Combustor and gas turbine
A combustor of the present disclosure includes a combustor plate configured to have a downstream end face perpendicular to a combustor axis; a nozzle segment configured such that a plurality of first nozzles that inject a premixed gas of air and fuel from a side of the downstream end face are collectively disposed; and a plurality of second nozzles configured to inject the fuel from the downstream end face. A plurality of the nozzles segments are provided at intervals in a direction perpendicular to the combustor axis. Each of the second nozzles injects the fuel from a dividing region between the nozzle segments on the downstream end face.
1. A combustor comprising:
a combustor plate configured to have a downstream end face intersected to a combustor axis;
a nozzle segment configured such that a plurality of first nozzles inject a premixed gas of air and fuel from a side of the downstream end face to generate a premixed flame are collectively disposed; and
a plurality of second nozzles configured to inject the fuel from the downstream end face to generate a diffusion flame,
wherein a plurality of the nozzle segments are provided at intervals in a direction perpendicular to the combustor axis, and
an end portion of each of the second nozzles on the downstream end face side is formed between the plurality of nozzle segments and is located in a dividing region on the downstream end face interposed between the nozzle segments adjacent to each other such that the nozzle segments are disposed with an interval therebetween.
2. The combustor according to claim 1 , further comprising:
as the nozzle segment,
a central segment configured to be disposed in a central portion of the combustor plate including the combustor axis; and
a plurality of outer-peripheral-side segments configured to be disposed at intervals on a radially outer side of the combustor axis in the central segment and at intervals in a circumferential direction of the combustor axis,
wherein the dividing region includes
an annular region that is a region between the central segment and the plurality of outer-peripheral-side segments and extends in an annular shape surrounding the combustor axis, and
a radial region that is a region between the outer-peripheral-side segments adjacent to each other and extends in a radial direction of the combustor axis.
3. The combustor according to claim 2 ,
wherein the second nozzles inject the fuel from a connection point between the annular region and the radial region in the dividing region.
4. The combustor according to claim 2 ,
wherein a plurality of the second nozzles are disposed along an extension direction of at least one of the annular region and the radial region of the dividing region.
5. The combustor according to claim 2 , further comprising:
a third nozzle configured to inject the fuel from an outer-peripheral-side region on the radially outer side of the outer-peripheral-side segment on the downstream end face.
6. The combustor according to claim 2 , further comprising:
a fourth nozzle configured to inject the fuel from a region in the nozzle segment on the downstream end face.
7. The combustor according to claim 1 ,
wherein, among the plurality of first nozzles of the nozzle segment, fuel concentration of the first nozzles disposed adjacent to the dividing region is higher than fuel concentration of the other first nozzles.
8. The combustor according to claim 1 ,
wherein, among the plurality of first nozzles of the nozzle segment, the fuel of the first nozzles disposed adjacent to the dividing region is a type of fuel that is more easily combusted than the fuel of the other first nozzles.
9. The combustor according to claim 1 ,
wherein the combustor plate is configured of a plurality of divided bodies divided as viewed from a direction of the combustor axis,
the nozzle segment is provided in each of the divided bodies, and
the dividing region is a region including a dividing line between the divided bodies.
10. A gas turbine comprising:
a compressor configured to generate air;
the combustor according to claim 2 , configured to generate a combustion gas by combusting a premixed gas generated by mixing fuel with the air compressed by the compressor; and
a turbine configured to be driven by the combustion gas.
11. A combustor comprising:
a combustor plate configured to have a downstream end face intersected to a combustor axis;
a nozzle segment configured such that a plurality of first nozzles that inject a premixed gas of air and fuel from a side of the downstream end face are collectively disposed; and
a plurality of second nozzles configured to inject the fuel from the downstream end face,
wherein a plurality of the nozzle segments are provided at intervals in a direction perpendicular to the combustor axis,
the combustor plate is configured of a plurality of divided bodies divided as viewed from a direction of the combustor axis, the nozzle segment is provided in each of the divided bodies, and each of the second nozzles injects the fuel from a dividing region between the nozzle segments on the downstream end face, and
the dividing region is a region including a dividing line between the divided bodies.