Fuel-air mixing system with mixing chambers of various lengths for gas turbine system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/22
F23R-003/28
F23D-014/62
F23R-003/10
F23D-014/64
F23R-003/22
출원번호
US-0797848
(2013-03-12)
등록번호
US-9650959
(2017-05-16)
발명자
/ 주소
Boardman, Gregory Allen
Melton, Patrick Benedict
Westmoreland, James Harold
Chila, Ronald James
Crothers, Sarah Lori
출원인 / 주소
General Electric Company
대리인 / 주소
Fletcher Yoder, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
68
초록▼
Embodiments of the present disclosure are directed to systems and methods for premixing fuel and air prior to combustion within a combustion chamber. The system includes a plurality of fuel injectors and a plurality of mixing tubes, wherein each mixing tube has a first portion for receiving one of t
Embodiments of the present disclosure are directed to systems and methods for premixing fuel and air prior to combustion within a combustion chamber. The system includes a plurality of fuel injectors and a plurality of mixing tubes, wherein each mixing tube has a first portion for receiving one of the plurality of fuel injectors and a second portion having a mixing chamber that is configured to mix fuel and air. The length of the mixing chamber varies among the plurality of mixing tubes to allow for different mixing times.
대표청구항▼
1. A premixing system for a gas turbine engine, the premixing system comprising: a plurality of fuel injectors;a plurality of mixing tubes, each mixing tube comprising: an annular wall defining the mixing tube and comprising a plurality of apertures configured to enable air to flow radially into the
1. A premixing system for a gas turbine engine, the premixing system comprising: a plurality of fuel injectors;a plurality of mixing tubes, each mixing tube comprising: an annular wall defining the mixing tube and comprising a plurality of apertures configured to enable air to flow radially into the mixing tube;a first portion configured to receive one of the plurality of fuel injectors, wherein the one fuel injector of the plurality of fuel injectors is positioned coaxially within the first portion of the mixing tube; anda second portion comprising a mixing chamber configured to mix fuel provided via one or more holes formed in the one fuel injector and the air, wherein the mixing chamber is defined by and extends between a tip of the one fuel injector and a second and of the mixing tube that is configured to deposit the fuel and the air directly into a combustion chamber of the gas turbine engine, wherein the fuel injector having a first end and the tip of the one fuel injector disposed at an opposite downstream end of the one fuel injector and the one or more holes are positioned upstream of the tip of the one fuel injector; wherein a respective length of the respective mixing chamber varies among the plurality of mixing tubes. 2. The system of claim 1, wherein the plurality of mixing tubes are of substantially similar length. 3. The system of claim 2, wherein a ratio between a first length of the first portion and a second length of the second portion varies among the plurality of mixing tubes. 4. The system of claim 1, wherein at least two of the plurality of fuel injectors have different lengths. 5. The system of claim 1, wherein the plurality of apertures formed on the respective annular wall of a first mixing tube of the plurality of mixing tube are the only apertures formed on the respective annular wall of the first mixing tube of the plurality of mixing tubes that are configured to enable air to flow radially into the first mixing tube, the plurality of apertures formed on the respective annular wall of the first mixing tube are positioned a first distance away from a first outlet of the first mixing tube, and the plurality of apertures formed on the respective annular wall of a second mixing tube of the plurality of mixing tubes are the only apertures formed on the respective annular wall of the second mixing tube of the plurality of mixing tubes that are configured to enable air to flow radially into the second mixing tube, and the plurality of apertures formed on the respective annular wall of the second mixing tube are positioned a second distance away from a second outlet of the second mixing tube, wherein the first and second distances are different. 6. The system of claim 5, wherein each of the plurality of fuel injectors comprises one or more holes configured to inject fuel directly into the respective mixing tube, and the respective one or more holes of a first fuel injector of the plurality of fuel injectors are the only holes formed in the first fuel injector that are configured to inject fuel directly into the first mixing tube, the respective one or more holes of the first fuel injector are positioned at a third distance from the first outlet of the first mixing tube, the respective one or more holes of a second fuel injector of the plurality of fuel injectors are the only holes formed in the second fuel injector that are configured to inject fuel directly into the second mixing tube, and the respective one or more holes of the second fuel injector are positioned at a fourth distance from the second outlet of the second mixing tube, and the third and fourth distances are different. 7. The system of claim 1, wherein the respective second ends of each of the plurality of mixing tubes are substantially aligned in a plane. 8. The system of claim 1, wherein the plurality of apertures are positioned upstream of the one or more holes. 9. The system of claim 1, wherein the plurality of apertures are the only apertures formed on the annular wall of each mixing tube that are configured to enable air to flow radially into each mixing tube, the one or more holes are the only holes formed in the one fuel injector, and an axial distance between the plurality of apertures and the one or more holes is constant among the plurality of mixing tubes. 10. The system of claim 1, wherein a respective axial distance between the tip and the one or more holes is constant among the plurality of fuel injectors. 11. A gas turbine system comprising: a combustor comprising: a combustion chamber;a plurality of fuel injectors;a plurality of mixing tubes, each mixing tube comprising: an annular wall defining the mixing tube and comprising a plurality of apertures configured to enable air to flow radially into the mixing tube, wherein the plurality of apertures are positioned in a section of the annular wall that extends along part of an axial length of the annular wall and the remainder of the annular wall outside of the section is devoid of apertures that are configured to enable air to flow radially into the mixing tube;a first portion configured to receive one of the plurality of fuel injectors; anda second portion downstream of the first portion and comprising a mixing chamber configured to mix fuel provided by the one fuel injector of the plurality of fuel injectors and the air;wherein the respective mixing chamber of a first mixing tube of the plurality of mixing tubes has a different length than the respective mixing chamber of a second mixing tube of the plurality of the mixing tubes;wherein the respective section of the first mixing tube is positioned a first distance away from the combustion chamber, and the respective section of the second mixing tube is positioned a second distance away from the combustion chamber, and the first and second distances are different from one another. 12. The system of claim 11, wherein the plurality of mixing tubes are of substantially similar length. 13. The system of claim 11, wherein at least two fuel injectors of the plurality of fuel injectors have different lengths. 14. The system of claim 11, wherein each of the plurality of mixing tubes extends between a first end and a second end, wherein the first end is configured to receive the one fuel injector and the second end is configured to deposit a fuel-air mixture directly into the combustion chamber. 15. The system of claim 11, wherein each of the plurality of fuel injectors comprises one or more holes configured to inject fuel into the respective mixing tube, and the respective one or more holes of a first fuel injector of the plurality of fuel injectors are the only holes formed in the first fuel injector that are configured to inject fuel directly into the first mixing tube, the respective one or more holes of the one of the plurality of mixing injectors are positioned at a third distance from the combustion chamber and the respective one or more holes of the another of the plurality of fuel injectors are the only holes formed in the another of the plurality of fuel injectors, and the respective one or more holes of the another fuel injector are positioned at a fourth distance different from the third distance from the combustion chamber. 16. The system of claim 11, wherein each fuel injector of the plurality of fuel injectors comprises one or more holes configured to flow the fuel from the respective fuel injector into the respective mixing chamber, the respective one or more holes are the only holes formed in the respective fuel injector that are configured to provide fuel to the respective mixing chamber and are positioned within a section of the respective fuel injector having a second discrete axial length less than a total length of the respective fuel injector, and an axial distance between the section of the annular wall and the section of the fuel injector is constant among the plurality of mixing tubes. 17. A method comprising: receiving air radially into a plurality of mixing chambers via apertures formed on a respective annular wall surrounding each of the plurality of mixing chambers, wherein each of the plurality of mixing chambers is within one of a plurality of mixing tubes;depositing fuel via holes formed on a plurality of fuel injectors into the plurality of mixing chambers, wherein the respective holes are formed upstream of a respective tip that forms a respective downstream end of a respective fuel injector of the plurality of fuel injectors, and each of the plurality of fuel injectors is positioned coaxially within one of the plurality of mixing tubes; andmixing the air and fuel within each of the plurality of mixing chambers, wherein a respective distance between the respective tip of the respective fuel injector of the plurality of fuel injectors and a respective outlet of the respective mixing chamber of the plurality of mixing chambers varies among the plurality of mixing tubes such that air-fuel mixing within a first mixing chamber of the plurality of mixing chambers is longer in duration than air-fuel mixing within a second mixing chamber of the plurality of mixing chambers. 18. The method of claim 17, wherein more than two different durations of air-fuel mixing occurs within the plurality of mixing chambers. 19. The method of claim 17, comprising depositing the air and the fuel directly into a combustion chamber from the first mixing chamber and the second mixing chamber of the plurality of mixing chambers. 20. The method of claim 17, wherein the apertures formed on the respective annular wall are positioned in a section that extends along a respective axial length of the respective annular wall, the remainder of the respective annular wall is devoid of the apertures, the respective section of the first mixing chamber is positioned a first distance away from a combustion chamber, and the respective section of the second mixing chamber is positioned a second distance away from the combustion chamber, and the first and second distances are different from one another, thereby facilitating the longer duration of air-fuel mixing within the first mixing chamber as compared to the second mixing chamber.
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