Nozzle for combustors, combustor, and gas turbine including the same

Patent metadata

Field	Value
Publication number	US-2019257522-A1
Application number	US-201816224870-A
Country	US
Kind code	A1
Filing date	Dec 19, 2018
Priority date	Feb 20, 2018
Publication date	Aug 22, 2019
Grant date	—

Abstract

A nozzle, a combustor, and a gas turbine are capable of efficiently atomizing fuel. The nozzle includes an outer tube; a first inner tube installed in the outer tube and configured to form an air passage between the first inner tube and the outer tube; a second inner tube installed in the first inner tube and configured to form a main fuel passage between the first inner tube and the second inner tube and to form a pilot fuel passage within the second inner tube; and a splash plate configured to form a first space between the outer tube and the splash plate, the first space communicating with the main fuel passage and with the air passage, and to form an injection slot communicating with the first space, the splash plate having a front end and a diameter increasing toward the front end.

First claim

What is claimed is:

1 . A nozzle for a combustor, comprising:
an outer tube; a first inner tube installed in the outer tube and configured to form an air passage between the first inner tube and the outer tube; a second inner tube installed in the first inner tube and configured to form a main fuel passage between the first inner tube and the second inner tube and to form a pilot fuel passage within the second inner tube; and a splash plate configured to form a first space between the outer tube and the splash plate, the first space communicating with the main fuel passage and with the air passage, and to form an injection slot communicating with the first space, the splash plate having a front end and a diameter increasing toward the front end.

2 . The nozzle according to claim 1 , wherein the injection slot is formed between an outer circumferential surface of the outer tube and the front end of the splash plate.

3 . The nozzle according to claim 1 , further comprising a plurality of struts installed in the first space so as to couple the splash plate with the outer tube and arranged at positions spaced apart from each other in a circumferential direction of the first space.

4 . The nozzle according to claim 3 , wherein the first space includes a divided region divided into spaces by the struts, and a connected region communicating with the spaces of the divided region and extending in a circumferential direction of the splash plate.

5 . The nozzle according to claim 1 , further comprising a first barrier between the first space and the air passage, in which a plurality of first connection holes are formed to connect the first space with the air passage.

6 . The nozzle according to claim 5 , further comprising a second barrier between the first space and the main fuel passage, in which a plurality of second connection holes are formed to connect the first space with the main fuel passage.

7 . The nozzle according to claim 1 , further comprising a curtain barrier in which a plurality of air curtain holes for communicating with the air passage are formed,
wherein the pilot fuel passage has a front end in which an injection hole is formed, and the curtain barrier is disposed in front of the injection hole to enclose a space in front of the injection hole.

8 . The nozzle according to claim 7 , wherein the air curtain holes communicate with the air passage through a plurality of connection passages in communication with a cooling guide flow passage extending in a circumferential direction of the second inner tube.

9 . The nozzle according to claim 7 , wherein the nozzle has a front end formed by an inclined part formed by the splash plate; a planar part having a planar surface communicating with a rear end of the inclined part; and a recessed part formed in the planar part, the recessed part having a side surface formed by the curtain barrier and a bottom surface in which the injection hole is formed.

10 . The nozzle according to claim 1 , further comprising a flow guide member installed in the pilot fuel passage, the flow guide member including a head having an outer circumferential surface in which a guide groove extending in a spiral shape is formed.

11 . The nozzle according to claim 10 , wherein the flow guide member further includes a guide tube coupled with the head, and wherein the guide tube comprises:
a diverging passage communicating with an inlet passage formed in a rear end of the guide tube; and a plurality of outlet passages each communicating with a front end of the diverging passage and with an outer circumferential surface of the guide tube.

12 . The nozzle according to claim 11 , wherein the outer circumferential surface of the guide tube has an inclined cross section such that an outer diameter of the guide tube is gradually reduced toward a front end of the guide tube, and wherein the outlet passages occur in the guide tube where the outer circumferential surface of the guide tube is inclined.

13 . The nozzle according to claim 10 , wherein the flow guide member further includes a guide protrusion having a conical shape protrudes rearward from the head.

14 . The nozzle according to claim 13 , wherein the guide protrusion includes an outer circumferential surface in which a plurality of channels extending outward from a center of the guide protrusion and extending in a longitudinal direction of the guide protrusion are formed.

15 . A combustor comprising a burner having a plurality of nozzles configured to eject fuel and air, and a duct assembly coupled to one side of the burner and configured to combust the ejected fuel and air and transfer combustion gas to a turbine, each nozzle comprising:
an outer tube; a first inner tube installed in the outer tube and configured to form an air passage between the first inner tube and the outer tube; a second inner tube installed in the first inner tube and configured to form a main fuel passage between the first inner tube and the second inner tube and to form a pilot fuel passage within the second inner tube; and a splash plate configured to
form a first space between the outer tube and the splash plate, the first space communicating with the main fuel passage and with the air passage,
form an injection slot communicating with the first space, and
diffuse fuel transferred from the main fuel passage.

16 . The combustor according to claim 15 , wherein the injection slot is formed between an outer circumferential surface of the outer tube and a front end of the splash plate.

17 . The combustor according to claim 15 , wherein each nozzle further comprises a plurality of struts installed in the first space so as to couple the splash plate with the outer tube and arranged at positions spaced apart from each other in a circumferential direction of the first space.

18 . A gas turbine comprising a compressor configured to compress air drawn from an outside, a combustor configured to produce combustion gas by mixing fuel with the compressed air and combust the mixture, and a turbine including a plurality of turbine blades configured to be rotated by the combustion gas,
wherein the combustor comprises a burner having a plurality of nozzles configured to eject fuel and air, and a duct assembly coupled to one side of the burner and configured to combust the ejected fuel and air and transfer the combustion gas to the turbine, each nozzle comprising:
an outer tube;
a first inner tube installed in the outer tube and configured to form an air passage between the first inner tube and the outer tube;
a second inner tube installed in the first inner tube and configured to form a main fuel passage between the first inner tube and the second inner tube and to form a pilot fuel passage within the second inner tube; and
a splash plate configured to form a first space between the outer tube and the splash plate, the first space communicating with the main fuel passage and with the air passage, and to form an injection slot communicating with the first space; and
a curtain barrier in which a plurality of air curtain holes for communicating with the air passage are formed,
wherein the pilot fuel passage has a front end in which an injection hole is formed, and the curtain barrier is disposed in front of the injection hole to enclose a space in front of the injection hole.

19 . The gas turbine according to claim 18 , wherein the splash plate having a front end and a diameter increasing toward the front end.

20 . The gas turbine

Assignees

• Doosan Heavy Ind & Construction Co Ltd

Inventors

• Myatlev Alexander
• Seok Jungmin
• Shershnyov Borys

Classifications

• F23R3/343 Primary

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title