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公开(公告)号：US20170356342A1
公开(公告)日：2017-12-14
申请号：US15182003
申请日：2016-06-14
Applicant: General Electric Company
Inventor： David Leach , Daniel R. Tegel , Alston Ilford Scipio , Praveen Kumar Uppaluri , Vishwanath R. Ardha , Sanji Ekanayake
Abstract: A gas turbine fuel heating system is disclosed having at least one coalescing filter configured to accept a main fuel supply and a plurality of fuel circuit heaters. Each fuel circuit heater can be configured to accept an independent fuel circuit portion of the main fuel supply leaving the at least one coalescing filter and also configured to accept a heating medium circuit portion of a heating medium. The system can have a plurality of scrubbers, a plurality of fuel circuit manifolds, and a plurality of fuel premix tubes. A controller circuit determines the MWI for each independent fuel circuit portion and adjusts the heating medium circuit portion passed to the corresponding fuel circuit heater to maintain at least one parameter selected from the group consisting of a baseline independent fuel circuit portion MWI setpoint and a predetermined independent fuel circuit portion nozzle gas injector pressure ratio.
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公开(公告)号：US09303564B2
公开(公告)日：2016-04-05
申请号：US13778164
申请日：2013-02-27
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sarah Lori Crothers , Christan Xavier Stevenson , David Leach
CPC classification number: F02C7/24 , F02C7/222 , F02C7/224 , F02C7/228 , F05D2260/96
Abstract: The present application provides a fuel delivery system for a combustor with reduced coherence and/or reduced combustion dynamics. The combustor can assembly may include a first manifold for delivering a first flow of fuel to a first set of fuel injectors and a second manifold for delivering a second flow of fuel to a second set of fuel injectors. The first flow of fuel may have a first temperature and the second flow of fuel may have a second temperature. The first temperature may be higher than the second temperature.
Abstract translation: 本申请提供了一种具有减小的相干性和/或降低的燃烧动力学的燃烧器的燃料输送系统。 燃烧器组件可以包括用于将第一燃料流输送到第一组燃料喷射器的第一歧管和用于将第二燃料流输送到第二组燃料喷射器的第二歧管。 第一燃料流可以具有第一温度，并且第二燃料流可以具有第二温度。 第一温度可以高于第二温度。
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公开(公告)号：US20150121887A1
公开(公告)日：2015-05-07
申请号：US14071127
申请日：2013-11-04
Applicant: General Electric Company
Inventor： Chi Ming Ho , Skigh Elliot Lewis , Priscilla Graves Childers , David Leach
IPC: F02C9/32
CPC classification number: F02C9/32 , F05D2270/03 , F05D2270/3061
Abstract: A method of controlling operability of a gas turbine during part-speed operation includes identifying that a combustion system of the gas turbine is operating at part-speed, the combustion system including a fuel source, fuel circuits and valves operably interposed between the fuel source and the fuel circuits, respectively, defining first and second boundaries based on first and second parameters and automatically controlling each of the valves to control fuel flow to each of the fuel circuits in accordance with the defined first and second boundaries.
Abstract translation: 一种在部分速度操作期间控制燃气轮机的可操作性的方法包括识别燃气轮机的燃烧系统以部分速度操作，所述燃烧系统包括燃料源，燃料回路和阀，其可操作地插入燃料源和 燃料电路分别基于第一和第二参数限定第一和第二边界，并且根据限定的第一和第二边界自动控制每个阀以控制到每个燃料回路的燃料流。
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公开(公告)号：US09771869B2
公开(公告)日：2017-09-26
申请号：US14154692
申请日：2014-01-14
Applicant: General Electric Company
Inventor： Suhui Li , Joel Meier Haynes , Ping Yu , Wei Chen , David Leach , John Joseph Lipinski , Manuel Moises Cardenas, Jr. , Wenjie Wu , Qingguo Zhang
Abstract: A fuel nozzle system for enabling a gas turbine to start and operate on low-Btu fuel includes a primary tip having primary fuel orifices and a primary fuel passage in fluid communication with the primary fuel orifices, and a fuel circuit capable of controlling flow rates of a first and second low-Btu fuel gases flowing into the fuel nozzle. The system is capable of operating at an ignition status, in which at least the first low-Btu fuel gas is fed to the primary fuel orifices and ignited to start the gas turbine, and a baseload status, in which at least the second low-Btu fuel gas is fired at baseload. The low-Btu fuel gas ignited at the ignition status has a content of the first low-Btu fuel gas higher than that of the low-Btu fuel gas fired at the baseload status. Methods for using the system are also provided.
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公开(公告)号：US09441835B2
公开(公告)日：2016-09-13
申请号：US13647359
申请日：2012-10-08
Applicant: General Electric Company
Inventor： Brandon Taylor Overby , David Leach
CPC classification number: F23R3/02 , F23L7/00 , F23L2900/07002 , F23L2900/07009 , F23R3/286 , F23R3/36
Abstract: A system includes a gas turbine combustor configured to combust a fuel and an oxidant, such as O2 and O2 mixtures. The system also includes an aerodynamic peg disposed in the gas turbine combustor. The aerodynamic peg includes a first passage configured to convey a first fluid into the gas turbine combustor and a second passage configured to convey a second fluid into the gas turbine combustor. The first fluid and second fluid are different from one another.
Abstract translation: 一种系统包括配置成燃烧燃料和氧化剂如O2和O2混合物的燃气轮机燃烧器。 该系统还包括设置在燃气轮机燃烧器中的空气动力学栓塞。 空气动力学栓塞包括构造成将第一流体输送到燃气涡轮机燃烧器中的第一通道和被构造成将第二流体输送到燃气涡轮机燃烧器中的第二通道。 第一流体和第二流体彼此不同。
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Patent Agency Ranking
公开(公告)号：US20140123652A1
公开(公告)日：2014-05-08
申请号：US14081062
申请日：2013-11-15
Applicant: General Electric Company
Inventor： Jesse Blair Butler , David Leach , Kevin Weston McMahan , Mark Allan Hadley , Geoffrey David Myers
CPC classification number: F23R3/286 , F23C2900/07001 , F23D2900/14004 , F23D2900/14701 , F23R3/14
Abstract: A gas turbine includes a compressor and at least one combustor downstream from the compressor. The combustor includes a burner having an inner shroud extending axially along at least a portion of the burner, an outer shroud radially separated from the inner shroud and extending axially along at least a portion of the burner, and a plurality of stator vanes extending radially between the inner shroud and the outer shroud. The stator vanes have an inner end proximate the inner shroud and an outer end proximate the outer shroud. The burner further includes a vortex tip at one of either the inner end or the outer end of the stator vanes. The vortex tip provides a gap between the inner end and the inner shroud or the outer end and the outer shroud, and the vortex tip includes a plurality of fuel ports. The gas turbine further includes a turbine downstream from the combustor.
Abstract translation: 燃气轮机包括压缩机和至少一个在压缩机下游的燃烧器。 所述燃烧器包括燃烧器，所述燃烧器具有沿所述燃烧器的至少一部分轴向延伸的内罩，所述外护罩与所述内护罩径向分离并且沿着所述燃烧器的至少一部分轴向延伸;以及多个定子叶片， 内护罩和外护罩。 定子叶片具有靠近内护罩的内端和靠近外护罩的外端。 燃烧器还包括在定子叶片的内端或外端之一处的涡流尖端。 涡流尖端在内端和内护罩或外端和外护罩之间提供间隙，并且涡流尖端包括多个燃料口。 燃气轮机还包括从燃烧器下游的涡轮机。
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公开(公告)号：US11893525B2
公开(公告)日：2024-02-06
申请号：US17243876
申请日：2021-04-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ilya Alexandrovich Slobodyanskiy , David Leach , Berardino Pezzella
IPC: G06Q10/06 , G06Q10/0631 , G05B13/04 , G06Q10/20 , G06Q30/018 , G06Q40/02 , G06Q50/06 , G06F3/04847
CPC classification number: G06Q10/06313 , G05B13/042 , G06Q10/20 , G06Q30/018 , G06Q40/02 , G06Q50/06 , G06F3/04847
Abstract: A dispatch advisor to assist in selecting operating conditions of a power plant that maximizes operational revenue is described. The dispatch advisor obtains a base load map for operating the power plant to meet base load power demands. The base load map includes a primary base load operating space for attaining target plant power output and efficiency, and an expanded base load portion for attaining higher plant power output and less than optimal efficiency. Both the primary base load operating space and the expanded base load portion associate power output and efficiency values of the power plant that result from a subset of operational parameter values for operating the power plant during base load. The dispatch advisor can transform the flexible base load map into one or more visualizations describing the revenue possibilities associated with operating the power plant based on operating values and attained power output and efficiency.
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公开(公告)号：US11203986B1
公开(公告)日：2021-12-21
申请号：US16895619
申请日：2020-06-08
Applicant: General Electric Company
Inventor： David Leach , Valerie Suzanne Vernet , Jason Nathaniel Cook , Jayaprakash Natarajan
Abstract: A method of operating a rotary machine below a minimum emissions compliance load in a response mode includes reducing a fuel split to zero. The fuel split apportions a total flow of fuel to the combustor between a first combustion zone and a second combustion zone. The method also includes determining a current operating temperature of the first combustion zone using a digital simulation of the rotary machine. The method further includes determining a target operating temperature of the first combustion zone. The target operating temperature enables the rotary machine to operate below a traditional Minimum Emissions Compliance Load (MECL) while still in compliance with emissions standards. The method also includes channeling a first flow of fuel to the first combustion zone. The first flow of fuel decreases the temperature of the first combustion zone to the target operating temperature.
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公开(公告)号：US09360221B2
公开(公告)日：2016-06-07
申请号：US14081062
申请日：2013-11-15
Applicant: General Electric Company
Inventor： Jesse Blair Butler , David Leach , Kevin Weston McMahan , Mark Allan Hadley , Geoffrey David Myers
CPC classification number: F23R3/286 , F23C2900/07001 , F23D2900/14004 , F23D2900/14701 , F23R3/14
Abstract: A gas turbine includes a compressor and at least one combustor downstream from the compressor. The combustor includes a burner having an inner shroud extending axially along at least a portion of the burner, an outer shroud radially separated from the inner shroud and extending axially along at least a portion of the burner, and a plurality of stator vanes extending radially between the inner shroud and the outer shroud. The stator vanes have an inner end proximate the inner shroud and an outer end proximate the outer shroud. The burner further includes a vortex tip at one of either the inner end or the outer end of the stator vanes. The vortex tip provides a gap between the inner end and the inner shroud or the outer end and the outer shroud, and the vortex tip includes a plurality of fuel ports. The gas turbine further includes a turbine downstream from the combustor.
Abstract translation: 燃气轮机包括压缩机和至少一个在压缩机下游的燃烧器。 所述燃烧器包括燃烧器，所述燃烧器具有沿所述燃烧器的至少一部分轴向延伸的内罩，所述外护罩与所述内护罩径向分离并且沿着所述燃烧器的至少一部分轴向延伸;以及多个定子叶片， 内护罩和外护罩。 定子叶片具有靠近内护罩的内端和靠近外护罩的外端。 燃烧器还包括在定子叶片的内端或外端之一处的涡流尖端。 涡流尖端在内端和内护罩或外端和外护罩之间提供间隙，并且涡流尖端包括多个燃料口。 燃气轮机还包括从燃烧器下游的涡轮机。
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公开(公告)号：US12158114B2
公开(公告)日：2024-12-03
申请号：US17243758
申请日：2021-04-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ilya Alexandrovich Slobodyanskiy , David Leach , Berardino Pezzella
Abstract: A dispatch advisor for operating a power plant having at least one gas turbine with flexibility is described. The dispatch advisor can generate a representation of a flexible base load map for operating the power plant. The representation can include an aggregation of a primary base load operating space and an expanded portion of the base load operating space. The representation offers a range of operating values for operational parameters of the power plant during base load at various base load settings at predetermined ambient conditions and corresponding power output and efficiency values that are attained while operating the power plant at the range of operating values. This offers an operator of the power plant with flexibility in controlling the plant during base load.
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