Gas turbine engine adapted for use in combination with an apparatus for separating a portion of oxygen from compressed air
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-003/26
F02C-006/10
출원번호
US-0848544
(2007-08-31)
등록번호
US-8127558
(2012-03-06)
발명자
/ 주소
Bland, Robert J.
Horazak, Dennis A.
출원인 / 주소
Siemens Energy, Inc.
인용정보
피인용 횟수 :
59인용 특허 :
8
초록▼
A gas turbine engine is provided comprising an outer shell, a compressor assembly, at least one combustor assembly, a turbine assembly and duct structure. The outer shell includes a compressor section, a combustor section, an intermediate section and a turbine section. The intermediate section inclu
A gas turbine engine is provided comprising an outer shell, a compressor assembly, at least one combustor assembly, a turbine assembly and duct structure. The outer shell includes a compressor section, a combustor section, an intermediate section and a turbine section. The intermediate section includes at least one first opening and at least one second opening. The compressor assembly is located in the compressor section to define with the compressor section a compressor apparatus to compress air. The at least one combustor assembly is coupled to the combustor section to define with the combustor section a combustor apparatus. The turbine assembly is located in the turbine section to define with the turbine section a turbine apparatus. The duct structure is coupled to the intermediate section to receive at least a portion of the compressed air from the compressor apparatus through the at least one first opening in the intermediate section, pass the compressed air to an apparatus for separating a portion of oxygen from the compressed air to produced vitiated compressed air and return the vitiated compressed air to the intermediate section via the at least one second opening in the intermediate section.
대표청구항▼
1. A gas turbine engine comprising: an outer shell having a compressor section, a combustor section, an intermediate section and a turbine section, said intermediate section being located between said combustor section and said turbine section and including at least one first opening and at least on
1. A gas turbine engine comprising: an outer shell having a compressor section, a combustor section, an intermediate section and a turbine section, said intermediate section being located between said combustor section and said turbine section and including at least one first opening and at least one second opening;a compressor assembly located in said compressor section to define with said compressor section a compressor apparatus to compress air;at least one combustor assembly coupled to said combustor section to define with said combustor section a combustor apparatus to receive compressed air and a fuel, combine the air and fuel to create an air/fuel mixture and ignite the air/fuel mixture to create combustion products;a turbine assembly comprising a plurality of stationary vanes, a plurality of rotatable blades and a rotatable shaft and disc assembly coupled to said blades, said turbine assembly being located in said turbine section to define with said turbine section a turbine apparatus to receive the combustion products from said combustor apparatus such that the combustion products expand in said turbine apparatus causing said blades and shaft and disc assembly to rotate;duct structure coupled to said intermediate section to receive at least a portion of the compressed air from said compressor apparatus through said at least one first opening in said intermediate section, pass the compressed air to an apparatus for separating a portion of oxygen from the compressed air to produce vitiated compressed air and return the vitiated compressed air to said intermediate section via said at least one second opening in said intermediate section; anda ring-shaped divider coupled to an inner surface of said intermediate section of said outer shell between said at least one first opening and said at least one second opening, said ring-shaped divider extending from said inner surface of said intermediate section to a location between said inner surface and a transition duct through which the combustion products travel to said turbine assembly so as to allow both compressed air and vitiated compressed air into said combustor apparatus to combust therein. 2. The gas turbine engine as set forth in claim 1, wherein said duct structure comprises a compressed air plenum coupled to said outer shell so as to communicate with said at least one first opening in said intermediate section of said outer shell and a vitiated air plenum coupled to said outer shell so as to communicate with said at least one second opening in said intermediate section of said outer shell. 3. The gas turbine engine as set forth in claim 2, wherein said intermediate section of said outer shell comprises a plurality of first openings which are aligned so as to define a first row of openings and a plurality of second openings which are aligned so as to define a second row of openings. 4. The gas turbine engine as set forth in claim 3, wherein said compressed air plenum is generally annular in shape and said vitiated air plenum is generally annular in shape. 5. The gas turbine engine as set forth in claim in claim 4, wherein said duct structure further comprises compressed air piping structure coupled to said compressed air plenum and the apparatus for separating a portion of oxygen from the compressed air, and vitiated air piping structure coupled to said vitiated air plenum and the apparatus for separating a portion of oxygen from the compressed air. 6. The gas turbine engine as set forth in claim 1, wherein said ring-shaped divider is configured such that: about 40-60% of the compressed air entering said intermediate section passes through said at least one first opening to the apparatus for separating a portion of oxygen from the compressed air; andabout 40-60% of the compressed air entering said intermediate section passes directly to said combustor apparatus without passing to the apparatus for separating a portion of oxygen from the compressed air. 7. A gas turbine engine comprising: a compressor apparatus to compress air;a combustor apparatus to receive compressed air and a fuel, combine the air and fuel to create an air/fuel mixture and ignite the air/fuel mixture to create combustion products;a turbine apparatus comprising a turbine assembly including a plurality of stationary vanes, a plurality of rotatable blades and a rotatable shaft and disc assembly coupled to said blades, said turbine apparatus to receive the combustion products from said combustor apparatus such that the combustion products expand in said turbine apparatus causing said blades and shaft and disc assembly to rotate;an intermediate section located between said combustor apparatus and said turbine apparatus and including at least one first opening and at least one second opening;duct structure coupled to said intermediate section to receive a first portion of the compressed air from said compressor apparatus through said at least one first opening in said intermediate section, pass the first portion of compressed air to an apparatus for separating a portion of oxygen from the first portion of compressed air to produce vitiated compressed air and return the vitiated compressed air to said intermediate section via said at least one second opening in said intermediate section, the vitiated compressed air passing to said combustor apparatus; andstructure provided in said intermediate section for allowing the first portion of compressed air to pass into said at least one first opening while allowing a second portion of the compressed air to pass directly to said combustor apparatus to combust therein without passing to the apparatus for separating a portion of oxygen from the first portion of compressed air. 8. The gas turbine engine as set forth in claim 7, wherein said duct structure comprises a compressed air plenum coupled to said intermediate section so as to communicate with said at least one first opening in said intermediate section and a vitiated air plenum coupled to said intermediate section so as to communicate with said at least one second opening in said intermediate section. 9. The gas turbine engine as set forth in claim 8, wherein said intermediate section comprises a plurality of first openings which are aligned so as to define a first row of openings and a plurality of second openings which are aligned so as to define a second row of openings. 10. The gas turbine engine as set forth in claim 9, wherein said compressed air plenum is generally annular in shape and said vitiated air plenum is generally annular in shape. 11. The gas turbine engine as set forth in claim 10, wherein said duct structure further comprises compressed air piping structure coupled to said compressed air plenum and vitiated air piping structure coupled to said vitiated air plenum. 12. The gas turbine engine as set forth in claim 7, wherein said structure provided in said intermediate section for allowing the first portion of compressed air to pass into said at least one first opening while allowing a second portion of the compressed air to pass directly to said combustor apparatus comprises a ring-shaped divider coupled to an inner surface of said intermediate section between said at least one first opening and said at least one second opening. 13. The gas turbine engine as set forth in claim 12, wherein said ring-shaped divider extends from said inner surface of said intermediate section to a location between said inner surface and a transition duct through which the combustion products travel to said turbine assembly. 14. The gas turbine engine as set forth in claim 7, wherein said structure provided in said intermediate section for allowing the first portion of compressed air to pass into said at least one first opening while allowing a second portion of the compressed air to pass directly to said combustor apparatus is configured such that: about 40-60% of the compressed air entering said intermediate section passes through said at least one first opening to the apparatus for separating a portion of oxygen from the first portion of compressed air; andabout 40-60% of the compressed air entering said intermediate section passes directly to said combustor apparatus without passing to the apparatus for separating a portion of oxygen from the first portion of compressed air. 15. A gas turbine engine comprising: an outer shell having a compressor section, a combustor section, an intermediate section and a turbine section, said intermediate section being located between said combustor section and said turbine section and including a row of first openings and a row of second openings;a compressor assembly located in said compressor section to define with said compressor section a compressor apparatus to compress air;at least one combustor assembly coupled to said combustor section to define with said combustor section a combustor apparatus to receive compressed air and a fuel, combine the air and fuel to create an air/fuel mixture and ignite the air/fuel mixture to create combustion products;a turbine assembly comprising a plurality of stationary vanes, a plurality of rotatable blades and a rotatable shaft and disc assembly coupled to said blades, said turbine assembly being located in said turbine section to define with said turbine section a turbine apparatus to receive the combustion products from said combustor apparatus such that the combustion products expand in said turbine apparatus causing said blades and shaft and disc assembly to rotate;duct structure coupled to said intermediate section to receive a first portion of the compressed air from said compressor apparatus through said row of first openings in said intermediate section, pass the first portion of compressed air to an apparatus for separating a portion of oxygen from the first portion of compressed air to produce vitiated compressed air and return the vitiated compressed air to said intermediate section via said row of second openings in said intermediate section; andstructure provided in said intermediate section for allowing the first portion of compressed air to pass into said row of first openings while allowing a second portion of the compressed air to pass directly to said combustor apparatus to combust therein without passing to the apparatus for separating a portion of oxygen from the first portion of compressed air. 16. The gas turbine engine as set forth in claim 15, wherein said duct structure comprises a generally annular compressed air plenum coupled to said outer shell so as to communicate with said at least one first opening in said intermediate section of said outer shell and a generally annular vitiated air plenum coupled to said outer shell so as to communicate with said at least one second opening in said intermediate section of said outer shell. 17. The gas turbine engine as set forth in claim in claim 16, wherein said duct structure further comprises compressed air piping structure coupled to said compressed air plenum and the apparatus for separating a portion of oxygen from the compressed air, and vitiated air piping structure coupled to said vitiated air plenum and the apparatus for separating a portion of oxygen from the compressed air. 18. The gas turbine engine as set forth in claim 15, wherein said structure provided in said intermediate section for allowing the first portion of compressed air to pass into said row of first openings while allowing a second portion of the compressed air to pass directly to said combustor apparatus comprises a ring-shaped divider coupled to an inner surface of said intermediate section between said row of first openings and said row of second openings. 19. The gas turbine engine as set forth in claim 18, wherein said ring-shaped divider extends from said inner surface of said intermediate section to a location between said inner surface and a transition duct through which the combustion products travel to said turbine assembly. 20. The gas turbine engine as set forth in claim 18, wherein said ring-shaped divider is configured such that: about 40-60% of the compressed air entering said intermediate section passes through said row of first openings to the apparatus for separating a portion of oxygen from the compressed air; andabout 40-60% of the compressed air entering said intermediate section passes directly to said combustor apparatus without passing to the apparatus for separating a portion of oxygen from the compressed air.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (8)
Moller Michael Scott, Bolted gas turbine combustor transition coupling.
Kang Doohee (Macungie PA) Thorogood Robert Michael (Cary NC) Allam Rodney John (Guildford GB2) Topham Anthony Knut James (Walton on Thames GB2), Integrated production of oxygen and electric power.
Drnevich Raymond Francis ; Gottzmann Christian Friedrich, Method for producing oxidized product and generating power using a solid electrolyte membrane integrated with a gas turb.
Prasad Ravi ; Gottzmann Christian Friedrich ; Drnevich Raymond Francis, Method for producing oxygen and generating power using a solid electrolyte membrane integrated with a gas turbine.
Chrtien Denis (Saint MandFRX) Girault Jean-Louis (Liege BEX) Darredeau Bernard (Sartrouville FRX), Process for the operation of a gas turbine group and the production of at least one air gas.
Minta, Moses; Mittricker, Franklin F.; Rasmussen, Peter C.; Starcher, Loren K.; Rasmussen, Chad C.; Wilkins, James T.; Meidel, Jr., Richard W., Low emission power generation and hydrocarbon recovery systems and methods.
Oelkfe, Russell H.; Huntington, Richard A.; Mittricker, Franklin F., Low emission power generation systems and methods incorporating carbon dioxide separation.
Minto, Karl Dean; Denman, Todd Franklin; Mittricker, Franklin F.; Huntington, Richard Alan, Method and system for combustion control for gas turbine system with exhaust gas recirculation.
Mittricker, Franklin F.; Starcher, Loren K.; Rasmussen, Chad C.; Huntington, Richard A.; Hershkowitz, Frank, Methods and systems for controlling the products of combustion.
Mittricker, Franklin F.; Starcher, Loren K.; Rasmussen, Chad; Huntington, Richard A.; Hershkowitz, Frank, Methods and systems for controlling the products of combustion.
Mittricker, Franklin F.; Huntington, Richard A.; Starcher, Loren K.; Sites, Omar Angus, Methods of varying low emission turbine gas recycle circuits and systems and apparatus related thereto.
Wichmann, Lisa Anne; Simpson, Stanley Frank, Methods, systems and apparatus relating to combustion turbine power plants with exhaust gas recirculation.
Huntington, Richard A.; Denton, Robert D.; McMahon, Patrick D.; Bohra, Lalit K.; Dickson, Jasper L., Processing exhaust for use in enhanced oil recovery.
Gupta, Himanshu; Huntington, Richard; Minta, Moses K.; Mittricker, Franklin F.; Starcher, Loren K., Stoichiometric combustion of enriched air with exhaust gas recirculation.
Denton, Robert D.; Gupta, Himanshu; Huntington, Richard; Minta, Moses; Mittricker, Franklin F.; Starcher, Loren K., Stoichiometric combustion with exhaust gas recirculation and direct contact cooler.
Stoia, Lucas John; DiCintio, Richard Martin; Melton, Patrick Benedict; Romig, Bryan Wesley; Slobodyanskiy, Ilya Aleksandrovich, System and method for a multi-wall turbine combustor.
Huntington, Richard A.; Minto, Karl Dean; Xu, Bin; Thatcher, Jonathan Carl; Vorel, Aaron Lavene, System and method for a stoichiometric exhaust gas recirculation gas turbine system.
Valeev, Almaz Kamilevich; Ginesin, Leonid Yul'evich; Shershnyov, Borys Borysovich; Sidko, Igor Petrovich; Meshkov, Sergey Anatolievich, System and method for a turbine combustor.
Slobodyanskiy, Ilya Aleksandrovich; Davis, Jr., Lewis Berkley; Minto, Karl Dean, System and method for barrier in passage of combustor of gas turbine engine with exhaust gas recirculation.
Minto, Karl Dean; Slobodyanskiy, Ilya Aleksandrovich; Davis, Jr., Lewis Berkley; Lipinski, John Joseph, System and method for controlling the combustion process in a gas turbine operating with exhaust gas recirculation.
Huntington, Richard A.; Dhanuka, Sulabh K.; Slobodyanskiy, Ilya Aleksandrovich, System and method for diffusion combustion in a stoichiometric exhaust gas recirculation gas turbine system.
Huntington, Richard A.; Dhanuka, Sulabh K.; Slobodyanskiy, Ilya Aleksandrovich, System and method for diffusion combustion with fuel-diluent mixing in a stoichiometric exhaust gas recirculation gas turbine system.
Huntington, Richard A.; Dhanuka, Sulabh K.; Slobodyanskiy, Ilya Aleksandrovich, System and method for diffusion combustion with oxidant-diluent mixing in a stoichiometric exhaust gas recirculation gas turbine system.
Subramaniyan, Moorthi; Hansen, Christian Michael; Huntington, Richard A.; Denman, Todd Franklin, System and method for exhausting combustion gases from gas turbine engines.
Huntington, Richard A.; Dhanuka, Sulabh K.; Slobodyanskiy, Ilya Aleksandrovich, System and method for load control with diffusion combustion in a stoichiometric exhaust gas recirculation gas turbine system.
Huntington, Richard A.; Mittricker, Franklin F.; Starcher, Loren K.; Dhanuka, Sulabh K.; O'Dea, Dennis M.; Draper, Samuel D.; Hansen, Christian M.; Denman, Todd; West, James A., System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system.
Biyani, Pramod K.; Leyers, Scott Walter; Miranda, Carlos Miguel, System and method for protecting components in a gas turbine engine with exhaust gas recirculation.
Biyani, Pramod K.; Saha, Rajarshi; Dasoji, Anil Kumar; Huntington, Richard A.; Mittricker, Franklin F., System and method for protecting components in a gas turbine engine with exhaust gas recirculation.
O'Dea, Dennis M.; Minto, Karl Dean; Huntington, Richard A.; Dhanuka, Sulabh K.; Mittricker, Franklin F., System and method of control for a gas turbine engine.
Oelfke, Russell H.; Huntington, Richard A.; Dhanuka, Sulabh K.; O'Dea, Dennis M.; Denton, Robert D.; Sites, O. Angus; Mittricker, Franklin F., Systems and methods for carbon dioxide capture in low emission combined turbine systems.
Thatcher, Jonathan Carl; West, James A.; Vorel, Aaron Lavene, Systems and methods for controlling exhaust gas flow in exhaust gas recirculation gas turbine systems.
Mittricker, Franklin F.; Huntington, Richard A.; Dhanuka, Sulabh K.; Sites, Omar Angus, Systems and methods for controlling stoichiometric combustion in low emission turbine systems.
Borchert, Bradford David; Trout, Jesse Edwin; Simmons, Scott Robert; Valeev, Almaz; Slobodyanskiy, Ilya Aleksandrovich; Sidko, Igor Petrovich; Ginesin, Leonid Yul'evich, Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation.
Vorel, Aaron Lavene; Thatcher, Jonathan Carl, Systems and methods of estimating a combustion equivalence ratio in a gas turbine with exhaust gas recirculation.
Thatcher, Jonathan Carl; Slobodyanskiy, Ilya Aleksandrovich; Vorel, Aaron Lavene, Systems and methods to respond to grid overfrequency events for a stoichiometric exhaust recirculation gas turbine.
Allen, Jonathan Kay; Borchert, Bradford David; Trout, Jesse Edwin; Slobodyanskiy, Ilya Aleksandrovich; Valeev, Almaz; Sidko, Igor Petrovich; Subbota, Andrey Pavlovich, Turbine system with exhaust gas recirculation, separation and extraction.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.