the cooling channels including cooling medium inlet openings arranged upstream of the annular space with respect to a hot combustion gas flow.

2. The combustor according to claim 1 , wherein the cooling channels are configured to cool at least one part of the closing plate.

3. The combustor according to claim 1 , wherein the cooling medium travels to the impingement cooling holes in the impingement plate after completion of a cooling operation along the cooling channels.

4. The combustor according to claim 1 , wherein the annular space has a recess in a circumferential direction of the sequential disposed liner.

5. The combustor according to claim 1 , wherein the annular space comprises at least one cavity for collecting dust particles.

6. The combustor according to claim 5 , wherein the at least one cavity is operatively connected to an aperture for discharging the collected dust particles from the at least one cavity.

7. The combustor according to claim 1 , wherein the at least one cooling arrangement operates on the basis of a convective cooling.

8. The combustor according to claim 1 , wherein the at least one cooling arrangement operates on the basis of a convective and an effusion cooling.

9. The combustor according to claim 1 , wherein the at least one cooling arrangement within the impingement cooling zone operates on the basis of an impingement, an effusion and/or a convective cooling.

10. A gas turbine arrangement, comprising:

the combustor as claimed in claim 1 ;

a compressor;

wherein the combustor is arranged downstream of the compressor wherein the transition piece is disposed within an intermediate zone of the combustor, and wherein hot gases of the combustor are admitted to a turbine, and the combustor has an annular or a can-combustor architecture.

11. A gas turbine arrangement, comprising:

the combustor as claimed in claim 1 , wherein the combustor is a first combustor;

a compressor; and

wherein the first combustor is arranged downstream of the compressor wherein the transition piece is disposed within an intermediate zone of the first combustor and wherein hot gases of the first combustor are admitted to a first turbine and a second combustor, hot gases of the second combustor are admitted to a second turbine or to a subsequent steam cycle; and at least one or both of the first combustor or the second combustor has an annular or a can-combustor architecture.

12. The gas turbine arrangement as claimed in claim 11 , wherein the first combustor has an annular combustion chamber comprising a plurality of premixing burners or semi-premixing burners, the first turbine connected to receive the hot gases from the first combustor, the second combustor is connected to receive the exhausted hot gases from the first turbine and to deliver the exhausted hot gases to the second turbine, wherein the second combustor comprises an annular duct forming a combustion space extending in a flow direction from an outlet of the first turbine to an inlet of the second turbine, and means for introducing a fuel into the second combustor for self-ignition combustion.

13. The gas turbine arrangement as claimed in claim 11 , wherein at least one of the first combustor and the second combustor are single can-combustors or separated can-combustors.