Coaxially staged burner for low-emission combustion chamber of dual-fuel gas turbine utilizing gaseous and liquid fuels

Patent metadata

Field	Value
Publication number	US-2026085837-A1
Application number	US-202519332080-A
Country	US
Kind code	A1
Filing date	Sep 18, 2025
Priority date	Sep 20, 2024
Publication date	Mar 26, 2026
Grant date	—

Abstract

The provided is a coaxially staged burner for a low-emission combustion chamber of a dual-fuel gas turbine utilizing gaseous and liquid fuels. The coaxially staged burner includes a mounting flange, a main fuel sleeve, and a swirler, where the mounting flange is provided with a fuel supply port; the main fuel sleeve is internally provided with coaxially nested four-stage fuel sleeves; the swirler includes a center pilot stage, a first premix stage, a second premix stage, a first-stage hub, and a second-stage hub; when a liquid fuel operates alone, the liquid fuel enters a swirler passage through a pilot-stage liquid fuel nozzle and a second-stage blade liquid fuel hole to achieve premixing and evaporation; and when a gaseous fuel operates alone, the gaseous fuel enters the swirler passage through a first-stage blade fuel hole and a second-stage blade gaseous fuel hole for mixing.

First claim

1 . A coaxially staged burner for a low-emission combustion chamber of a dual-fuel gas turbine utilizing gaseous and liquid fuels, comprising: a mounting flange ( 1 ), a main fuel sleeve ( 2 ), and a swirler ( 3 ), wherein the mounting flange ( 1 ), the main fuel sleeve ( 2 ), and the swirler ( 3 ) are connected in a sealed manner;
the swirler ( 3 ) comprises a first-stage hub ( 4 ), a plurality of first-stage full blades ( 7 ), a pilot-stage bluff body ( 10 ), a plurality of second-stage full blades ( 8 ), a second-stage hub ( 5 ), and a plurality of second-stage split blades ( 9 ); the pilot-stage bluff body ( 10 ) is connected to a rear end of the main fuel sleeve ( 2 ); a liquid fuel nozzle ( 6 ) is disposed inside the pilot-stage bluff body ( 10 ); an inner periphery of the first-stage hub ( 4 ) and an outer wall of the pilot-stage bluff body ( 10 ) are connected via the plurality of first-stage full blades ( 7 ); an inner periphery of the second-stage hub ( 5 ) and an outer wall of the first-stage hub ( 4 ) are connected via the plurality of second-stage full blades ( 8 ); and the inner periphery of the second-stage hub ( 5 ) and the outer wall of the first-stage hub ( 4 ) are connected via the plurality of second-stage split blades ( 9 ); and the pilot-stage bluff body ( 10 ) and the liquid fuel nozzle ( 6 ) form a center pilot stage; the pilot-stage bluff body ( 10 ), the first-stage hub ( 4 ), and the plurality of first-stage full blades ( 7 ) form a first premix stage; and the first-stage hub ( 4 ), the second-stage hub ( 5 ), the plurality of second-stage full blades ( 8 ), and the plurality of second-stage split blades ( 9 ) form a second premix stage; wherein the plurality of second-stage full blades ( 8 ) are arranged at equal intervals around an axis of the pilot-stage bluff body ( 10 ); each of the plurality of second-stage full blades ( 8 ) is internally provided with a second-stage blade gaseous fuel cavity ( 82 ); and an outer wall of the second-stage blade gaseous fuel cavity ( 82 ) is provided with a plurality of second-stage blade gaseous fuel holes ( 81 ); wherein the plurality of second-stage split blades ( 9 ) are arranged at equal intervals around the axis of the pilot-stage bluff body ( 10 ); one second-stage split blade ( 9 ) is disposed between any two adjacent second-stage full blades ( 8 ); each of the plurality of second-stage split blades ( 9 ) is internally provided with a second-stage blade liquid fuel cavity ( 92 ); and an outer wall of the second-stage blade liquid fuel cavity ( 92 ) is provided with a plurality of second-stage blade liquid fuel holes ( 91 ).

2 . The coaxially staged burner for the low-emission combustion chamber of the dual-fuel gas turbine utilizing gaseous and liquid fuels according to claim 1 , wherein the mounting flange ( 1 ) comprises a pilot-stage liquid fuel port ( 11 ), a first-premix-stage gaseous fuel port ( 12 ), a second-premix-stage gaseous fuel port ( 13 ), second-premix-stage liquid fuel ports ( 14 ), and a mounting and positioning base ( 15 ); a front end of the main fuel sleeve ( 2 ) is connected to the mounting and positioning base ( 15 ); a front side of the mounting and positioning base ( 15 ) is provided with one pilot-stage liquid fuel port ( 11 ), one first-premix-stage gaseous fuel port ( 12 ), one second-premix-stage gaseous fuel port ( 13 ), and two second-premix-stage liquid fuel ports ( 14 ); and the pilot-stage liquid fuel port ( 11 ), the first-premix-stage gaseous fuel port ( 12 ), the second-premix-stage gaseous fuel port ( 13 ), and the second-premix-stage liquid fuel ports ( 14 ) are threaded to an external fuel supply pipe.

3 . The coaxially staged burner for the low-emission combustion chamber of the dual-fuel gas turbine utilizing gaseous and liquid fuels according to claim 2 , wherein the main fuel sleeve ( 2 ) is internally provided with a pilot-stage liquid fuel pipe ( 21 ), a first-stage gaseous fuel annular cavity ( 221 ), a first-stage gaseous fuel pipe ( 222 ), a second-stage gaseous fuel annular cavity ( 231 ), a second-stage gaseous fuel pipe ( 232 ), a second-stage liquid fuel annular cavity ( 241 ), a second-stage liquid fuel pipe ( 242 ), and a plurality of oil supply branches ( 243 ); the second-stage gaseous fuel pipe ( 232 ), the first-stage gaseous fuel pipe ( 222 ), and the second-stage liquid fuel pipe ( 242 ) are annular pipes; the pilot-stage liquid fuel pipe ( 21 ), the second-stage gaseous fuel pipe ( 232 ), the first-stage gaseous fuel pipe ( 222 ), and the second-stage liquid fuel pipe ( 242 ) are arranged coaxially; a second-stage liquid fuel transition cavity ( 244 ), the second-stage gaseous fuel pipe ( 232 ), the first-stage gaseous fuel pipe ( 222 ), and the second-stage liquid fuel pipe ( 242 ) are arranged sequentially from inside to outside around the pilot-stage liquid fuel pipe ( 21 ); an inner wall of a rear end of the pilot-stage liquid fuel pipe ( 21 ) is provided with the second-stage liquid fuel transition cavity ( 244 ); a thin wall is disposed between the pilot-stage liquid fuel pipe ( 21 ) and the second-stage liquid fuel transition cavity ( 244 ); and the second-stage liquid fuel transition cavity ( 244 ) and the second-stage liquid fuel pipe ( 242 ) communicate in a sealed manner via the plurality of oil supply branches ( 243 ) arranged circumferentially.

4 . The coaxially staged burner for the low-emission combustion chamber of the dual-fuel gas turbine utilizing gaseous and liquid fuels according to claim 3 , wherein a front end of the pilot-stage liquid fuel pipe ( 21 ) communicates with the pilot-stage liquid fuel port ( 11 ); a front end of the second-stage gaseous fuel pipe ( 232 ) communicates with the second-stage gaseous fuel annular cavity ( 231 ); the second-premix-stage gaseous fuel port ( 13 ) communicates with the second-stage gaseous fuel annular cavity ( 231 ); a front end of the first-stage gaseous fuel pipe ( 222 ) communicates with the first-stage gaseous fuel annular cavity ( 221 ); the first-premix-stage gaseous fuel port ( 12 ) communicates with the first-stage gaseous fuel annular cavity ( 221 ); a front end of the second-stage liquid fuel pipe ( 242 ) communicates with the second-stage liquid fuel annular cavity ( 241 ); and the two second-premix-stage liquid fuel ports ( 14 ) communicate with the second-stage liquid fuel annular cavity ( 241 ).

5 . The coaxially staged burner for the low-emission combustion chamber of the dual-fuel gas turbine utilizing gaseous and liquid fuels according to claim 4 , wherein the liquid fuel nozzle ( 6 ) communicates with a rear end of the pilot-stage liquid fuel pipe ( 21 ); the plurality of first-stage full blades ( 7 ) are arranged at equal intervals around the axis of the pilot-stage bluff body ( 10 ); each of the plurality of first-stage full blades ( 7 ) is internally provided with a first-stage blade gaseous fuel cavity ( 72 ), a first-stage blade gaseous fuel delivery pipe ( 73 ), and a first-stage blade liquid fuel delivery pipe ( 74 ); the first-stage blade gaseous fuel cavity ( 72 ) communicates with the first-stage gaseous fuel pipe ( 222 ); an outer wall of the first-stage blade gaseous fuel cavity ( 72 ) is provided with a plurality of first-stage blade fuel holes ( 71 ); an end of the first-stage blade gaseous fuel delivery pipe ( 73 ) communicates with the second-stage gaseous fuel pipe ( 232 ); and an end of the first-stage blade liquid fuel delivery pipe ( 74 ) communicates with the second-stage liquid fuel transition cavity ( 244 ).

6 . The coaxially staged burner for the low-emission combustion chamber of the dual-fuel gas turbine utilizing gaseous and liquid fuels according to claim 1 , wherein the first-stage hub ( 4 ) is a cavity structure; and the first-stage hub ( 4 ) is internally provided with a gaseous-liqui

Assignees

• Univ Harbin Eng

Inventors

• Zhao ningbo
• Feng Zhongmin
• Sun Jihao
• Luo Shaowen
• Xu Honghao
• Yang Honglei
• Zheng Hongtao

Classifications

• F23R3/36

  Supply of different fuels · CPC title

• F23R3/343

  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

• F23R3/14

  by using swirl vanes · CPC title

• F23D2204/10

  gaseous and liquid fuel · CPC title

• F23R3/346

  for staged combustion · CPC title