公开(公告)号：US09388985B2

公开(公告)日：2016-07-12

申请号：US13194385

申请日：2011-07-29

Applicant: Chunyang Wu ,  Derrick Walter Simons ,  Jonathan Dwight Berry ,  Michael John Hughes

Inventor： Chunyang Wu ,  Derrick Walter Simons ,  Jonathan Dwight Berry ,  Michael John Hughes

IPC: F23R3/14 ,  F23R3/28 ,  F23R3/34

CPC classification number: F23R3/14 ,  F05B2260/96 ,  F23R3/286 ,  F23R3/34 ,  F23R2900/00014

Abstract: A premixing apparatus for a gas turbine system includes non-swirl elements around a periphery of a face of a premixing apparatus and a swirl assembly located substantially at a center of the face. The non-swirl elements premix a premixture prior to the premixture being delivered to a combustor of the gas turbine system. The swirl assembly disturbs a flow of fluid prior to the fluid being delivered to the combustor. The premixture includes fuel and oxidant, and the fluid disturbed by the swirl assembly includes the oxidant or the premixture.

Abstract translation: 用于燃气涡轮机系统的预混合装置包括围绕预混合装置的表面的周边的非旋转元件和基本上位于该表面中心的旋转组件。 非旋流元件在将预混合物输送到燃气轮机系统的燃烧器之前将混合物预混合。 涡流组件在流体被输送到燃烧器之前会扰乱流体流动。 预混合物包括燃料和氧化剂，并且由涡旋组件扰动的流体包括氧化剂或预混合物。

公开(公告)号：US08904797B2

公开(公告)日：2014-12-09

申请号：US13194178

申请日：2011-07-29

Applicant: Jonathan Dwight Berry ,  Derrick Walter Simons ,  Jason Thurman Stewart

Inventor： Jonathan Dwight Berry ,  Derrick Walter Simons ,  Jason Thurman Stewart

IPC: F02C1/00 ,  F23R3/28

CPC classification number: F23R3/283 ,  F23M20/005 ,  F23R3/286 ,  F23R2900/00005 ,  F23R2900/00014

Abstract: Systems are provided for mounting sector nozzles within gas turbine combustors. In one embodiment, a sector nozzle includes a nozzle portion configured to mix fuel and air to produce a fuel-air mixture and a shell coupled to the nozzle portion. The sector nozzle also includes a first longitudinal strut and a second longitudinal strut coupled to a first surface of the shell on opposite sides of a window within the first surface. A third longitudinal strut is coupled to a second surface of the shell, and the second surface is disposed opposite of the first surface.

Abstract translation: 提供了用于在燃气轮机燃烧器中安装扇形喷嘴的系统。 在一个实施例中，扇形喷嘴包括配置成混合燃料和空气以产生燃料 - 空气混合物的喷嘴部分和联接到喷嘴部分的壳体。 扇形喷嘴还包括第一纵向支柱和第二纵向支柱，该第二纵向支柱在第一表面内的窗口的相对侧上联接到壳体的第一表面。 第三纵向支柱联接到壳体的第二表面，并且第二表面设置成与第一表面相对。

公开(公告)号：US20130014514A1

公开(公告)日：2013-01-17

申请号：US13182956

申请日：2011-07-14

Applicant: Bryan Wesley Romig ,  Willy Steve Ziminsky ,  Derrick Walter Simons

Inventor： Bryan Wesley Romig ,  Willy Steve Ziminsky ,  Derrick Walter Simons

IPC: F02C7/22 ,  F02C7/08

CPC classification number: F23R3/46 ,  F02C7/224 ,  F23K5/20 ,  F23K2301/204 ,  F23R3/28 ,  F23R2900/00013

Abstract: A gas turbine includes a plurality of combustion chambers; at least one fuel nozzle for each of the combustion chambers; at least one fuel line for each fuel nozzle in each of the combustion chambers; at least one heat exchanger for each fuel line configured to adjust a temperature of a fuel flow to each fuel nozzle; and a controller configured to control each of the heat exchangers to reduce temperature variations amongst the combustion chambers.

Abstract translation: 燃气轮机包括多个燃烧室; 用于每个燃烧室的至少一个燃料喷嘴; 用于每个燃烧室中的每个燃料喷嘴的至少一个燃料管线; 每个燃料管线的至少一个热交换器被配置为调节到每个燃料喷嘴的燃料流的温度; 以及控制器，被配置为控制每个所述热交换器以减少所述燃烧室之间的温度变化。

公开(公告)号：US20100058767A1

公开(公告)日：2010-03-11

申请号：US12205503

申请日：2008-09-05

Applicant: Derrick Walter Simons ,  Alberto Jose Negroni ,  Larry Lou Thomas ,  Jeffrey Scott LeBegue

Inventor： Derrick Walter Simons ,  Alberto Jose Negroni ,  Larry Lou Thomas ,  Jeffrey Scott LeBegue

IPC: F02C1/00

CPC classification number: F23R3/14 ,  F23D2900/14701 ,  F23R3/286 ,  F23R3/34

Abstract: A combustor includes a primary combustion chamber and a secondary combustion chamber, one or more primary nozzles disposed in the primary combustion chamber and providing fuel to the primary combustion chamber, a centerbody assembly, a venturi disposed downstream of the centerbody assembly, and a secondary fuel nozzle housed within the centerbody assembly and extending towards the venturi and providing fuel to the secondary combustion chamber. The secondary fuel nozzle includes a fuel passage and an air passage, and a swirler positioned around the fuel passage and having one or more vanes projecting radially within the air passage, each vane having a trailing edge arranged at a swirl angle relative to a longitudinal axis of the secondary fuel nozzle, the swirl angle is greater than 45°.

Abstract translation: 燃烧器包括主燃烧室和二次燃烧室，设置在主燃烧室中的一个或多个主喷嘴并向主燃烧室提供燃料，中心体组件，设置在中心体组件下游的文丘里管和辅助燃料 喷嘴容纳在中心体组件内并且朝向文丘里管延伸并向第二燃烧室提供燃料。 二次燃料喷嘴包括燃料通道和空气通道，以及旋转器，其位于燃料通道周围并且具有一个或多个径向地在空气通道内突出的叶片，每个叶片具有相对于纵向轴线以旋转角度布置的后缘 的二次燃料喷嘴，旋转角度大于45°。

公开(公告)号：US20090211255A1

公开(公告)日：2009-08-27

申请号：US12035225

申请日：2008-02-21

Applicant: Derrick Walter Simons ,  Geoffrey D. Myers ,  Larry L. Thomas ,  Jeffrey Lebegue

Inventor： Derrick Walter Simons ,  Geoffrey D. Myers ,  Larry L. Thomas ,  Jeffrey Lebegue

IPC: F02C1/00

CPC classification number: F23R3/18 ,  F23M20/00 ,  F23M2900/13002 ,  F23R3/286

Abstract: A gas turbine combustor is presented, which includes a combustion chamber that is positioned downstream of a premixing chamber. The premixing chamber includes at least one opening for ingesting air. At least one primary fuel nozzle is disposed to discharge fuel into the premixing chamber. The fuel discharged from the primary fuel nozzle mixes with the ingested air in the premixing chamber to provide a fuel air mix. A secondary fuel nozzle is disposed proximate the combustion chamber to discharge fuel at the combustion chamber. A stabilizer is disposed at the secondary fuel nozzle so as to be positioned in close proximity to a flame when fuel at the secondary fuel nozzle is ignited. The stabilizer is composed of a material having the ability to absorb heat from a heat flux generated within the combustor and maintaining a temperature sufficient to sustain ignition of the flame. A method of stabilizing a flame in a gas turbine combustor is also presented. The method including discharging fuel at a combustion chamber of the gas turbine combustor and positioning a stabilizer in close proximity to a flame when the fuel at a combustion chamber is ignited. The stabilizer absorbing heat from a heat flux generated within the combustor and maintaining a temperature sufficient to sustain ignition of the flame.

Abstract translation: 提出了一种燃气轮机燃烧器，其包括位于预混合室下游的燃烧室。 预混合室包括至少一个用于吸入空气的开口。 设置至少一个主燃料喷嘴以将燃料排放到预混合室中。 从主燃料喷嘴排出的燃料与预混合室中摄入的空气混合以提供燃料空气混合物。 辅助燃料喷嘴设置在燃烧室附近以在燃烧室排出燃料。 当辅助燃料喷嘴处的燃料被点燃时，稳定器设置在次级燃料喷嘴处，以便定位成靠近火焰。 稳定器由具有从燃烧器内产生的热通量吸收热量并保持足以维持火焰点火的温度的材料构成。 还提出了一种在燃气轮机燃烧器中稳定火焰的方法。 该方法包括在燃气轮机燃烧器的燃烧室处排出燃料，并且当燃烧室处的燃料被点燃时将稳定器定位成非常接近火焰。 该稳定器从燃烧器内产生的热通量吸收热量并保持足以维持火焰点燃的温度。

公开(公告)号：US08997558B2

公开(公告)日：2015-04-07

申请号：US13075055

申请日：2011-03-29

Applicant: Bryan Wesley Romig ,  Jonathan Hale Kegley ,  Robert Wade Clifford ,  Derrick Walter Simons

Inventor： Bryan Wesley Romig ,  Jonathan Hale Kegley ,  Robert Wade Clifford ,  Derrick Walter Simons

IPC: G01M15/05 ,  G01N1/22 ,  F01D21/00

CPC classification number: G01N1/2252 ,  F01D21/003 ,  F05D2270/80 ,  F23N5/003 ,  F23N5/18 ,  F23N2031/18 ,  F23N2041/20 ,  F23N2900/05005 ,  F23R3/00

Abstract: Embodiments of the present disclosure are directed towards a turbine combustor probe having a combustion dynamics monitoring probe configured to monitor combustion dynamics within a turbine combustor. The turbine combustor probe also has a gas sampling sleeve configured to collect a gas sample from an airflow path between a liner and a flow sleeve of the turbine combustor.

Abstract translation: 本公开的实施例涉及具有燃烧动力学监测探针的涡轮机燃烧器探头，其被配置为监测涡轮机燃烧器内的燃烧动力学。 涡轮机燃烧器探头还具有气体采样套筒，该气体采样套筒构造成从涡轮机燃烧器的衬套和流动套筒之间的气流通道收集气体样品。

公开(公告)号：US20100192587A1

公开(公告)日：2010-08-05

申请号：US12364924

申请日：2009-02-03

Applicant: William Kirk Hessler ,  Derrick Walter Simons ,  Jeffrey Scott Lebegue

Inventor： William Kirk Hessler ,  Derrick Walter Simons ,  Jeffrey Scott Lebegue

IPC: F23R3/42 ,  B23P11/00

CPC classification number: F23R3/16 ,  Y10T29/4932

Abstract: A combustor assembly for use in a gas turbine engine and method of assembly is described. The combustor assembly includes a combustor liner having a slot that at least partially circumscribes the combustor liner. The slot is defined adjacent to a venturi throat region defined within the liner. The combustor assembly also includes a restrictor plate having at least one aperture defined therein. The restrictor plate is removably coupled within the combustor assembly such that the restrictor plate is inserted within the slot and extends at least partially across the venturi throat region.

Abstract translation: 描述了一种用于燃气涡轮发动机的燃烧器组件和组装方法。 燃烧器组件包括具有至少部分地围绕燃烧器衬套的槽的燃烧器衬套。 狭槽被限定在衬里内限定的文丘里喉部区域附近。 燃烧器组件还包括具有限定在其中的至少一个孔的限制板。 节流板可拆卸地联接在燃烧器组件内，使得限流板插入槽内并至少部分延伸穿过文丘里喉部区域。

公开(公告)号：US20090053054A1

公开(公告)日：2009-02-26

申请号：US11841053

申请日：2007-08-20

Applicant: Neal William Grooms ,  Jeffrey Scott Lebegue ,  Derrick Walter Simons

Inventor： Neal William Grooms ,  Jeffrey Scott Lebegue ,  Derrick Walter Simons

IPC: F01D1/02

CPC classification number: F23R3/002 ,  F23R3/04 ,  F23R3/286

Abstract: Disclosed is a leakage reducing venturi for a dry low nitric oxides (NOx) emissions combustor, the venturi including a substantially annular outer liner, a substantially annular inner liner, a venturi channel defined by the annular inner liner and the annular outer liner, the venturi channel including a forward end and an aft end, a forward weld disposed in proximity to the forward end of the venturi channel, the forward weld being configured to connect the annular outer liner with the annular inner liner, and an aft weld disposed in proximity to the aft end of the venturi channel, the aft weld being configured to connect the annular outer liner with the annular inner liner.

Abstract translation: 公开了一种用于干燥的低氧化氮（NOx）排放燃烧器的泄漏降低文丘里管，文丘里管包括基本上环形的外衬套，基本上环形的内衬，由环形内衬和环形外衬层限定的文丘里通道，文丘里管 通道，其包括前端和后端，设置在文丘里通道的前端附近的正向焊接，所述正向焊接构造成将环形外衬套与环形内衬连接，以及设置在靠近 文丘里通道的后端，后焊接构造成将环形外衬与环形内衬连接。

公开(公告)号：US08959925B2

公开(公告)日：2015-02-24

申请号：US13352496

申请日：2012-01-18

Applicant: Bryan Wesley Romig ,  Derrick Walter Simons ,  Venkat Narra

Inventor： Bryan Wesley Romig ,  Derrick Walter Simons ,  Venkat Narra

IPC: F02C7/22 ,  F02C7/26 ,  F02C7/264 ,  F02G1/055 ,  F02G3/00 ,  F02C9/00 ,  F02C3/00 ,  F02C1/00

CPC classification number: F02C7/262 ,  F02C9/26 ,  F23R3/48 ,  Y02E20/344

Abstract: A method is disclosed for controlling gas turbine operation in response to lean blowout of a combustion can. The gas turbine comprises a pair of combustion cans. The method includes sensing that a first combustion can is extinguished during a full load operation of the gas turbine, adjusting a fuel ratio between the fuel nozzles in each can, delivering a richer fuel mixture to the fuel nozzles nearest to the cross-fire tubes, generating a cross-fire from the second combustion can to the first combustion can, detecting a recovery of the turbine load, and adjusting the fuel ratio to the normal balanced fuel distribution between the fuel nozzles in each can.

Abstract translation: 公开了一种用于响应于燃烧罐的精馏而控制燃气轮机操作的方法。 燃气轮机包括一对燃烧罐。 该方法包括检测在燃气轮机的满载操作期间第一燃烧罐被熄灭，调节每个罐中的燃料喷嘴之间的燃料比，将更加丰富的燃料混合物输送到最靠近交叉火管的燃料喷嘴， 产生从第二燃烧罐到第一燃烧罐的交叉火焰，检测涡轮机负载的恢复，以及将燃料比调整到每个罐中的燃料喷嘴之间的正常平衡燃料分配。

公开(公告)号：US08707704B2

公开(公告)日：2014-04-29

申请号：US11756448

申请日：2007-05-31

Applicant: Derrick Walter Simons ,  Jeffrey Scott Lebegue ,  Krishna Kumar Venkataraman

Inventor： Derrick Walter Simons ,  Jeffrey Scott Lebegue ,  Krishna Kumar Venkataraman

IPC: F02C1/00

CPC classification number: F23R3/002 ,  F23R3/286

Abstract: A method of assembling a turbine engine includes defining a first chamber and defining a second chamber. The method also includes forming at least one venturi device oriented with a predetermined venturi step angle greater than approximately 48°. The method further includes coupling the first chamber in flow communication with the second chamber via the venturi device therebetween.

Abstract translation: 一种组装涡轮发动机的方法包括限定第一室并限定第二室。 该方法还包括形成至少一个以大于约48°的预定文丘里阶梯角取向的文氏管装置。 该方法还包括通过其间的文丘里装置将第一室与第二室流体连通地联接。