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公开(公告)号：US11566790B1
公开(公告)日：2023-01-31
申请号：US17513066
申请日：2021-10-28
Applicant: General Electric Company
Inventor： Michael John Hughes , Willy Steve Ziminsky
Abstract: A method of operating a combustor of a turbomachine on a total fuel input that contains a concentration of hydrogen that is greater than about 80% is provided. The method includes injecting a first mixture of air and a first fuel containing a first amount of hydrogen into the primary combustion zone of the combustor to generate a first flow of combustion gases having a first temperature. The method further includes injecting, with one or more premix injectors disposed downstream of the fuel nozzles, a second mixture of air and a second fuel containing a second amount of hydrogen into the secondary combustion zone of the combustor to generate a second flow of combustion gases having a second temperature. The method further includes separately injecting a third fuel into secondary combustion zone to generate a third flow of combustion gases having a third temperature.
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公开(公告)号：US20210301722A1
公开(公告)日：2021-09-30
申请号：US16833954
申请日：2020-03-30
Applicant: General Electric Company
Inventor： Willy Steve Ziminsky , Mark William Pinson , Jayaprakash Natarajan , Lucas John Stoia
Abstract: Combustors, gas turbines, and associated methods of operation are provided. A method for operating a combustor includes firing a bundled tube fuel nozzle assembly within a combustion liner of the combustor to generate combustion gases at a first temperature within a first combustion zone length. The method further includes firing a fuel injector downstream from the bundled tube fuel nozzle assembly within the combustion liner of the combustor to generate combustion gases at a second temperature within a second combustion zone length. The first combustion zone length is less than the second combustion zone length. The combustion gases travel through the first combustion zone length in a first time period and through the second combustion zone length in a second time period. The second time period is less than the first time period.
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公开(公告)号：US09546598B2
公开(公告)日：2017-01-17
申请号：US13760090
申请日：2013-02-06
Applicant: General Electric Company
Inventor： Heath Michael Ostebee , Willy Steve Ziminsky , Thomas Edward Johnson , Christopher Paul Keener
Abstract: The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner.
Abstract translation: 本申请提供了一种与燃气涡轮发动机一起使用的可变体积燃烧器。 可变体积燃烧器可以包括衬套，位于衬套内的多个微混合器燃料喷嘴，以及线性致动器，以便沿着衬套轴向地操纵微混合器燃料喷嘴。
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公开(公告)号：US20150000299A1
公开(公告)日：2015-01-01
申请号：US14302028
申请日：2014-06-11
Inventor： Baifang Zuo , Willy Steve Ziminsky , Christian Xavier Stevenson , Ilya Aleksandrovich Slobodyanskiy
CPC classification number: F02C7/222 , F02C3/04 , F02C3/34 , F02C7/22 , F23R3/005 , F23R3/12 , F23R3/28 , F23R3/46 , Y02E20/16 , Y02T50/675
Abstract: A system includes an oxidant compressor and a gas turbine engine turbine, which includes a turbine combustor, a turbine, and an exhaust gas compressor. The turbine combustor includes a plurality of diffusion fuel nozzles, each including a first oxidant conduit configured to inject a first oxidant through a plurality of first oxidant openings configured to impart swirling motion to the first oxidant in a first rotational direction, a first fuel conduit configured to inject a first fuel through a plurality of first fuel openings configured to impart swirling motion to the first fuel in a second rotational direction, and a second oxidant conduit configured to inject a second oxidant through a plurality of second oxidant openings configured to impart swirling motion to the second oxidant in a third rotational direction. The first fuel conduit surrounds the first oxidant conduit and the second oxidant conduit surrounds the first fuel conduit.
Abstract translation: 一种系统包括氧化剂压缩机和燃气涡轮发动机涡轮机，其包括涡轮机燃烧器，涡轮机和排气压缩机。 涡轮机燃烧器包括多个扩散燃料喷嘴，每个扩散燃料喷嘴包括第一氧化剂导管，其构造成通过多个第一氧化剂开口喷射第一氧化剂，所述第一氧化剂开口被配置为在第一旋转方向上向第一氧化剂施加旋动运动，第一燃料导管配置 以通过构造成在第二旋转方向上向第一燃料施加旋动运动的多个第一燃料开口注入第一燃料，以及第二氧化剂导管，其构造成通过构造成施加旋动运动的多个第二氧化剂开口喷射第二氧化剂 在第三旋转方向上与第二氧化剂接触。 第一燃料导管围绕第一氧化剂导管并且第二氧化剂导管围绕第一燃料导管。
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公开(公告)号：US20140216051A1
公开(公告)日：2014-08-07
申请号：US13760101
申请日：2013-02-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Thomas Edward Johnson , Willy Steve Ziminsky , Heath Michael Ostebee , Christopher Paul Keener
IPC: F02C7/22
CPC classification number: F23R3/04 , F23R3/045 , F23R3/286 , F23R2900/00012 , Y02T50/675
Abstract: The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a liner and an air bypass system position about the liner. The air bypass system variably allows a bypass portion of the flow of air to bypass the micro-mixer fuel nozzles.
Abstract translation: 本申请提供了一种用于燃气涡轮发动机中的燃料流和空气流的燃烧器。 燃烧器可以包括位于衬套内的多个微混合器燃料喷嘴和围绕衬套的空气旁路系统位置。 空气旁路系统可变地允许空气流的旁路部分绕过微混合器燃料喷嘴。
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Patent Agency Ranking
公开(公告)号：US12025314B2
公开(公告)日：2024-07-02
申请号：US18147208
申请日：2022-12-28
Applicant: General Electric Company
Inventor： Michael John Hughes , Willy Steve Ziminsky
Abstract: A method of operating a combustor of a turbomachine on a total fuel input that contains a concentration of hydrogen that is greater than about 80% is provided. The method includes injecting a first mixture of air and a first fuel containing a first amount of hydrogen into the primary combustion zone of the combustor to generate a first flow of combustion gases having a first temperature. The method further includes injecting, with one or more premix injectors disposed downstream of the fuel nozzles, a second mixture of air and a second fuel containing a second amount of hydrogen into the secondary combustion zone of the combustor to generate a second flow of combustion gases having a second temperature. The method further includes separately injecting a third fuel into secondary combustion zone to generate a third flow of combustion gases having a third temperature.
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公开(公告)号：US20230136865A1
公开(公告)日：2023-05-04
申请号：US18147208
申请日：2022-12-28
Applicant: General Electric Company
Inventor： Michael John Hughes , Willy Steve Ziminsky
Abstract: A method of operating a combustor of a turbomachine on a total fuel input that contains a concentration of hydrogen that is greater than about 80% is provided. The method includes injecting a first mixture of air and a first fuel containing a first amount of hydrogen into the primary combustion zone of the combustor to generate a first flow of combustion gases having a first temperature. The method further includes injecting, with one or more premix injectors disposed downstream of the fuel nozzles, a second mixture of air and a second fuel containing a second amount of hydrogen into the secondary combustion zone of the combustor to generate a second flow of combustion gases having a second temperature. The method further includes separately injecting a third fuel into secondary combustion zone to generate a third flow of combustion gases having a third temperature.
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8.发明申请公开(公告)号：US20150292744A1
公开(公告)日：2015-10-15
申请号：US14249158
申请日：2014-04-09
Applicant: General Electric Company
Inventor： Willy Steve Ziminsky , Sarah Lori Crothers
IPC: F23R3/42
CPC classification number: F23R3/42 , F02C7/24 , F23R2900/00014
Abstract: The present disclosure generally relates to a system with a gas turbine engine including a first combustor and a second combustor. The first combustor includes a first end cover with a first geometry and the second combustor includes a second end cover with a second geometry. The first geometry has one or more geometric differences relative to the second geometry.
Abstract translation: 本公开总体上涉及具有包括第一燃烧器和第二燃烧器的燃气涡轮发动机的系统。 第一燃烧器包括具有第一几何形状的第一端盖，并且第二燃烧器包括具有第二几何形状的第二端盖。 第一几何具有相对于第二几何形状的一个或多个几何差异。
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公开(公告)号：US09845956B2
公开(公告)日：2017-12-19
申请号：US14249158
申请日：2014-04-09
Applicant: General Electric Company
Inventor： Willy Steve Ziminsky , Sarah Lori Crothers
CPC classification number: F23R3/42 , F02C7/24 , F23R2900/00014
Abstract: The present disclosure generally relates to a system with a gas turbine engine including a first combustor and a second combustor. The first combustor includes a first end cover with a first geometry and the second combustor includes a second end cover with a second geometry. The first geometry has one or more geometric differences relative to the second geometry.
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公开(公告)号：US09562687B2
公开(公告)日：2017-02-07
申请号：US13760101
申请日：2013-02-06
Applicant: General Electric Company
Inventor： Thomas Edward Johnson , Willy Steve Ziminsky , Heath Michael Ostebee , Christopher Paul Keener
CPC classification number: F23R3/04 , F23R3/045 , F23R3/286 , F23R2900/00012 , Y02T50/675
Abstract: The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a liner and an air bypass system position about the liner. The air bypass system variably allows a bypass portion of the flow of air to bypass the micro-mixer fuel nozzles.
Abstract translation: 本申请提供了一种用于燃气涡轮发动机中的燃料流和空气流的燃烧器。 燃烧器可以包括位于衬套内的多个微混合器燃料喷嘴和围绕衬套的空气旁路系统位置。 空气旁路系统可变地允许空气流的旁路部分绕过微混合器燃料喷嘴。
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