公开(公告)号：US09920696B2

公开(公告)日：2018-03-20

申请号：US13555331

申请日：2012-07-23

Applicant: Norbert Walter Emberger ,  Pankaj Bajaj ,  Michael Kenyon ,  Frank Keppler ,  Tobias Christian Amsler ,  Mengbin Zhang ,  Zlatko Pavlic

Inventor： Norbert Walter Emberger ,  Pankaj Bajaj ,  Michael Kenyon ,  Frank Keppler ,  Tobias Christian Amsler ,  Mengbin Zhang ,  Zlatko Pavlic

IPC: F02C9/40 ,  F02C9/34 ,  F02C9/28 ,  F02C9/48 ,  G01N21/3504

CPC classification number: F02C9/40 ,  F02C9/28 ,  F02C9/34 ,  F02C9/48 ,  F05B2270/15 ,  F23R2900/00013 ,  G01N21/3504

Abstract: A method for operating a gas turbine (11) having a compressor (12), a turbine (14) and a combustor (13) with a pilot burner group (15a), a rich premix burner group (15b) and a lean premix burner group (15c), under changing composition of the incoming fuel gas (16), includes the steps of: continuously measuring, in real time, the composition of the fuel gas (16); and controlling the operation of the gas turbine (11) and the combustion of the burners (15a-c) by using the real time fuel gas composition measurements.

公开(公告)号：US09890714B2

公开(公告)日：2018-02-13

申请号：US14610760

申请日：2015-01-30

Applicant: ANSALDO ENERGIA IP UK LIMITED

Inventor： Sumit Soni ,  Nicolas Roger Demougeot ,  Peter John Stuttaford

IPC: F02C9/28 ,  F02C7/228 ,  F02C9/34 ,  F23R3/34

CPC classification number: F02C9/28 ,  F02C7/228 ,  F02C9/34 ,  F05D2260/80 ,  F05D2270/05 ,  F05D2270/082 ,  F05D2270/301 ,  F05D2270/31 ,  F23N2041/20 ,  F23R3/343 ,  F23R3/346 ,  F23R2900/00013

Abstract: An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions. Upon determination that one or more of the conditions exceeds a predetermined upper limit, a fuel flow split to a fuel circuit on all of the combustors on the engine is adjusted by a predetermined amount. The control system continues to monitor the combustion dynamics and to recursively adjust the fuel flow split by the predetermined amount until the combustion dynamics and/or emissions are operating within a prescribed range of the GT engine. Additionally, a method of automated extended turndown of a GT engine to find a minimum load is provided.

公开(公告)号：US20170328284A1

公开(公告)日：2017-11-16

申请号：US15666607

申请日：2017-08-02

Applicant: Siemens Aktiengesellschaft

Inventor： Gavin Brickwood ,  Ghenadie Bulat

IPC: F02C9/28 ,  F23R3/34 ,  F23N5/24

CPC classification number: F02C9/28 ,  F23N5/242 ,  F23N2041/20 ,  F23R3/34 ,  F23R3/343 ,  F23R2900/00013 ,  F23R2900/03281

Abstract: A method of operating a control unit for controlling at least two different input fuel flows to a combustion device, e.g. a gas turbine includes the step of determining on the basis of at least one operating parameter whether the combustion device is in a predefined operating stage. In response hereto, generating a control signal configured for setting a ratio of at least two different input fuel flows to a predetermined value (psc1, psc3) for a predetermined time (dt) in case the combustion device is in the predefined operating stage.

公开(公告)号：US09644846B2

公开(公告)日：2017-05-09

申请号：US14248194

申请日：2014-04-08

Applicant: General Electric Company

Inventor： Christian Xavier Stevenson ,  Sarah Lori Crothers

IPC: F23R3/34 ,  F23M20/00 ,  F23R3/28

CPC classification number: F23R3/34 ,  F05D2260/964 ,  F23M20/005 ,  F23R3/286 ,  F23R2900/00013 ,  F23R2900/03342

Abstract: A gas turbine engine system including a first combustor having a first fuel nozzle and a second combustor having a second fuel nozzle. The system further includes a first acoustic adjuster having a first drive coupled to a first piston with a first fuel orifice. The first piston is disposed along a first fuel passage leading to the first fuel nozzle of the first combustor. The system further includes a second acoustic adjuster having a second drive coupled to a second piston with a second fuel orifice. The second piston is disposed along a second fuel passage leading to the second fuel nozzle of the second combustor.

公开(公告)号：US20170044996A1

公开(公告)日：2017-02-16

申请号：US15306574

申请日：2015-04-17

Applicant: Siemens Aktiengesellschaft

Inventor： Eberhard Deuker ,  Boris Ferdinand Kock ,  Dieter Simon

IPC: F02C9/48

CPC classification number: F02C9/48 ,  F02C9/00 ,  F05D2260/964 ,  F23N5/16 ,  F23R2900/00013

Abstract: A method for operating a burner assembly, in particular a burner assembly of a gas turbine, wherein an evaluation variable representing the combustion stability is determined and at least one control variable is altered, at least based on the determined evaluation variable, when the determined evaluation variable does not fall within a previously defined desired range, the desired range of the evaluation variable being constant over the entire output range of the machine, and wherein the evaluation variable is determined based on measured maximum actual amplitudes in previously defined frequency bands and measured actual outputs of the burner assembly.

Abstract translation: 一种用于操作燃烧器组件，特别是燃气轮机的燃烧器组件的方法，其中确定表示燃烧稳定性的评估变量，并且至少基于所确定的评估变量改变至少一个控制变量，当确定的评估 变量不在先前定义的期望范围内，评估变量的期望范围在机器的整个输出范围内是恒定的，并且其中评估变量基于先前定义的频带中测量的最大实际振幅和测量的实际值 燃烧器组件的输出。

公开(公告)号：US20150345402A1

公开(公告)日：2015-12-03

申请号：US14288875

申请日：2014-05-28

Applicant: General Electric Company

Inventor： Sarah Lori Crothers ,  Joseph Vincent Citeno ,  Christian Xavier Stevenson

IPC: F02C7/24 ,  F23R3/28

CPC classification number: F02C7/24 ,  F01D9/023 ,  F05B2260/96 ,  F05B2260/966 ,  F05D2260/96 ,  F23D2210/00 ,  F23N1/022 ,  F23N5/242 ,  F23R3/28 ,  F23R3/346 ,  F23R2900/00013 ,  F23R2900/00014

Abstract: A system includes a gas turbine engine having a first combustor and a second combustor. The first combustor includes a first fuel conduit having a first plurality of injectors. The first plurality of injectors are disposed in a first configuration within the first combustor along a first fuel path, and the first plurality of injectors are configured to route a fuel to a first combustion chamber. The system further includes a second combustor having a second fuel conduit having a second plurality of injectors. The second plurality of injectors are disposed in a second configuration within the second combustor along a second fuel path, and the second plurality of injectors are configured to route the fuel to a second combustion chamber. The second configuration has at least one difference relative to the first configuration.

Abstract translation: 一种系统包括具有第一燃烧器和第二燃烧器的燃气涡轮发动机。 第一燃烧器包括具有第一多个喷射器的第一燃料管道。 第一组多个喷射器沿着第一燃料路径设置在第一燃烧器内的第一构造中，并且第一多个喷射器构造成将燃料路由到第一燃烧室。 该系统还包括具有第二燃料管道的第二燃烧器，其具有第二多个喷射器。 第二组多个喷射器沿着第二燃料路径设置在第二燃烧器内的第二构造中，并且第二多个喷射器构造成将燃料路由到第二燃烧室。 第二配置相对于第一配置具有至少一个差异。

公开(公告)号：US20150337742A1

公开(公告)日：2015-11-26

申请号：US14814731

申请日：2015-07-31

Applicant: ALSTOM Technology Ltd

Inventor： Stefano BERNERO ,  Frank GRAF ,  Gianfranco Ludovico GUIDATI ,  Martin GASSNER ,  Felix GUETHE

IPC: F02C9/40 ,  F02C7/22 ,  F02C3/22

CPC classification number: F02C3/22 ,  F02C6/18 ,  F02C7/22 ,  F02C9/40 ,  F23L7/007 ,  F23N1/002 ,  F23N2037/08 ,  F23R3/36 ,  F23R2900/00002 ,  F23R2900/00013 ,  Y02E20/16 ,  Y02E20/344

Abstract: A method for operating a gas turbine plant is provided. According to the method a first fuel gas with a first fuel reactivity and a second fuel gas with a second fuel reactivity which is higher than the first fuel reactivity are injected into a combustor of the gas turbine, and the ratio of the mass flows of the second fuel gas to the first fuel gas is controlled depending on the combustion behavior of the combustor. A gas turbine plant configured to carry out the method is further shown.

Abstract translation: 提供了一种操作燃气轮机设备的方法。 根据该方法，将具有第一燃料反应性的第一燃料气体和具有高于第一燃料反应性的第二燃料反应性的第二燃料气体注入到燃气轮机的燃烧器中，并且， 取决于燃烧器的燃烧行为来控制到第一燃料气体的第二燃料气体。 进一步示出了配置为执行该方法的燃气轮机设备。

公开(公告)号：US20150315969A1

公开(公告)日：2015-11-05

申请号：US14268696

申请日：2014-05-02

Applicant: General Electric Company

Inventor： Mark Jason Fisher ,  Douglas Scott Byrd ,  Alberto Jose Negroni ,  Carlos Gabriel Roman

IPC: F02C7/22

CPC classification number: F02C7/222 ,  F05D2260/606 ,  F05D2260/96 ,  F05D2260/964 ,  F23R3/28 ,  F23R2900/00013

Abstract: A fuel supply system includes a main fuel line path configured to route a fuel to a combustion inlet region and a secondary fuel line path fluidly coupled to the main fuel line path. The secondary fuel line path is configured to divert a portion of the fuel from the main fuel line path through a first segment of the secondary fuel line path and return the fuel to the main fuel line path through a second segment of the secondary fuel line path. An obstruction mechanism is located proximate the main fuel line path at an obstruction location and is configured to cyclically translate into the main fuel line path to cyclically alter a cross-sectional area of the main fuel line path to effectively oscillate fuel flow pressure into a combustion system.

Abstract translation: 燃料供给系统包括：主燃料路径路径，其被配置为将燃料路由到燃料入口区域和与主燃料路径路径流体耦合的二次燃料路径路径。 辅助燃料路径路径被配置成使来自主燃料管路路径的燃料的一部分通过二次燃料路径路径的第一段转向，并且通过第二燃料路径路径的第二段将燃料返回到主燃料路径路径 。 阻塞机构位于障碍物位置处的主燃料路径附近，并被构造成循环地平移到主燃料管线路径中以循环地改变主燃料管线路径的横截面面积，以有效地将燃料流动压力摆动到燃烧 系统。

公开(公告)号：US09017064B2

公开(公告)日：2015-04-28

申请号：US12795786

申请日：2010-06-08

Applicant: Samer P. Wasif

Inventor： Samer P. Wasif

IPC: F02C3/30 ,  F23R3/28 ,  F23N1/08 ,  F23N5/16

CPC classification number: F23R3/28 ,  F02C3/30 ,  F23K2301/103 ,  F23L2900/07003 ,  F23N1/082 ,  F23N5/16 ,  F23R2900/00013

Abstract: A method of influencing combustion dynamics, including measuring a combustion dynamics parameter, and controlling a diluent flow (26) delivered to a fuel flow (32) upstream of a pilot burner fuel outlet (40) in response to the measured combustion dynamics parameter.

Abstract translation: 一种影响燃烧动力学的方法，包括测量燃烧动力学参数，以及响应于所测量的燃烧动力学参数，控制在引燃燃烧器燃料出口（40）上方输送到燃料流（32）的稀释剂流（26）。

公开(公告)号：US08919131B2

公开(公告)日：2014-12-30

申请号：US12942687

申请日：2010-11-09

Applicant: Kapil Kumar Singh ,  Fei Han ,  Shiva Srinivasan ,  Kwanwoo Kim ,  Preetham Balasubramanyam ,  Qingguo Zhang

Inventor： Kapil Kumar Singh ,  Fei Han ,  Shiva Srinivasan ,  Kwanwoo Kim ,  Preetham Balasubramanyam ,  Qingguo Zhang

IPC: F02C7/22 ,  F02C7/228 ,  F02C9/50 ,  F23N5/24 ,  F23N5/16

CPC classification number: F02C7/228 ,  F02C9/50 ,  F05D2260/96 ,  F05D2270/14 ,  F23N5/16 ,  F23N5/24 ,  F23R2900/00013 ,  Y02T50/677

Abstract: A combustion dynamics control system for an aviation based or land based gas turbine engine employs an acoustic driver that is configured to drive pressure perturbations across a premixed fuel injection orifice to substantially zero in response to a control signal such that fuel flow perturbations across the fuel injection orifice are substantially zero.

Abstract translation: 用于基于航空或陆基燃气涡轮发动机的燃烧动力学控制系统采用声学驱动器，该声学驱动器被配置为响应于控制信号而将预混合燃料喷射孔的压力扰动驱动到基本上为零，使得燃料流动扰动穿过燃料喷射 孔基本上为零。