Combustor and gas turbine including the same

Patent metadata

Field	Value
Publication number	US-11149951-B2
Application number	US-201816134653-A
Country	US
Kind code	B2
Filing date	Sep 18, 2018
Priority date	Oct 11, 2017
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

In a combustor including a plurality of combustion nozzles, and a gas turbine including the same, fuel can be uniformly mixed with compressed air for each combustion nozzle. The combustor includes a plurality of combustion nozzles arranged in a nozzle casing, and each combustion nozzle includes a nozzle shroud for taking in compressed air; an injection cylinder concentrically disposed in the nozzle shroud and configured to be supplied with fuel for mixing with the compressed air; and a plurality of swirlers circumferentially arranged around the injection cylinder and configured to inject the fuel from the injection cylinder into the shroud. The plurality of swirlers divide an interior space of the nozzle shroud into a plurality of fluid flow regions, and include a pair of adjacent swirlers spaced apart from each other by a circumferential distance that differs from a circumferential distance between another pair of adjacent swirlers.

First claim

What is claimed is:

1. A combustor including a plurality of combustion nozzles arranged in a nozzle casing, each combustion nozzle comprising:
a nozzle shroud for taking in compressed air;
an injection cylinder concentrically disposed in the nozzle shroud and configured to be supplied with fuel for mixing with the compressed air; and
a plurality of swirlers circumferentially arranged around the injection cylinder and configured to divide an interior mace of the nozzle shroud into a plurality of fluid flow regions such that each swirler of the plurality of swirlers is disposed between two adjacent fluid flow regions of the plurality of fluid flow regions, said each swirler having a plurality of fuel injection holes for injecting an amount of the fuel from the injection cylinder into each of the two adjacent fluid flow regions,
wherein the plurality of fluid flow regions include a first fluid flow region and a remainder of the plurality of fluid flow regions that excludes the first fluid flow region, the remainder of the plurality of fluid flow regions including a second fluid flow region, the first fluid flow region being smaller than the second fluid flow region,
wherein each of the plurality of fluid flow regions is configured to receive an amount of the compressed air, the amount of the compressed air in the first flow region being lean compared to the amount of the compressed air in the second flow region,
wherein the plurality of swirlers include
a first swirler having a first circumferential side in which first fuel injection holes of the plurality of fuel injection holes are formed and a second circumferential side in which second fuel injection holes of the plurality of fuel injection holes are formed, the first circumferential side of the first swirler facing the first fluid flow region and the second circumferential side of the first swirler facing the second fluid flow region, and
a second swirler having a third circumferential side in which third fuel injection holes of the plurality of fuel injection holes are formed, the third circumferential side of the second swirler facing the second fluid flow region,
wherein the plurality of swirlers are configured to inject less of the fuel into the first fluid flow region in which the amount of the compressed air is lean than into the second fluid flow region, by forming the first fuel injection holes in the first circumferential side of the first swirler to include at least one of
the first fuel injection holes that are smaller in size than the second fuel injection holes formed in the second circumferential side of the first swirler, the first fuel injection holes being smaller in size than the third fuel injection holes formed in the third circumferential side of the second swirler, and
the first fuel injection holes that are fewer in number than the second fuel injection holes formed in the second circumferential side of the first swirler, the first fuel, injection holes being fewer in number than the third fuel injection holes formed in the third circumferential side of the second swirler,
wherein a number of the first fuel injection holes in the first circumferential side of the first swirler and a number of the second fuel injection holes in the second circumferential side of the first swirler is different, and a number of the second fuel injection holes in the second circumferential side of the first swirler and a number of the third fuel injection holes in the third circumferential side of the second swirler is same, and
wherein a size of the first fuel injection holes in the first circumferential side of the first swirler and a size of the second fuel injection holes in the second circumferential side of the first swirler is different, and a size of the second fuel injection holes in the second circumferential side of the first swirler and a size of the third fuel injection holes in the third circumferential side of the second swirler is same.

2. The combustor according to claim 1 ,
wherein the number of the third fuel injection holes formed in the third circumferential side of the second swirler facing the second fluid flow region is same as a number of fuel injection holes formed in opposite side of the third circumferential side of the second swirler, and
wherein the size of the third fuel injection holes formed in the third circumferential side of the second swirler facing the second fluid flow region is same as a size of fuel injection holes formed in opposite side of the third circumferential side of the second swirler.

3. The combustor according to claim 1 ,
wherein the plurality of swirlers further include a third swirler having fifth and sixth circumferential sides each facing the first fluid flow region, and
wherein the number and the size of the fuel injection holes of the fifth circumferential side of the third swirler equal the number and the size of the fuel injection holes of the sixth circumferential side of the third swirler.

4. The combustor according to claim 1 ,
wherein the plurality of combustion nozzles comprise:
a central nozzle centrally disposed in the nozzle casing; and
a plurality of outer nozzles arranged along an imaginary annular line surrounding the central nozzle,

wherein the first fluid flow region in each of the plurality of outer nozzles is adjacent to the central nozzle, and
wherein the remainder of the plurality of fluid flow regions in each of the plurality of outer nozzles are adjacent to an inner peripheral surface of the nozzle casing.

5. The combustor according to claim 1 ,
wherein the plurality of swirlers include a pair of adjacent swirlers spaced apart from each other by a circumferential distance that differs from a circumferential distance between another pair of adjacent swirlers of the plurality of swirlers, and
wherein the pair of adjacent swirlers includes the first swirler and the second swirler.

6. A gas turbine comprising a compressor to compress air, a combustor to mix the compressed air with fuel to produce combustion gas by combusting the mixture, and a turbine having a rotor configured to be rotated by the combustion gas, the combustor including a plurality of combustion nozzles arranged in a nozzle casing, each combustion nozzle comprising:
a nozzle shroud for taking in the compressed air;
an injection cylinder concentrically disposed in the nozzle shroud and configured to be supplied with the fuel for mixing with the compressed air; and
a plurality of swirlers circumferentially arranged around the injection cylinder and configured to divide an interior space of the nozzle shroud into a plurality of fluid flow regions such that each swirler of the plurality of swirlers is disposed between two adjacent fluid flow regions of the plurality of fluid flow regions, said each swirler having a plurality of fuel injection holes for injecting an amount of the fuel from the injection cylinder into each of the two adjacent fluid flow regions,
wherein the plurality of fluid flow regions include a first fluid flow region and a remainder of the plurality of fluid flow regions that excludes the first fluid flow region, the remainder of the plurality of fluid flow regions including a second fluid flow region, the first fluid flow region being smaller than the second fluid flow region,
wherein each of the plurality of fluid flow regions is configured to receive an amount of the compressed air, the amount of the compressed air in the first flow region being lean compared to the amount of the compressed air in the second flow region,
wherein the plurality of swirlers include
a first swirler having a first circumferential side in which first fuel injection holes of the plurality of fuel injection holes are formed and a second circumferential side in which second fuel

Assignees

• Doosan Heavy Ind & Construction Co Ltd

Inventors

• Seo Jaewon

Classifications

• F23D14/24

  at least one of the fluids being submitted to a swirling motion · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23C2900/07001

  Air swirling vanes incorporating fuel injectors · CPC title

• F23C7/004

  using vanes · CPC title