公开(公告)号：US07096671B2

公开(公告)日：2006-08-29

申请号：US10686458

申请日：2003-10-14

申请人： Robert Bland ,  Ramarao V. Bandaru ,  John Battaglioli

发明人： Robert Bland ,  Ramarao V. Bandaru ,  John Battaglioli

IPC分类号： F02C7/22 ,  F02C7/26

CPC分类号： F23R3/40

摘要： Aspects according to the invention relate to a catalytic combustor system for a turbine engine and an associated method. Catalytic combustors are used in connection with turbine engines because they can minimize the formation of oxides of nitrogen during combustion. Despite this emissions advantage, catalytic combustion systems can increase the level of CO in the turbine exhaust. According to aspects of the invention, vortex formation devices includes vortex generators, swirlers and mixers can be placed downstream of each catalytic module surrounding the pilot nozzle so as to form one or more vortices in the otherwise substantially laminar flow exiting the modules. The vortices can create a suction so that a portion of the flow exiting the pilot nozzles is mixed with the flow exiting the catalyst modules. The introduction of the higher temperature pilot flow can accelerate the catalytic reaction time, promoting burnout of the CO formed during combustion.

摘要翻译： 根据本发明的方面涉及一种用于涡轮发动机的催化燃烧器系统和相关联的方法。 催化燃烧器用于涡轮发动机，因为它们可以在燃烧过程中最小化氮氧化物的形成。 尽管这种排放优势，催化燃烧系统可以增加涡轮排气中的CO水平。 根据本发明的方面，涡流形成装置包括涡流发生器，旋流器和混合器可以放置在围绕引燃喷嘴的每个催化剂模块的下游，以便在离开模块的基本层流中形成一个或多个涡流。 涡流可以产生吸力，使得离开引燃喷嘴的流的一部分与离开催化剂模块的流混合。 引入较高温度的先导流可以加速催化反应时间，促进燃烧过程中形成的CO的烧坏。

公开(公告)号：US07096667B2

公开(公告)日：2006-08-29

申请号：US10754196

申请日：2004-01-09

申请人： Walter Ray Laster ,  Ramarao V. Bandaru ,  Joan Mae Baer

发明人： Walter Ray Laster ,  Ramarao V. Bandaru ,  Joan Mae Baer

IPC分类号： F02C9/16 ,  F23R3/40

CPC分类号： F02C9/22 ,  F02C9/18 ,  F05D2260/20 ,  F23R3/40

摘要： A catalytic gas turbine includes a compressor, a catalytic combustor, a turbine, and a flow path conducting a bypass portion of the compressed air around the combustor and turbine. A method of operating the catalytic gas turbine to activate a catalyst in the catalytic combustor includes opening an inlet guide vane upstream of the compressor to a position to produce an increased volume of compressed air. The increased volume exceeds a volume of compressed air needed to support combustion. A bypass portion of the compressed air is extracted and directed around the combustor and turbine. The method may also include extracting a recirculation portion of the compressed air and directing the recirculation portion into the inlet of the compressor.

摘要翻译： 催化燃气轮机包括压缩机，催化燃烧器，涡轮机以及在燃烧器和涡轮机周围传导压缩空气的旁路部分的流路。 操作催化燃气轮机以在催化燃烧器中活化催化剂的方法包括将压缩机上游的入口引导叶片打开以产生增加的压缩空气体积的位置。 体积增加超过支持燃烧所需的压缩空气体积。 压缩空气的旁路部分被提取并引导到燃烧室和涡轮机周围。 该方法还可以包括提取压缩空气的再循环部分并将再循环部分引导到压缩机的入口中。

公开(公告)号：US06775989B2

公开(公告)日：2004-08-17

申请号：US10244064

申请日：2002-09-13

申请人： Ramarao V. Bandaru ,  John Carl Glessner

发明人： Ramarao V. Bandaru ,  John Carl Glessner

IPC分类号： F23R340

CPC分类号： F23R3/40 ,  B01J35/04 ,  F23C2900/13001

摘要： A catalytic combustor 30 includes a frame 32 and catalyst support plate assemblies 34 carried by the frame. A catalyst support plate assembly 34 includes a pair of opposing plates 36A, 36B, at least one having ridges 38A, 38B that define passageways 40 between the pair of opposing plates. A catalyst 44 is carried by the catalyst support plate assemblies 34. Both of the opposing plates 36A, 36B may have ridges 38A, 38B with valleys 42A, 42B between adjacent ridges. A pair of opposing plates 36A, 36B may be aligned and connected at opposing ridges 38A, 38B so that opposing valleys 42A, 42B define air passageways having predetermined shapes. The catalyst support plate assemblies 34 may be arranged in back-to-back relation so that adjacent pairs of catalyst support plate assemblies 34 define fuel/air passageways 46. Adjacent pairs of catalyst support plate assemblies 34 may be offset from one another to define a nested configuration.

公开(公告)号：US06923001B2

公开(公告)日：2005-08-02

申请号：US10619342

申请日：2003-07-14

申请人： Walter Ray Laster ,  Ramarao V. Bandaru

发明人： Walter Ray Laster ,  Ramarao V. Bandaru

IPC分类号： F23R3/40

CPC分类号： F23R3/40 ,  F23C2900/13002

摘要： A pilotless catalytic combustor (10) including a basket (12) having a central axis (14) and a central core region (16) disposed along a portion of the central axis. Catalytic combustion modules (18) are circumferentially disposed about the central axis radially outward of the central core region for receiving a fuel flow (20) and a first portion of an oxidizer flow (22), and discharge a partially oxidized fuel/oxidizer mixture (24) at respective exit ends (26). A base plate (30) is positioned in the central core region upstream of the exit ends of the catalytic combustion modules, the baseplate defining a recirculation zone (32) near the respective exit ends for stabilizing oxidation in the burnout zone. A method of staged fueling for a pilotless catalytic combustor includes providing fuel to at least one of the modules during start up and progressively providing fuel to other modules as a load on the turbine engine is increased.

摘要翻译： 一种无引导催化燃烧器（10），其包括具有中心轴线（14）的篮（12）和沿中心轴线的一部分设置的中心芯区域（16）。 催化燃烧模块（18）围绕中心芯区域径向向外的中心轴周向设置，用于接收燃料流（20）和氧化剂流（22）的第一部分，并且将部分氧化的燃料/氧化剂混合物 24）在相应的出口端（26）处。 基板（30）位于催化燃烧模块的出口端上游的中心芯区域中，底板限定在相应出口端附近的再循环区域（32），用于稳定燃尽区域中的氧化。 用于无引导催化燃烧器的分级加油的方法包括在启动期间向至少一个模块提供燃料，并且随着涡轮发动机上的负载增加而逐渐向其它模块提供燃料。

公开(公告)号：US20080245337A1

公开(公告)日：2008-10-09

申请号：US11732143

申请日：2007-04-03

申请人： Ramarao V. Bandaru ,  Kwanwoo Kim ,  Shiva Srinivasan ,  William Byrne

发明人： Ramarao V. Bandaru ,  Kwanwoo Kim ,  Shiva Srinivasan ,  William Byrne

IPC分类号： F02C7/12

CPC分类号： F23R3/46 ,  F23M20/005 ,  F23R3/04 ,  F23R3/283 ,  F23R2900/00014 ,  F23R2900/03044

摘要： A system for dampening combustor dynamics within a turbomachine. The system may include at least one resonator installed adjacent a head-end region of a combustion can. The at least one resonator may include a first side having a plurality of holes forming a cold side hole pattern; a second side having a plurality of holes forming a hot side hole pattern; and a cavity substantially defined by the first side and the hot side. The cold side hole pattern may be oriented such that each of the plurality of holes in the cold side hole pattern allows for a jet of a cooling air to substantially impinge a second side facing surface; and wherein the hot side hole pattern is oriented such that each of the plurality of holes in the hot side hole pattern allows for a jet of a working fluid to substantially impinges a first side facing surface.

摘要翻译： 一种用于抑制涡轮机内燃烧室动力学的系统。 该系统可以包括邻近燃烧罐的前端区域安装的至少一个谐振器。 所述至少一个谐振器可以包括具有形成冷侧孔图案的多个孔的第一侧面; 具有形成热侧孔图案的多个孔的第二侧; 以及基本上由第一侧和热侧限定的空腔。 冷侧孔图案可以被定向成使得冷侧孔图案中的多个孔中的每一个允许冷却空气的射流基本上撞击第二侧面; 并且其中所述热侧孔图案被定向成使得所述热侧孔图案中的所述多个孔中的每一个允许工作流体的射流基本上撞击第一面对面。

公开(公告)号：US07421843B2

公开(公告)日：2008-09-09

申请号：US11035561

申请日：2005-01-15

申请人： Walter Ray Laster ,  Ramarao V. Bandaru

发明人： Walter Ray Laster ,  Ramarao V. Bandaru

IPC分类号： F02C7/22 ,  F02C7/26

CPC分类号： F23R3/40 ,  F23C13/04 ,  F23R3/346 ,  F23R2900/00002

摘要： A gas turbine combustor (23) includes a catalytic combustion stage (22) receiving a first portion (18) of a total oxidizer flow (16) and a first portion (30) of a total fuel flow (29) and discharging a partially oxidized fuel/oxidizer mixture (40) into a post catalytic combustion stage (24) defined by a combustion liner (58). The combustor further includes an injector scoop (54) having an injector scoop inlet (56) in fluid communication with an opening (56) in the combustion liner for receiving a second portion (20) of the oxidizer flow. A fuel outlet (e.g. 64) selectively supplies a second portion (42) of the total fuel flow into the second portion of the oxidizer flow. The injector scoop includes an injector scoop outlet (66) in fluid communication with the post catalytic combustion stage and discharges a fuel/oxidizer mixture (44) into the partially combusted fuel/oxidizer mixture at an angle relative to the flow axis to impart a swirl to the fuel/oxidizer mixture as it enters the post catalytic combustion stage.

摘要翻译： 燃气轮机燃烧器（23）包括接收总氧化剂流（16）的第一部分（18）和总燃料流（29）的第一部分（30）的催化燃烧阶段（22），并且将部分氧化 燃料/氧化剂混合物（40）进入由燃烧衬套（58）限定的后催化燃烧阶段（24）。 燃烧器还包括具有与燃烧衬套中的开口（56）流体连通的喷射器勺入口（56）的喷射器勺（54），用于接收氧化剂流的第二部分（20）。 燃料出口（例如64）选择性地将总燃料流的第二部分（42）供应到氧化剂流的第二部分中。 喷射器勺包括与后催化燃烧阶段流体连通的喷射器勺出口（66），并且将燃料/氧化剂混合物（44）以相对于流动轴线成一定角度排放到部分燃烧的燃料/氧化剂混合物中以赋予涡流 燃料/氧化剂混合物进入后催化燃烧阶段。

公开(公告)号：US07752850B2

公开(公告)日：2010-07-13

申请号：US11173655

申请日：2005-07-01

申请人： Walter R. Laster ,  Ramarao V. Bandaru

发明人： Walter R. Laster ,  Ramarao V. Bandaru

IPC分类号： F02C9/00

CPC分类号： F23R3/40 ,  F23R3/343

摘要： A combustor (22) for a gas turbine (10) includes a main burner oxidizer flow path (34) delivering a first portion (32) of an oxidizer flow (e.g., 16) to a main burner (28) of the combustor and a pilot oxidizer flow path (38) delivering a second portion (36) of the oxidizer flow to a pilot (30) of the combustor. The combustor also includes a flow controller (42) disposed in the pilot oxidizer flow path for controlling an amount of the second portion delivered to the pilot.

摘要翻译： 用于燃气轮机（10）的燃烧器（22）包括主燃烧器氧化器流动路径（34），其将氧化剂流（例如16）的第一部分（32）输送到燃烧器的主燃烧器（28） 导向氧化剂流动路径（38）将氧化剂流的第二部分（36）输送到燃烧器的导向件（30）。 燃烧器还包括设置在先导氧化剂流动路径中的流量控制器（42），用于控制输送到飞行员的第二部分的量。

公开(公告)号：US07721553B2

公开(公告)日：2010-05-25

申请号：US11488563

申请日：2006-07-18

申请人： Sean A. Miller ,  Ramarao V. Bandaru

发明人： Sean A. Miller ,  Ramarao V. Bandaru

IPC分类号： F02C7/25 ,  F02C3/00 ,  F23R3/14

CPC分类号： F02C7/266 ,  F23D2209/10 ,  F23M11/00 ,  F23N5/12 ,  F23N5/245 ,  F23R3/286

摘要： A method and apparatus for detecting a flashback condition in a fuel nozzle (8) of a gas turbine (10) are provided. The fuel nozzle is configured to pass a flow of air (20) to be mixed with a fuel in a premixing zone (11). The apparatus includes at least one fuel injecting device (12) positioned to define a point of fuel injection in the premixing zone. The apparatus further includes an electrode (16) positioned upstream of the point of fuel injection. The electrode is adapted to sense a flashback condition that can occur in the premixing zone.

摘要翻译： 提供一种用于检测燃气轮机（10）的燃料喷嘴（8）中的回火状态的方法和装置。 燃料喷嘴构造成通过与预混合区域（11）中的燃料混合的空气流（20）。 该装置包括至少一个燃料喷射装置（12），其定位成在预混合区域中限定燃料喷射点。 该装置还包括位于燃料喷射点的上游的电极（16）。 电极适于感测可能发生在预混合区域中的闪回状态。

公开(公告)号：US20080016877A1

公开(公告)日：2008-01-24

申请号：US11488563

申请日：2006-07-18

申请人： Sean A. Miller ,  Ramarao V. Bandaru

发明人： Sean A. Miller ,  Ramarao V. Bandaru

IPC分类号： F02C7/00

CPC分类号： F02C7/266 ,  F23D2209/10 ,  F23M11/00 ,  F23N5/12 ,  F23N5/245 ,  F23R3/286

摘要： A method and apparatus for detecting a flashback condition in a fuel nozzle (8) of a gas turbine (10) are provided. The fuel nozzle is configured to pass a flow of air (20) to be mixed with a fuel in a premixing zone (11). The apparatus includes at least one fuel injecting device (12) positioned to define a point of fuel injection in the premixing zone. The apparatus further includes an electrode (16) positioned upstream of the point of fuel injection. The electrode is adapted to sense a flashback condition that can occur in the premixing zone.

摘要翻译： 提供一种用于检测燃气轮机（10）的燃料喷嘴（8）中的回火状态的方法和装置。 燃料喷嘴构造成通过与预混合区域（11）中的燃料混合的空气流（20）。 该装置包括至少一个燃料喷射装置（12），其定位成在预混合区域中限定燃料喷射点。 该装置还包括位于燃料喷射点的上游的电极（16）。 电极适于感测可能发生在预混合区域中的闪回状态。