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公开(公告)号：US20170138600A1
公开(公告)日：2017-05-18
申请号：US15221747
申请日：2016-07-28
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , Kara Johnston Edwards
CPC classification number: F23R3/286 , F02C7/222 , F05D2220/32 , F23R3/343 , F23R2900/03343
Abstract: An apparatus for injecting premixed fuel and air through a center body and into the combustion zone of a gas turbine includes a fuel injector nozzle with a premix pilot nozzle having a plurality of premix passages in fluid communication with an air supply and a fuel supply that premixes air and fuel within the premix passages. The apparatus has either an active or passive fuel feed control. Fuel can be fed to the apparatus either conventionally or as a breech load circuit integrated into the oil cartridge. Fuel can be supplied passively via a fuel channel connecting the swozzle fuel plenum to the premix passages. Alternatively, fuel can be injected from the oil cartridge into the premix passages.
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公开(公告)号：US20170138267A1
公开(公告)日：2017-05-18
申请号：US14944298
申请日：2015-11-18
Applicant: General Electric Company
Inventor： Michael John Hughes , Stanley Kevin Widener , Jonathan Dwight Berry
CPC classification number: F02C7/222 , F02C7/22 , F05D2220/32 , F05D2240/35 , F23D14/62 , F23D14/64 , F23R3/04 , F23R3/045 , F23R3/10 , F23R3/12 , F23R3/14 , F23R3/28 , F23R3/286 , F23R3/32 , F23R3/36
Abstract: A bundled tube fuel nozzle assembly includes a fuel injector and a tube bundle comprising a plurality of tubes that provide for fluid communication through a forward plate, a fuel plenum and an aft plate of the bundled tube fuel nozzle assembly. Each tube includes an inlet defined at an upstream end of the tube and an outlet defined at a downstream end of the tube. The fuel injector is disposed upstream from the inlets of each of the tubes. The upstream end of each tube is noncircular and includes at least one side portion that abuts a complementary upstream end side portion of an immediately adjacent tube of the plurality of tubes. The downstream end of each tube may be circular and is spaced apart from the downstream ends of immediately adjacent tubes of the plurality of tubes.
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公开(公告)号：US09353950B2
公开(公告)日：2016-05-31
申请号：US13709320
申请日：2012-12-10
Applicant: General Electric Company
Inventor： Jong Ho Uhm , Willy Steve Ziminsky , Thomas Edward Johnson , Michael John Hughes , William David York
CPC classification number: F23R3/286 , F23D14/46 , F23D14/58 , F23D14/62 , F23R3/10 , F23R2900/00014
Abstract: A combustor includes an end cap that extends radially across at least a portion of the combustor. The end cap includes an upstream surface axially separated from a downstream surface. A plurality of tubes extend from the upstream surface through the downstream surface of the end cap to provide fluid communication through the end cap. Each tube in a first set of the plurality of tubes has an inlet proximate to the upstream surface and an outlet downstream from the downstream surface. Each outlet has a first portion that extends a different axial distance from the inlet than a second portion.
Abstract translation: 燃烧器包括沿着燃烧器的至少一部分径向延伸的端盖。 端盖包括从下游表面轴向分离的上游表面。 多个管从上游表面延伸通过端盖的下游表面以提供通过端盖的流体连通。 多个管的第一组中的每个管具有靠近上游表面的入口和从下游表面下游的出口。 每个出口具有第一部分，该第一部分与第二部分相比延伸与入口不同的轴向距离。
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公开(公告)号：US20150159875A1
公开(公告)日：2015-06-11
申请号：US14102846
申请日：2013-12-11
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , Kara Johnston Edwards
IPC: F23R3/28
CPC classification number: F23R3/286 , F02C7/222 , F05D2220/32 , F23R3/343 , F23R2900/03343
Abstract: An apparatus for injecting premixed fuel and air through a center body and into the combustion zone of a gas turbine includes a fuel injector nozzle with a premix pilot nozzle having a plurality of premix passages in fluid communication with an air supply and a fuel supply that premixes air and fuel within the premix passages. The apparatus has either an active or passive fuel feed control. Fuel can be fed to the apparatus either conventionally or as a breech load circuit integrated into the oil cartridge. Fuel can be supplied passively via a fuel channel connecting the swozzle fuel plenum to the premix passages. Alternatively, fuel can be injected from the oil cartridge into the premix passages.
Abstract translation: 用于将预混合燃料和空气通过中心体注入燃气轮机的燃烧区域的装置包括具有预混合引燃喷嘴的燃料喷射器喷嘴，该预混合引燃喷嘴具有与空气源流体连通的多个预混合通道和预混合燃料 空气和燃料在预混通道内。 该装置具有主动或被动燃料供给控制。 燃料可以传统地或作为集成到油盒中的后膛负载回路供给到设备。 可以通过将喷嘴燃料增压室连接到预混通道的燃料通道被动地供给燃料。 或者，可以将燃料从油盒注入预混通道。
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公开(公告)号：US12222106B2
公开(公告)日：2025-02-11
申请号：US17708860
申请日：2022-03-30
Applicant: General Electric Company
Inventor： Hatem M. Selim , Baha Suleiman , Majed Sammak , Michael John Hughes , Abdurrahman Abdallah Khalidi , Alaaeldin Elsaeed Dawood
Abstract: A method includes delivering fuel and a first portion of oxidant as a rich mixture to the first zone of the combustion chamber. The fuel includes ammonia (NH3). The method further includes burning the rich mixture in the first zone. Combustion gases containing nitrogen oxides (NOx) are produced. The method further includes delivering a second portion of oxidant into the second zone to break down unburned ammonia into ammonia intermediates in the second zone. The nitrogen oxides (NOx) are consumed by reacting with the ammonia intermediates in the second zone. Byproduct hydrogen is produced as a result of breaking down the unburned ammonia into the ammonia intermediates. The method further includes delivering a third portion of oxidant into the third zone. The byproduct hydrogen is burned in the third zone. The third portion of oxidant is greater than the first portion of oxidant and the second portion of oxidant.
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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：US20230313995A1
公开(公告)日：2023-10-05
申请号：US17708860
申请日：2022-03-30
Applicant: General Electric Company
Inventor： Hatem M. Selim , Baha Suleiman , Majed Sammak , Michael John Hughes , Abdurrahman Abdallah Khalidi , Alaaeldin Elsaeed Dawood
CPC classification number: F23R3/346 , F23R3/36 , F02C3/30 , F02C3/22 , F23R2900/00004 , F05D2240/35
Abstract: A method includes delivering fuel and a first portion of oxidant as a rich mixture to the first zone of the combustion chamber. The fuel includes ammonia (NH3). The method further includes burning the rich mixture in the first zone. Combustion gases containing nitrogen oxides (NOx) are produced. The method further includes delivering a second portion of oxidant into the second zone to break down unburned ammonia into ammonia intermediates in the second zone. The nitrogen oxides (NOx) are consumed by reacting with the ammonia intermediates in the second zone. Byproduct hydrogen is produced as a result of breaking down the unburned ammonia into the ammonia intermediates. The method further includes delivering a third portion of oxidant into the third zone. The byproduct hydrogen is burned in the third zone. The third portion of oxidant is greater than the first portion of oxidant and the second portion of oxidant.
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公开(公告)号：US20230296253A1
公开(公告)日：2023-09-21
申请号：US17697285
申请日：2022-03-17
Applicant: General Electric Company
Inventor： Carlos Miranda , Michael John Hughes
CPC classification number: F23R3/346 , F23R3/286 , F02C7/222 , F02C7/224 , F05D2220/72 , F05D2240/35 , F05D2260/213
Abstract: A gas turbine combustion system includes a combustor that has at least two injection stages each configured to inject fuel into a combustion chamber of the combustor. A fuel supply circuit is in fluid communication with the at least two injection stages for providing the fuel from a fuel supply to the injection stages. The fuel supply circuit includes at least two branches, each branch being fluidly coupled to a respective injection stage. The gas turbine combustion system further includes at least two heat exchangers fluidly coupled to a thermal fluid supply. Each heat exchanger is disposed in thermal communication on a respective branch of the at least two branches for modifying a temperature of fuel within the respective branch.
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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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公开(公告)号：US11371702B2
公开(公告)日：2022-06-28
申请号：US17007068
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The integrated combustor nozzle further includes an impingement panel having an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment. The impingement plate defines a plurality of impingement holes that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel is radially spaced from the exterior surface to form a cooling flow gap therebetween. The impingement panel includes a collection duct that extends from the impingement panel and defines a collection passage.
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