Integrated combustor and stage 1 nozzle in a gas turbine and method
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01C-001/00
F01D-009/02
F01D-009/04
F23R-003/00
F23R-003/28
F23R-003/46
출원번호
US-0269411
(2008-11-12)
등록번호
US-9822649
(2017-11-21)
발명자
/ 주소
Davis, Jr., Lewis Berkley
Ziminsky, Willy Steve
McMahan, Kevin Weston
Chila, Ronald James
Meshkov, Sergey Anatolievich
출원인 / 주소
GENERAL ELECTRIC COMPANY
대리인 / 주소
Nixon & Vanderhye P.C.
인용정보
피인용 횟수 :
0인용 특허 :
33
초록▼
An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbi
An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.
대표청구항▼
1. An integrated can-annular combustor and stage one nozzle in a gas turbine, comprising a liner, a transition piece, and a stage one nozzle integrated as a single part, wherein the liner and the transition piece define a combustion chamber, the combustion chamber receiving premixed fuel and air fro
1. An integrated can-annular combustor and stage one nozzle in a gas turbine, comprising a liner, a transition piece, and a stage one nozzle integrated as a single part, wherein the liner and the transition piece define a combustion chamber, the combustion chamber receiving premixed fuel and air from at least one fuel nozzle group operatively associated with the liner to produce hot combustion gas, and wherein the hot combustion gas is delivered from the liner through the transition piece and stage one nozzle to the turbine, one of the one or more fuel nozzle groups including a plurality of mixing nozzles that premix fuel and air and concentrate heat release and reduce flame length. 2. An integrated can-annular combustor and stage one nozzle according to claim 1, wherein the mixing nozzles are arranged in one of a single plane or a plurality of axial locations and include fuel control for each axial location. 3. An integrated can-annular combustor and stage one nozzle according to claim 2, further comprising at least one first stage fuel injector cooperable with the at least one fuel nozzle group and a second stage fuel injector disposed in the transition piece, wherein the fuel control comprises a fuel circuit that controllably divides fuel flow between the at least one first stage fuel injector and the second stage fuel injector. 4. An integrated can-annular combustor and stage one nozzle according to claim 1, wherein the mixing nozzles have a length of 1/10 to 1/10 of a liner diameter. 5. An integrated can-annular combustor and stage one nozzle according to claim 1, wherein the mixing nozzles are arranged in an array in a single plane. 6. An integrated can-annular combustor and stage one nozzle according to claim 1, wherein the mixing nozzles are arranged in an array in a plurality of axial locations. 7. An integrated can-annular combustor and stage one nozzle according to claim 1, wherein the gas turbine includes a stage one turbine bucket disposed adjacent the single part, and wherein the transition piece comprises a choked end that directs flow of the hot combustion gas at a suitable angle toward the stage one turbine bucket. 8. An integrated can-annular combustor and stage one nozzle according to claim 7, wherein the choked end of the transition piece serves as the stage one nozzle. 9. An integrated can-annular combustor and stage one nozzle according to claim 1, wherein the gas turbine includes a stage one turbine bucket disposed adjacent the single part, and wherein the transition piece comprises an extended shroud disposed surrounding the stage one nozzle, the extended shroud and the stage one nozzle directing flow of the hot combustion gas at a suitable angle toward the stage one turbine bucket. 10. An integrated can-annular combustor and stage one nozzle in a gas turbine, comprising a liner, a transition piece, and a stage one nozzle, wherein the liner and the transition piece define a combustion chamber, the combustion chamber receiving premixed fuel and air from at least one fuel nozzle group operatively associated with the liner to produce hot combustion gas, and wherein the hot combustion gas is delivered from the liner through the transition piece and stage one nozzle to the turbine, one of the one or more fuel nozzle groups including a plurality of mixing nozzles that premix fuel and air and concentrate heat release and reduce flame length, and wherein the reduced flame length enables the stage one nozzle, the liner and the transition piece to be integrated into a single part. 11. A method of integrating a can-annular combustor and a stage one nozzle in a gas turbine, the method comprising: arranging a combustion chamber to receive premixed fuel and air from at least one fuel nozzle group, wherein the combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine;providing one of the one or more fuel nozzle groups with a plurality of mixing nozzles that premix fuel and air and concentrate heat release and reduce flame length; andintegrating the stage one nozzle, the liner and the transition piece into a single part by virtue of the reduced flame length,wherein the mixing nozzles have a length of 1/10 to 1/100 of a liner diameter.
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