Segmented annular combustion system

1. An annular combustion system, comprising:

a fuel nozzle;

a panel fuel injector disposed adjacent to and extending downstream from the fuel nozzle, wherein the panel fuel injector includes a fuel plenum and at least one premixing channel therein;

an inner liner comprising an inner band radially spaced from an outer band and an inner flow annulus formed therebetween; and

an outer liner radially spaced from the inner liner and comprising an inner band radially spaced from an outer band and an outer flow annulus formed therebetween, wherein the fuel nozzle is positioned radially between the inner liner and the outer liner, and the panel fuel injector fully extends radially between the inner liner and the outer liner; wherein at least one of the inner flow annulus and the outer flow annulus is in fluid communication with at least one of a premix air plenum, a cooling air cavity, and a cooling air plenum defined within the panel fuel injector, wherein an aft wall of the panel fuel injector defines a plurality of cooling holes, and wherein one or more of the cooling holes of the plurality of cooling holes is oriented towards at least one of a leading edge, a pressure side wall, or a suction side wall of a stationary nozzle disposed proximate to the aft end wall.

2. The annular combustion system as in claim 1 , wherein the outer band of the inner liner defines a plurality of apertures, the plurality of apertures being oriented to direct jets of cooling air against a cool side surface of the inner band of the inner liner.

3. The annular combustion system as in claim 1 , wherein the outer band of the outer liner defines a plurality of apertures, the plurality of apertures being oriented to direct jets of cooling air against a cool side surface of the inner band of the outer liner.

4. The annular combustion system as in claim 1 , wherein one or more of the cooling holes of the plurality of cooling holes is in fluid communication with the inner flow annulus.

5. The annular combustion system as in claim 1 , wherein one or more of the cooling holes of the plurality of cooling holes is in fluid communication with the outer flow annulus.

6. The annular combustion system as in claim 1 , wherein the inner band of the inner liner defines a primary aperture, the primary aperture providing for fluid communication between the inner flow annulus and at least one of the premix air plenum, the cooling air cavity, and the cooling air plenum of the panel fuel injector.

7. The annular combustion system as in claim 1 , wherein the inner band of the outer liner defines a primary aperture, the primary aperture providing for fluid communication between the outer flow annulus and at least one of the premix air plenum, the cooling air cavity, and the cooling air plenum of the panel fuel injector.

8. The annular combustion system as in claim 1 , wherein the inner band of the inner liner defines a plurality of secondary apertures, and wherein the plurality of secondary apertures provides for fluid communication from the inner flow annulus through the inner band and across a hot side surface of the inner band.

9. The annular combustion system as in claim 1 , wherein the inner band of the outer liner defines a plurality of secondary apertures, and wherein the plurality of secondary apertures provides for fluid communication from the outer flow annulus through the inner band and across a hot side surface of the outer band.

10. The annular combustion system as in claim 1 , wherein an inlet to the inner flow annulus is defined at a downstream end of the inner liner.

11. The annular combustion system as in claim 1 , wherein an inlet to the outer flow annulus is defined at a downstream end of the outer liner.

12. A gas turbine, comprising:

a compressor;

a compressor discharge casing defining a high pressure plenum therein, wherein the high pressure plenum is in fluid communication with the compressor;

a combustion system, comprising:

a plurality of panel fuel injectors arranged in an annular array about an axial centerline of the combustion system, wherein each adjacent pair of panel fuel injectors is circumferentially separated by a fuel nozzle of a plurality of fuel nozzles, wherein the plurality of panel fuel injectors and the plurality of fuel nozzles are disposed between an inner liner and an outer liner and each panel fuel injector of the plurality of panel fuel injectors fully extends radially from the inner liner to the outer liner;

wherein the inner liner includes an inner band radially spaced from an outer band, defining an inner flow annulus therebetween;

wherein the outer liner includes an inner band radially spaced from an outer band, defining an outer flow annulus therebetween; and

wherein at least one of the inner flow annulus and the outer flow annulus is in fluid communication with at least one of a premix air plenum, a cooling air cavity, and a cooling air plenum defined within a respective panel fuel injector of the plurality of panel fuel injectors, wherein an aft wall of the respective panel fuel injector of the plurality of panel fuel injectors defines a plurality of cooling holes, and wherein one or more of the cooling holes of the plurality of cooling holes is oriented towards at least one of a leading edge, a pressure side wall, or a suction side wall of a stationary nozzle disposed proximate to the aft end wall.

13. The gas turbine as in claim 12 , wherein the outer band of the inner liner defines a plurality of apertures, the plurality of apertures being oriented to direct jets of cooling air against a cool side surface of the inner band of the inner liner.

14. The gas turbine as in claim 12 , wherein the outer band of the outer liner defines a plurality of apertures, the plurality of apertures being oriented to direct jets of cooling air against a cool side surface of the inner band of the outer liner.

15. The annular combustion system as in claim 12 , wherein one or more of the cooling holes of the plurality of cooling holes is in fluid communication with the inner flow annulus.

16. The annular combustion system as in claim 12 , wherein one or more of the cooling holes of the plurality of cooling holes is in fluid communication with the outer flow annulus.

17. The gas turbine as in claim 12 , wherein the inner band of the inner liner defines a primary aperture, the primary aperture providing for fluid communication between the inner flow annulus and at least one of the premix air plenum, the cooling air cavity, and the cooling air plenum of the respective panel fuel injector of the plurality of panel fuel injectors.

18. The gas turbine as in claim 12 , wherein the inner band of the outer liner defines a primary aperture, the primary aperture providing for fluid communication between the outer flow annulus and at least one of the premix air plenum, the cooling air cavity, and the cooling air plenum of the respective panel fuel injector of the plurality of panel fuel injectors.

19. The gas turbine as in claim 12 , wherein the inner band of the inner liner defines a plurality of secondary apertures, and wherein the plurality of secondary apertures provides for fluid communication from the inner flow annulus through the inner band and across a hot side surface of the inner band.

20. The gas turbine as in claim 12 , wherein the inner band of the outer liner defines a plurality of secondary apertures, and wherein the plurality of secondary apertures provides for fluid communication from the outer flow annulus through the inner band and across a hot side surface of the outer band.