公开(公告)号：US20190154263A1

公开(公告)日：2019-05-23

申请号：US15817861

申请日：2017-11-20

Applicant: Mirko Ruben BOTHIEN ,  Douglas PENNELL ,  Peter STUTTAFORD

Inventor： Mirko Ruben BOTHIEN ,  Douglas PENNELL ,  Peter STUTTAFORD

IPC: F23R3/34 ,  F02C9/26 ,  F02C7/228 ,  F23R3/28

Abstract: A method is disclosed for controlling fuel injection in a reheat combustor of a gas turbine combustor assembly including a combustor casing defining a gas flow channel and a plurality of injection nozzles distributed in or around the gas flow channel; the method includes the step of distributing fuel among the injection nozzles according to a non-uniform distribution pattern.

公开(公告)号：US08091363B2

公开(公告)日：2012-01-10

申请号：US11998769

申请日：2007-11-29

Applicant: Daniel J. Sullivan ,  Peter Stuttaford ,  Robert J. Kraft ,  Khalid Oumejjoud ,  Yan Chen

Inventor： Daniel J. Sullivan ,  Peter Stuttaford ,  Robert J. Kraft ,  Khalid Oumejjoud ,  Yan Chen

IPC: F02C1/00 ,  B05B7/10

CPC classification number: F23R3/286 ,  F23R3/14

Abstract: Embodiments for an apparatus and associated method for reducing the residence time in a gas turbine combustor are disclosed. The embodiments of the present invention comprise a fuel nozzle that extends to a downstream plane of an end cap for a combustion liner where the axial distance of the premixer is reduced, however the swirl for mixing the fuel and air, is increased. As a result, the mixing of the fuel and air is essentially unchanged, thereby allowing higher air pressures and operating temperatures within the premixer without inducing auto-ignition.

Abstract translation: 公开了用于减少在燃气轮机燃烧器中的停留时间的设备和相关方法的实施例。 本发明的实施例包括燃料喷嘴，其延伸到用于燃烧衬套的端盖的下游平面，其中预混合器的轴向距离减小，然而用于混合燃料和空气的涡流增加。 结果，燃料和空气的混合基本上没有变化，从而允许在预混合器内更高的空气压力和操作温度而不引起自动点火。

公开(公告)号：US07677025B2

公开(公告)日：2010-03-16

申请号：US10906057

申请日：2005-02-01

Applicant: Peter Stuttaford ,  Stephen Jennings

Inventor： Peter Stuttaford ,  Stephen Jennings

IPC: F02C3/00

CPC classification number: F23R3/343 ,  F02C7/22 ,  F05D2260/60 ,  F23D2209/30

Abstract: A gas turbine combustor having a self-purging pilot fuel injection system and method of operation thereof is disclosed. The pilot fuel injection system comprises a radial inflow swirler, a generally axially extending centerbody, and at least one fuel injection source. In operation a fluid containing at least air passes along the centerbody outer surface clearing any remaining fuel from proximate the fuel injection source so as to prevent flame attachment proximate the fuel injection source.

Abstract translation: 公开了一种具有自净化引燃燃料喷射系统及其操作方法的燃气轮机燃烧器。 引燃燃料喷射系统包括径向流入旋流器，大致轴向延伸的中心体和至少一个燃料喷射源。 在操作中，至少含有空气的流体沿着中心体外表面通过，从燃料喷射源的附近清除任何剩余的燃料，以便防止燃料喷射源附近的火焰附着。

公开(公告)号：US07624564B2

公开(公告)日：2009-12-01

申请号：US10897785

申请日：2004-07-23

Applicant: Peter Stuttaford ,  Jon Glende ,  Peter So ,  Lee Rosen ,  Khalid Oumejjoud

Inventor： Peter Stuttaford ,  Jon Glende ,  Peter So ,  Lee Rosen ,  Khalid Oumejjoud

IPC: F02C3/22

CPC classification number: F02C9/40 ,  F02C7/22 ,  F02C7/228

Abstract: A fuel supply system and method thereof that utilizes an off-gas in addition to the primary fuel to lower the emissions of a gas turbine combustion system is disclosed. The fuel supply system apparatus comprises a fuel gas supply conduit and an off-gas supply conduit in fluid communication with the fuel gas supply conduit such that the flow of an off-gas to the fuel gas supply conduit can be regulated as required by the operator to the desired fuel nozzle(s). The fuel gas supply preferably operates with natural gas and the off-gas supply preferably comprises the constituents hydrogen and methane.

Abstract translation: 公开了一种燃料供应系统及其方法，其利用除主燃料之外的废气以降低燃气轮机燃烧系统的排放。 燃料供应系统设备包括燃料气体供应管道和与燃料气体供应管道流体连通的废气供应管道，使得可以根据操作者的要求调节到燃料气体供应管道的废气流量 到所需的燃料喷嘴。 燃料气体供应优选用天然气进行操作，废气供应优选地包括氢和甲烷的组分。

公开(公告)号：US07137256B1

公开(公告)日：2006-11-21

申请号：US10906631

申请日：2005-02-28

Applicant: Peter Stuttaford ,  Nuria Margarit-Bel ,  Yan Chen ,  Khalid Oumejjoud ,  Stephen Jennings

Inventor： Peter Stuttaford ,  Nuria Margarit-Bel ,  Yan Chen ,  Khalid Oumejjoud ,  Stephen Jennings

IPC: F02C9/00

CPC classification number: F02C7/228 ,  F23R3/343

Abstract: A method of operating a gas turbine engine combustion system at lower load conditions while maintaining required emissions levels is disclosed. The present invention includes multiple embodiments of axial, radial, and circumferential fuel staging within a can-type combustor having alternate ignition techniques of spark ignition or torch ignition.

Abstract translation: 公开了一种在维持所需排放水平的同时在较低负载条件下操作燃气涡轮发动机燃烧系统的方法。 本发明包括在具有火花点火或火炬点火的交替点火技术的罐型燃烧器内的轴向，径向和周向燃料分级的多个实施例。

公开(公告)号：US06898937B2

公开(公告)日：2005-05-31

申请号：US10452449

申请日：2003-06-02

Applicant: Peter Stuttaford ,  Stephen T. Jennings ,  Ryan McMahon ,  Hany Rizkalla ,  Alfredo Cires

Inventor： Peter Stuttaford ,  Stephen T. Jennings ,  Ryan McMahon ,  Hany Rizkalla ,  Alfredo Cires

IPC: F23R3/28 ,  F02C7/22

CPC classification number: F23R3/286 ,  F23D2214/00 ,  F23D2900/00008 ,  F23D2900/14004

Abstract: A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly. An alternate embodiment includes an additional fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly. A second alternate embodiment is disclosed which reconfigures the injector assembly and fuel injection locations to minimize flow blockage issues at the injector assembly.

Abstract translation: 公开了一种用于燃气轮机燃烧器中的预混燃料喷嘴和操作方法。 预混合燃料喷嘴利用包括多个径向延伸的翅片的翅片组件，用于喷射燃料和压缩空气，以提供更均匀的喷射模式。 燃料和压缩空气在燃烧室的上游混合并作为均匀的混合物流入燃烧室。 预混合燃料喷嘴包括多个同轴通道，其向燃料组件提供燃料和压缩空气，以及压缩空气以冷却喷嘴盖组件。 替代实施例包括沿着预混合燃料喷嘴的锥形锥形部分位于鳍片组件下游的附加燃料喷射区域。 公开了第二替代实施例，其重新配置喷射器组件和燃料喷射位置以最小化喷射器组件处的流动阻塞问题。

公开(公告)号：US06722132B2

公开(公告)日：2004-04-20

申请号：US10195823

申请日：2002-07-15

Applicant: Peter Stuttaford ,  Stephen T. Jennings ,  Ryan McMahon ,  Brian R. Mack

Inventor： Peter Stuttaford ,  Stephen T. Jennings ,  Ryan McMahon ,  Brian R. Mack

IPC: F02G100

CPC classification number: F23L7/002 ,  F23D2209/30 ,  F23D2214/00 ,  F23D2900/00008 ,  F23D2900/14004 ,  F23R3/286 ,  F23R3/36

Abstract: A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform injection pattern and homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber. An alternate embodiment includes an additional gas fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly.

Abstract translation: 公开了一种用于燃气轮机燃烧器的双燃料预混喷嘴和操作方法。 双燃料预混喷嘴利用一种翅片组件，其包括多个径向延伸的翅片，用于喷射气体燃料和压缩空气，以便提供更均匀的注射模式和均匀的混合物。 预混合燃料喷嘴包括多个同轴通道，其向翅片组件提供气体燃料和压缩空气。 当处于液体燃料运行时，气体回路用压缩空气吹扫，液体燃料和水通过同轴通道到达双燃料预混燃料喷嘴的末端，在那里它们将液体燃料和水注入到二次燃烧室中。 替代实施例包括沿着预混合燃料喷嘴的锥形锥形部分位于鳍片组件下游的附加气体燃料喷射区域。

公开(公告)号：US06530222B2

公开(公告)日：2003-03-11

申请号：US09903638

申请日：2001-07-13

Applicant: Peter Stuttaford ,  Aleksandar Kojovic

Inventor： Peter Stuttaford ,  Aleksandar Kojovic

IPC: F02C100

CPC classification number: F23R3/286 ,  F23D14/64 ,  F23R2900/03044

Abstract: A swirled diffusion dump combustor of the present invention includes a cylindrical combustor can and a fuel and air mixer attached to the upstream end of the combustor can. The mixer is generally formed by an annular chamber which is defined between annular outer and inner walls, having an annularly continuous truncated conical crass-section. The upstream end of the annular chamber is closed by a manifold ring which includes an annular fuel passage and two rows of swirled air passages. Thus, the compressor air approaching the mixer from above enters the swirled air passages, and the swirled air flow in the annular chamber shears fuel from the lips of the annular fuel passage to produce a fuel/air mixture. The mixture swirl is accelerated in the annular chamber and passes a downstream annular passage which serves as the region of diffusive mixing, and also as a flame flashback restrictor. The flow then dumps into the combustor can, providing the final level of mixing, where it then burns. The burning fuel/air mixture is stabilized by the swirling flow from the swirled air passages, as well as by the pressure gradient induced re-circulation to the upstream end of the combustor can. The front face of the combustor can is cooled by compressor air flowing through a series of effusion holes and the cylindrical side wall of the combustor can is cooled by air flow through an impingement cooling skin.

Abstract translation: 本发明的涡流扩散倾倒式燃烧器包括一个圆柱形燃烧器罐和一个连接到燃烧器罐的上游端的燃料和空气混合器。 混合器通常由环形室形成，该环形室限定在环形外壁和内壁之间，具有环形连续的截头圆锥形截面。 环形室的上游端由歧管环封闭，歧管环包括环形燃料通道和两排旋转的空气通道。 因此，从上方接近混合器的压缩机空气进入漩涡的空气通道，并且环形室中的旋转的空气流从环形燃料通道的唇缘剪切燃料以产生燃料/空气混合物。 混合物漩涡在环形室中加速并通过用作扩散混合区域的下游环形通道，并且还作为火焰回流限制器。 然后，流动将进入燃烧器罐，提供最终的混合水平，然后在那里燃烧。 燃烧的燃料/空气混合物通过来自涡旋空气通道的旋转流以及压力梯度引起的再循环稳定到燃烧室的上游端。 燃烧器壳体的前表面可以通过流过一系列渗出孔的压缩机空气来冷却，燃烧室的圆柱形侧壁可以通过冲击冷却皮肤的空气流进行冷却。

公开(公告)号：US08997499B2

公开(公告)日：2015-04-07

申请号：US12686933

申请日：2010-01-13

Applicant: Nicolas Demougeot ,  Jon Glende ,  Peter Stuttaford

Inventor： Nicolas Demougeot ,  Jon Glende ,  Peter Stuttaford

IPC: F02C7/22 ,  F02C9/00 ,  G05D3/12 ,  F02C9/46 ,  F02C7/262 ,  F02C9/34

CPC classification number: F02C9/46 ,  F02C7/262 ,  F02C9/34

Abstract: A system and way for controlling a gas turbine engine in the event of a partial or full load rejection from a generator is disclosed. Upon detection of a partial or full load rejection, the fuel flow of the combustor is directed to a secondary circuit of a secondary fuel nozzle to maintain a flame in a downstream chamber of the combustor. By maintaining the flame in the downstream chamber while the engine speed is controlled, the recovery process to a load condition avoids use of spark ignition system and flame detectors in the upstream chamber.

Abstract translation: 公开了在发电机发生部分或全部负载的情况下控制燃气涡轮发动机的系统和方法。 在检测到部分或全部负载排斥时，燃烧器的燃料流动被引导到次级燃料喷嘴的次级回路，以在燃烧器的下游腔室中保持火焰。 通过在控制发动机转速的同时维​​持下游室中的火焰，恢复到负载状态的过程避免了在上游室中使用火花点火系统和火焰探测器。

公开(公告)号：US08566001B2

公开(公告)日：2013-10-22

申请号：US13087048

申请日：2011-04-14

Applicant: Peter Stuttaford ,  Nicolas Demougeot ,  Melvin Swann

Inventor： Peter Stuttaford ,  Nicolas Demougeot ,  Melvin Swann

IPC: F02C3/00 ,  G06F19/00

CPC classification number: F02C7/1435 ,  F02C7/22 ,  F02C7/228 ,  F02C9/28 ,  F05D2270/083 ,  F05D2270/16 ,  F05D2270/708

Abstract: Methods for controlling a gas turbine engine are provided, where a compressor inlet temperature, ambient temperature, and relative humidity are measured. Utilizing these measurements, it is first determined whether an evaporation cooler is actively importing water content into inlet air entering the compressor. This determination is based on whether the inlet air is substantially cooler than the ambient temperature. If so, an EC correction factor is added to an inlet air temperature value (CTIM) and set as an air temperature parameter (INLETIM). Second, it is determined whether the relative humidity is greater than a predefined threshold. If so, a relative humidity (RH) correction factor is added to CTIM and set as the INLETIM. Next, the INLETIM and TTRF are located in a look-up table, and a bias value corresponding to these inputs is identified. The fuel-flow for a fuel circuit is adjusted according to the identified bias value.

Abstract translation: 提供了用于控制燃气涡轮发动机的方法，其中测量压缩机入口温度，环境温度和相对湿度。 利用这些测量，首先确定蒸发冷却器是否积极地将水分输入到进入压缩机的入口空气中。 该确定基于入口空气是否比环境温度基本上更冷。 如果是这样，将EC校正因子加到入口空气温度值（CTIM），并设置为空气温度参数（INLETIM）。 其次，确定相对湿度是否大于预定阈值。 如果是这样，将相对湿度（RH）校正因子添加到CTIM并设置为INLETIM。 接下来，INLETIM和TTRF位于查找表中，并且识别与这些输入相对应的偏置值。 根据所识别的偏置值来调节燃料回路的燃料流量。