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公开(公告)号：US20140196466A1
公开(公告)日：2014-07-17
申请号：US13741797
申请日：2013-01-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Fabien Thibault Codron , John Edward Pritchard , Stanley Kevin Widener
IPC: F02C7/22
Abstract: Methods and systems for operating a gas turbine engine including a fuel delivery system and a plurality of combustor assemblies are provided. The fuel delivery system comprises a primary fuel circuit configured to continuously supply fuel to each of the plurality of combustor assemblies during a first mode of operation and a second mode of operation. At least one secondary fuel circuit of the fuel delivery system is configured to supply fuel to each of the plurality of combustor assemblies during the second mode of operation. The secondary fuel circuit includes at least one isolation valve coupled in flow communication with each of the plurality of combustor assemblies. The at least one isolation valve facilitates preventing fluid flow upstream into the secondary fuel circuit during the first mode of operation. The fuel delivery system, using the isolation valve, replaces a purging system in the gas turbine engine.
Abstract translation: 提供了用于操作包括燃料输送系统和多个燃烧器组件的燃气涡轮发动机的方法和系统。 燃料输送系统包括主燃料回路，其被配置为在第一操作模式和第二操作模式期间向多个燃烧器组件中的每一个连续供应燃料。 燃料输送系统的至少一个次级燃料回路构造成在第二操作模式期间向多个燃烧器组件中的每一个供应燃料。 二次燃料回路包括与多个燃烧器组件中的每一个流体连通地连接的至少一个隔离阀。 所述至少一个隔离阀有助于在第一操作模式期间阻止在二次燃料回路中上游的流体流动。 使用隔离阀的燃料输送系统代替燃气涡轮发动机中的清洗系统。
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公开(公告)号：US09303562B2
公开(公告)日：2016-04-05
申请号：US13741797
申请日：2013-01-15
Applicant: General Electric Company
Inventor： Fabien Thibault Codron , John Edward Pritchard , Stanley Kevin Widener
Abstract: Methods and systems for operating a gas turbine engine including a fuel delivery system and a plurality of combustor assemblies are provided. The fuel delivery system comprises a primary fuel circuit configured to continuously supply fuel to each of the plurality of combustor assemblies during a first mode of operation and a second mode of operation. At least one secondary fuel circuit of the fuel delivery system is configured to supply fuel to each of the plurality of combustor assemblies during the second mode of operation. The secondary fuel circuit includes at least one isolation valve coupled in flow communication with each of the plurality of combustor assemblies. The at least one isolation valve facilitates preventing fluid flow upstream into the secondary fuel circuit during the first mode of operation. The fuel delivery system, using the isolation valve, replaces a purging system in the gas turbine engine.
Abstract translation: 提供了用于操作包括燃料输送系统和多个燃烧器组件的燃气涡轮发动机的方法和系统。 燃料输送系统包括主燃料回路，其被配置为在第一操作模式和第二操作模式期间向多个燃烧器组件中的每一个连续供应燃料。 燃料输送系统的至少一个次级燃料回路构造成在第二操作模式期间向多个燃烧器组件中的每一个供应燃料。 二次燃料回路包括与多个燃烧器组件中的每一个流体连通地连接的至少一个隔离阀。 所述至少一个隔离阀有助于在第一操作模式期间阻止在二次燃料回路中上游的流体流动。 使用隔离阀的燃料输送系统代替燃气涡轮发动机中的清洗系统。
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公开(公告)号：US20160053999A1
公开(公告)日：2016-02-25
申请号：US14464008
申请日：2014-08-20
Applicant: General Electric Company
Abstract: A combustor for a gas turbomachine includes a combustor body, and a combustor liner arranged in the combustor body and defining a combustion chamber extending from a head end to a combustor discharge. The combustor liner is spaced from the combustor body forming a compressor discharge casing (CDC) airflow passage. At least one nozzle is arranged at the head end of the combustor liner. The at least one nozzle includes an outlet configured and disposed to establish a flame zone. At least one recirculation member is arranged at the head end of the combustor liner. The at least one recirculation member is configured and disposed to guide oxygen-depleted combustion products from the flame zone back to the outlet of the at least one nozzle.
Abstract translation: 用于气体涡轮机的燃烧器包括燃烧器主体和布置在燃烧器主体中并限定从头端延伸到燃烧器排放口的燃烧室的燃烧器衬套。 燃烧器衬套与燃烧器主体间隔开，形成压缩机排气壳（CDC）气流通道。 在燃烧器衬套的头端处布置有至少一个喷嘴。 所述至少一个喷嘴包括配置和设置成建立火焰区的出口。 在燃烧器衬套的头端处布置有至少一个再循环构件。 所述至少一个再循环构件被构造和设置成将氧耗尽的燃烧产物从所述火焰区引导回所述至少一个喷嘴的出口。
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