Combustor and gas turbine including the same

Patent metadata

Field	Value
Publication number	US-11060728-B2
Application number	US-201816180000-A
Country	US
Kind code	B2
Filing date	Nov 4, 2018
Priority date	Nov 9, 2017
Publication date	Jul 13, 2021
Grant date	Jul 13, 2021

Abstract

A combustor includes a plurality of fuel nozzles arranged in a nozzle casing. Each fuel nozzle includes a first fuel injection passage disposed at the axial center of the fuel nozzle and configured to inject liquid fuel into a combustion chamber. A second fuel injection passage encloses the first fuel injection passage and injects liquid fuel into the combustion chamber at a predetermined spray angle with respect to a center line of the fuel nozzle. A first air injection passage encloses the second fuel injection passage and injects air to be mixed with the injected liquid fuel from the second fuel injection passage. At the combustion chamber end, opposing surfaces of the first and second fuel injection passages are each inclined with respect to the center line and are separated by a space through which the liquid fuel of the second fuel injection passage is injected.

First claim

What is claimed is:

1. A combustor comprising a nozzle casing and a plurality of first fuel nozzles disposed in the nozzle casing and spaced apart from each other along an annular imaginary line, each first fuel nozzle having an axial center at which a first center line is drawn and comprising:
a first fuel injection passage disposed at the axial center of the first fuel nozzle and configured to inject liquid fuel into a combustion chamber;
a second fuel injection passage enclosing the first fuel injection passage, and configured to inject liquid fuel into the combustion chamber at a first predetermined spray angle with respect to the first center line;
a first air injection passage enclosing the second fuel injection passage, and configured to inject air to be mixed with the injected liquid fuel from the second fuel injection passage, the first air injection passage receiving the air from a first air supply passage surrounding the first air injection passage via at least one through-hole formed along the first air injection passage; and
a first water supply passage communicating with the first air injection passage and configured to inject water into the first air injection passage at a location upstream of the at least one through-hole, the water and the air being mixed with each other in the first air injection passage and injected from the first air injection passage,
wherein the second fuel injection passage is enclosed by the first water supply passage and the first air injection passage, and
wherein the first water supply passage is disposed around the second fuel injection passage in a direction parallel to the first air injection passage, and supplies water to a combustion chamber of the combustor through the first air injection passage to mix the liquid fuel and water in the combustion chamber.

2. The combustor according to claim 1 ,
wherein the first fuel injection passage includes a first end disposed adjacent to the combustion chamber, the first end having an outer circumferential surface inclined at a first predetermined angle with respect to the first center line, and
wherein the second fuel injection passage includes a second end disposed adjacent to the combustion chamber, the second end having an inner circumferential surface inclined at the first predetermined angle with respect to the first center line.

3. The combustor according to claim 2 , wherein the outer circumferential surface of the first end and the inner circumferential surface of the second end are opposing surfaces separated by a space through which the liquid fuel of the second fuel injection passage is injected into the combustion chamber.

4. The combustor according to claim 2 , wherein the outer circumferential surface of the first end has a truncated conical shape.

5. The combustor according to claim 4 , wherein the inner circumferential surface of the second end has a shape corresponding to the outer circumferential surface of the first end.

6. The combustor according to claim 5 , wherein the inner circumferential surface of the second end has a truncated conical shape.

7. The combustor according to claim 1 , wherein the liquid fuel is injected into the combustion chamber from either one of the first fuel injection passage and the second fuel injection passage.

8. The combustor according to claim 1 , wherein each first fuel nozzle further comprises a plurality of first swirlers disposed at positions spaced apart from each other along a circumference of the first air injection passage.

9. The combustor according to claim 1 , further comprising a plurality of second fuel nozzles disposed along the annular imaginary line, each second fuel nozzle being disposed between a pair of adjacent first fuel nozzles of the plurality of first fuel nozzles and having an axial center at which a second center line is drawn.

10. The combustor according to claim 9 , wherein each of the plurality of second fuel nozzles comprises:
a central shaft disposed at the axial center of the second fuel nozzle;
a third fuel injection passage enclosing the central shaft, and configured to inject liquid fuel into the combustion chamber at a second predetermined spray angle with respect to the second center line; and
a second air injection passage enclosing the third fuel injection passage, and configured to inject air to be mixed with the injected liquid fuel from the third fuel injection passage.

11. The combustor according to claim 10 ,
wherein the central shaft includes a third end disposed adjacent to the combustion chamber, the third end having an outer circumferential surface inclined at a second predetermined angle with respect to the second center line, and
wherein the third fuel injection passage includes a fourth end disposed adjacent to the combustion chamber, the fourth end having an inner circumferential surface inclined at the predetermined angle with respect to the second center line.

12. The combustor according to claim 11 , wherein the outer circumferential surface of the third end and the inner circumferential surface of the fourth end are opposing surfaces separated by a space through which the liquid fuel of the third fuel injection passage is injected into the combustion chamber.

13. The combustor according to claim 12 , wherein the inner circumferential surface of the fourth end has a shape corresponding to the outer circumferential surface of the third end.

14. The combustor according to claim 13 , wherein each of the outer circumferential surface of the third end and the inner circumferential surf ace of the fourth end has a truncated conical shape.

15. The combustor according to claim 10 , further comprising a second water supply passage communicating with the second air injection passage and configured to supply water to the second air injection passage, the water and the air being mixed with each other in the second air injection passage and injected from the second air injection passage.

16. The combustor according to claim 10 , wherein each second fuel nozzle further comprises a plurality of second swirlers disposed at positions spaced apart from each other along a circumference of the second air injection passage.

17. A gas turbine comprising a compressor to compress air drawn from outside of the gas turbine, a combustor to produce combustion gas by mixing fuel with the compressed air and combusting a mixture of the fuel and the compressed air, and a turbine configured to be rotated by the combustion gas, the combustor comprising:
a nozzle casing; and
a plurality of first fuel nozzles disposed in the nozzle casing and spaced apart from each other along an annular imaginary line, each first fuel nozzle having an axial center at which a first center line is drawn and comprising:
a first fuel injection passage disposed at the axial center of the first fuel nozzle and configured to inject liquid fuel into a combustion chamber;
a second fuel injection passage enclosing the first fuel injection passage, and configured to inject liquid fuel into the combustion chamber at a predetermined spray angle with respect to the first center line;
a first air injection passage enclosing the second fuel injection passage, and configured to inject air to be mixed with the injected liquid fuel from the second fuel injection passage, the first air injection passage receiving the air from a first air supply passage surrounding the first air injection passage via at least one through-hole formed along the first air injection passage; and
a first water supply passage communicating with the first air injectio

Assignees

• Doosan Heavy Ind & Construction Co Ltd

Inventors

• Seok Jungmin

Classifications

• F23D11/383

  with swirl means · CPC title

• F23D11/10

  the spraying being induced by a gaseous medium, e.g. water vapour · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23R3/16

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title