US-12624836-B2 - Combustor nozzle, combustor, and gas turbine including same

US12624836B2US 12624836 B2US12624836 B2US 12624836B2US-12624836-B2

Abstract

A combustor nozzle includes a plurality of mixing tubes through which air and fuel flow, an accommodation tube accommodating and supporting the plurality of mixing tubes therein, a first fuel tube coupled to the accommodation tube to supply a first fuel into the accommodation tube, a second fuel tube coupled to the accommodation tube to supply a second fuel into the accommodation tube, a first fuel supply member supplying the first fuel into each mixing tube, and a second fuel supply member supplying the second fuel into each mixing tube.

Inventors

Joong Hyun LIM
Young Gun GO
Kyoung Taek OH
Sang Pil JO

Assignees

DOOSAN ENERBILITY CO., LTD.

Dates

Publication Date: 20260512
Application Date: 20241012
Priority Date: 20231130

Claims (16)

1 . A combustor nozzle comprising: a plurality of mixing tubes, extending in an axial direction, through which air and fuel flow; an accommodation tube accommodating and supporting the plurality of mixing tubes therein; a first fuel tube coupled to the accommodation tube to supply a first fuel into the accommodation tube; a second fuel tube coupled to the accommodation tube to supply a second fuel into the accommodation tube; a plurality of first fuel supply members supplying the first fuel into the plurality of mixing tubes; and a plurality of second fuel supply members supplying the second fuel into the plurality of mixing tubes, each second fuel supply member having a rear end configured to receive the second fuel supplied from the second fuel tube and a leading end coupled with a hole formed on a corresponding mixing tube from among the plurality of mixing tubes to discharge the second fuel into the corresponding mixing tube, wherein each of the plurality of second fuel supply members is provided with a guide portion for injecting the second fuel toward a wall portion of an inner circumferential wall of the corresponding mixing tube, the wall portion being axially aligned with and located directly downstream of the hole formed on the corresponding mixing tube, and the guide portion is curved in an arc or inclined toward the wall portion of the inner circumferential wall such that an outlet of each second fuel supply member is open toward the wall portion of the inner circumferential wall, wherein a virtual plane forming the outlet of each second fuel supply member is formed to be inclined at a first inclination angle with respect to the inner circumferential wall of the corresponding mixing tube located downstream of the outlet, and the first inclination angle ranges from 30 degrees to 80 degrees so as to inject the second fuel toward the wall portion of the inner circumferential wall of the corresponding mixing tube.
2 . The combustor nozzle according to claim 1 , further comprising: a tip plate coupled to a leading end of each accommodation tube; a middle plate spaced apart from the tip plate to define a first distribution space between the tip plate and the middle plate in which the first fuel is accommodated; and a rear plate spaced apart from the middle plate to define a second distribution space between the rear plate and the middle plate in which the second fuel is accommodated.
3 . The combustor nozzle according to claim 2 , wherein each first fuel supply member is connected to the first distribution space, and each second fuel supply member is connected to the second distribution space.
4 . The combustor nozzle according to claim 3 , wherein an outlet of each first fuel supply member is disposed closer to the center of the mixing tube than the outlet of each second fuel supply member.
5 . The combustor nozzle according to claim 3 , wherein the outlet of each second fuel supply member is located further downstream of the outlet of each first fuel supply member.
6 . The combustor nozzle according to claim 3 , wherein each second fuel supply member extends from the second distribution space into the first distribution space and then into the corresponding mixing tube.
7 . The combustor nozzle according to claim 3 , wherein each second fuel supply member forms a concentrated fuel flow along the inner circumferential wall of the corresponding mixing tube.
8 . The combustor nozzle according to claim 3 , wherein the first fuel comprises a hydrogen-based fuel having hydrogen as a major component or a hydrocarbon-based fuel having hydrocarbon as a major component, and the second fuel comprises a hydrocarbon-based fuel having hydrocarbon as a major component.
9 . A combustor comprising: a burner having a plurality of nozzles through which fuel and air are injected; and a duct assembly coupled to one side of the burner to allow the fuel and the air to be combusted therein and combustion gases to be transferred to a turbine, wherein each nozzle of the plurality of nozzles comprises: a plurality of mixing tubes, extending in an axial direction, through which air and fuel flow; an accommodation tube accommodating and supporting the plurality of mixing tubes therein; a first fuel tube coupled to the accommodation tube to supply a first fuel into the accommodation tube; a second fuel tube coupled to the accommodation tube to supply a second fuel into the accommodation tube; a plurality of first fuel supply members supplying the first fuel into the plurality of mixing tubes; and a plurality of second fuel supply members supplying the second fuel into the plurality of mixing tubes, each second fuel supply member having a rear end configured to receive the second fuel supplied from the second fuel tube and a leading end coupled with a hole formed on a corresponding mixing tube from among the plurality of mixing tubes to discharge the second fuel into the corresponding mixing tube, wherein each second fuel supply member is provided with a guide portion for injecting the second fuel toward a wall portion of an inner circumferential wall of the corresponding mixing tube, the wall portion being axially aligned with and located directly downstream of the hole formed on the corresponding mixing tube, and the guide portion is curved in an arc or inclined toward the wall portion of the inner circumferential wall such that an outlet of each second fuel supply member is open toward the wall portion of the inner circumferential wall, wherein a virtual plane forming the outlet of each second fuel supply member is formed to be inclined at a first inclination angle with respect to the inner circumferential wall of the corresponding mixing tube located downstream of the outlet, and the first inclination angle ranges from 30 degrees to 80 degrees so as to inject the second fuel toward the wall portion of the inner circumferential wall of the corresponding mixing tube.
10 . The combustor according to claim 9 , further comprising: a tip plate coupled to a leading end of each accommodation tube; a middle plate spaced apart from the tip plate to define a first distribution space between the tip plate and the middle plate in which the first fuel is accommodated; and a rear plate spaced apart from the middle plate to define a second distribution space between the rear plate and the middle plate in which the second fuel is accommodated.
11 . The combustor according to claim 10 , wherein each first fuel supply member is connected to the first distribution space, and the second fuel supply member is connected to each second distribution space.
12 . The combustor according to claim 11 , wherein an outlet of each first fuel supply member is disposed closer to the center of the corresponding mixing tube than the outlet of the second fuel supply member, and the outlet of each second fuel supply member is located further downstream of the outlet of the first fuel supply member.
13 . The combustor according to claim 11 , wherein each second fuel supply member extends from the second distribution space into the first distribution space and then into the corresponding mixing tube.
14 . The combustor according to claim 11 , wherein each second fuel supply member forms a concentrated fuel flow along the inner circumferential wall of the corresponding mixing tube.
15 . The combustor according to claim 11 , wherein the first fuel comprises a hydrogen-based fuel having hydrogen as a major component or a hydrocarbon-based fuel having hydrocarbon as a major component, and the second fuel comprises a hydrocarbon-based fuel having hydrocarbon as a major component.
16 . A gas turbine comprising: a compressor compressing an externally introduced air; a combustor mixing the compressed air from the compressor with fuel to produce a mixture and combusting the mixture; and a turbine having a plurality of turbine blades rotated by the combustion gases from the combustor, wherein the combustor comprises: a burner having a plurality of nozzles through which fuel and air are injected; and a duct assembly coupled to one side of the burner to allow the fuel and the air to be combusted therein and combustion gases to be transferred to a turbine, wherein each nozzle of the plurality of nozzles includes: a plurality of mixing tubes, extending in an axial direction, through which air and fuel flow; an accommodation tube accommodating and supporting the plurality of mixing tubes therein; a first fuel tube coupled to accommodation tube to supply a first fuel into the accommodation tube; a second fuel tube coupled to accommodation tube to supply a second fuel into the accommodation tube; a plurality of first fuel supply members supplying the first fuel into the plurality of mixing tubes; and a plurality of second fuel supply members supplying the second fuel into the plurality of mixing tubes, each second fuel supply member having a rear end configured to receive the second fuel supplied from the second fuel tube and a leading end coupled with a hole formed on a corresponding mixing tube from among the plurality of mixing tubes to discharge the second fuel into the corresponding mixing tube, wherein each second fuel supply member is provided with a guide portion for injecting the second fuel toward a wall portion of an inner circumferential wall of the corresponding mixing tube, the wall portion being axially aligned with and located directly downstream of the hole formed on the corresponding mixing tube, and the guide portion is curved in an arc or inclined toward the wall portion of the inner circumferential wall such that an outlet of each second fuel supply member is open toward the wall portion of the inner circumferential wall, wherein a virtual plane forming the outlet of each second fuel supply member is formed to be inclined at a first inclination angle with respect to the inner circumferential wall of the corresponding mixing tube located downstream of the outlet, and the first inclination angle ranges from 30 degrees to 80 degrees so as to inject the second fuel toward the wall portion of the inner circumferential wall of the corresponding mixing tube.

Description

CROSS REFERENCE TO RELATED APPLICATION The present application claims priority to Korean Patent Application No. 10-2023-0171648, filed on Nov. 30, 2023, the entire contents of which are incorporated herein for all purposes by this reference. BACKGROUND 1. Technical Field The present disclosure relates to a combustor nozzle, a combustor, and a gas turbine and, more particularly, to a combustor nozzle using hydrogen-containing fuel, a combustor, and a gas turbine including the same. 2. Description of the Related Art A gas turbine is a combustion engine in which a mixture of air compressed by a compressor and fuel is combusted to produce a high temperature gas, which drives a turbine. The gas turbine is used to drive electric generators, aircraft, ships, trains, or the like. The gas turbine generally includes a compressor, a combustor, and a turbine. The compressor serves to intake external air, compress the air, and transfer the compressed air to the combustor. The compressed air compressed by the compressor has a high temperature and a high pressure. The combustor serves to mix compressed air from the compressor and fuel and combust the mixture of compressed air and fuel to produce combustion gases, which are discharged to the turbine. The combustion gases drive turbine blades in the turbine to produce power. The power generated through the above processes is applied to a variety of fields such as generation of electricity, driving of mechanical units, etc. Fuel is injected through nozzles disposed in respective combustors, wherein the fuel includes gaseous fuel and liquid fuel. In recent years, in order to minimize the emission of carbon dioxide, use of hydrogen fuel or a fuel containing hydrogen is recommended. However, since hydrogen has a high combustion rate, when such fuels are burned with a gas turbine combustor, the flame formed in the gas turbine combustor approaches and heats the structure of the gas turbine combustor, thereby degrading the reliability of the gas turbine combustor. To solve this problem, a combustor nozzle having multiple tubes has been proposed. The nozzle with multiple tubes is efficient for combustion of hydrogen by discharging fuel at a high speed. However, when hydrocarbon-based fuel such as natural gas is supplied to the multiple tubes, the fuel is injected at an excessively high speed, causing the flame to escape from the nozzle. As a result, the combustor with multiple tubes has the problem of not being able to burn a wide variety of fuels. The foregoing is intended merely to aid in the understanding of the background of the present disclosure, and is not intended to mean that the present disclosure falls within the purview of the related art that is already known to those skilled in the art. SUMMARY Accordingly, the present disclosure has been made keeping in mind the above problems occurring in the related art, and an objective of the present disclosure is to provide a combustor nozzle capable of burning a variety of fuels, not only hydrogen-based fuels, a combustor, and a gas turbine including the same. An aspect of the present disclosure provides a combustor nozzle including: a plurality of mixing tubes through which air and fuel flow; an accommodation tube accommodating and supporting the plurality of mixing tubes therein; a first fuel tube coupled to the accommodation tube to supply a first fuel into the accommodation tube; a second fuel tube coupled to the accommodation tube to supply a second fuel into the accommodation tube; a first fuel supply member supplying the first fuel into each mixing tube; and a second fuel supply member supplying the second fuel into each mixing tube. The combustor nozzle may further include: a tip plate coupled to a leading end of each accommodation tube; a middle plate spaced apart from the tip plate to define a first distribution space between the tip plate and the middle plate in which the first fuel is accommodated; and a rear plate spaced apart from the middle plate to define a second distribution space between the rear plate and the middle plate in which the second fuel is accommodated. The first fuel supply member may be connected to the first distribution space, and the second fuel supply member may be connected to the second distribution space. An outlet of the first fuel supply member may be disposed closer to the center of the mixing tube than an outlet of the second fuel supply member. An outlet of the second fuel supply member may be located further downstream of the outlet of the first fuel supply member. The second fuel supply member may extend from the second distribution space into the first distribution space and then into the mixing tube. The second fuel supply member may form a concentrated fuel flow along an inner circumferential wall of the mixing tube. The first fuel may include a hydrogen-based fuel having hydrogen as a major component or a hydrocarbon-based fuel having hydrocarbon as a major component, and the se