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    AIR BIASING SYSTEM IN A GAS TURBINE COMBUSTOR
    2.
    发明申请
    AIR BIASING SYSTEM IN A GAS TURBINE COMBUSTOR 审中-公开
    气体涡轮机中的空气偏心系统

    公开(公告)号：US20120006029A1

    公开(公告)日：2012-01-12

    申请号：US12832099

    申请日：2010-07-08

    申请人： Juan E. Portillo Bilbao ,  Scott M. Martin ,  David M. Ritland

    发明人： Juan E. Portillo Bilbao ,  Scott M. Martin ,  David M. Ritland

    IPC分类号： F02C7/22

    CPC分类号： F23R3/286 ,  F23R3/14 ,  F23R3/26 ,  F23R3/54 ,  F23R2900/00013

    摘要： A combustor (10) including: a first premix main burner (14) comprising a first swirler airfoil section (38); a second premix main burner (15) comprising a second swirler airfoil section (40); and a supply air reversing region upstream of the premix burners (14), (15). The first swirler airfoil section (38) and the second swirler airfoil section (40) are effective to impart swirl to a first airflow and a second airflow characterized by a same swirl number as the airflows exit respective burners (14), (15). The combustor (10) is effective to generate a first airflow volume through the first premix main burner (14) that is different than a second airflow volume through the second premix main burner (15).

    摘要翻译： 1.一种燃烧器（10），包括：第一预混合主燃烧器（14），包括第一旋流器翼型件部分（38）; 第二预混器主燃烧器（15），包括第二旋流器翼型部（40）; 以及在预混燃烧器（14），（15）的上游的供气反向区域。 第一旋流器翼型部分（38）和第二旋流器翼型部分（40）有效地使第一气流产生涡流，并且第二气流的特征在于与气流从相应的燃烧器（14），（15）出口相同的涡流数。 燃烧器（10）有效地通过第一预混合主燃烧器（14）产生与通过第二预混合燃烧器（15）的第二气流体积不同的第一气流量。

    COMBUSTOR LINER FOR A CAN-ANNULAR GAS TURBINE ENGINE AND A METHOD FOR CONSTRUCTING SUCH A LINER
    3.
    发明申请
    COMBUSTOR LINER FOR A CAN-ANNULAR GAS TURBINE ENGINE AND A METHOD FOR CONSTRUCTING SUCH A LINER 审中-公开
    用于CAN-ANNULAR气体涡轮发动机的燃烧器衬管和用于构造这种衬管的方法

    公开(公告)号：US20140216043A1

    公开(公告)日：2014-08-07

    申请号：US14140610

    申请日：2013-12-26

    申请人： Weidong Cai ,  Krishna C. Miduturi ,  David M. Ritland

    发明人： Weidong Cai ,  Krishna C. Miduturi ,  David M. Ritland

    IPC分类号： F23R3/00

    CPC分类号： F23R3/002 ,  F23R3/005 ,  F23R2900/03043 ,  F23R2900/03045 ,  Y10T29/49229

    摘要： A combustor liner (30) for a can-annular gas turbine engine (10) and a method for constructing such a liner are provided. The combustor liner includes an annular wall member (32) A cooling channel (34, 42, 50, 54, 56, 58) is formed through the wall member and extends from an inlet end of the liner to an outlet end of the liner A property of the cooling channel may be varied along a length of the cooling channel. The cooling channel may be formed through the combustor liner using an electro-chemical machining (ECM) process or a three dimensional printing process (3DP).

    摘要翻译： 提供了一种用于罐环式燃气涡轮发动机（10）的燃烧器衬套（30）和用于构造这种衬套的方法。 燃烧器衬套包括环形壁构件（32）。冷却通道（34,42,50,54,56,58）通过壁构件形成并且从衬套的入口端延伸到衬套A的出口端 冷却通道的特性可以沿冷却通道的长度变化。 冷却通道可以使用电化学加工（ECM）工艺或三维印刷工艺（3DP）通过燃烧器衬套形成。

    Turbine engine flow sleeve
    4.
    发明授权
    Turbine engine flow sleeve 有权
    涡轮发动机流量套管

    公开(公告)号：US08528340B2

    公开(公告)日：2013-09-10

    申请号：US12180657

    申请日：2008-07-28

    申请人： David M. Ritland

    发明人： David M. Ritland

    IPC分类号： F02C7/22

    CPC分类号： F02C7/222 ,  F23R3/283 ,  F23R3/286

    摘要： A flow sleeve for use in a turbine engine including a compressor section, a combustion section, and a turbine section downstream from the combustion section. The flow sleeve includes a sleeve wall defining a pre-mixing passage of the combustion section and has a forward end proximate to a cover plate of the combustion section and an opposed aft end. The sleeve wall includes a first wall section extending axially from the sleeve wall forward end and a second wall section extending from the first wall section between the forward and aft ends of the sleeve wall toward the aft end of the sleeve wall. A cavity is formed between the first wall section and the second wall section.

    摘要翻译： 一种用于涡轮发动机的流动套筒，包括压缩机部分，燃烧部分和在燃烧部分下游的涡轮部分。 流动套管包括限定燃烧部分的预混合通道的套管壁，并且具有靠近燃烧部分的盖板的前端和相对的后端。 套筒壁包括从套筒壁前端轴向延伸的第一壁部分和从套筒壁的前端和后端之间的第一壁部分延伸到套管壁的后端的第二壁部分。 在第一壁部和第二壁部之间形成空腔。

    Attenuation of combustion dynamics using a Herschel-Quincke filter
    5.
    发明授权
    Attenuation of combustion dynamics using a Herschel-Quincke filter 有权
    使用Herschel-Quincke过滤器对燃烧动力学的衰减

    公开(公告)号：US08336312B2

    公开(公告)日：2012-12-25

    申请号：US12486213

    申请日：2009-06-17

    申请人： Rajesh Rajaram ,  David M. Ritland

    发明人： Rajesh Rajaram ,  David M. Ritland

    IPC分类号： F02C3/14 ,  F02C7/24 ,  F23R3/46

    CPC分类号： F02C7/24 ,  F05D2260/96 ,  F23M20/005 ,  F23R3/002 ,  F23R3/045 ,  F23R3/286 ,  F23R2900/00014

    摘要： A can-annular gas turbine engine including a casing defining an annulus for receiving air flow from a compressor. A combustor basket is supported within the casing, and a swirler assembly is located within the basket and includes an air inlet and an outlet located in a combustion chamber. The swirler assembly is configured to discharge a fuel/air mixture from the outlet downstream into the combustion chamber. An acoustic filter is provided comprising a Herschel-Quincke tube having a first open end at the annulus and a second open end adjacent to the swirler assembly within the combustion chamber. Components of acoustic pressure oscillations travel along two paths of different lengths from one end of the Herschel-Quincke tube to the opposite end of the tube where out of phase components of the pressure oscillations interact to attenuate the pressure oscillations.

    摘要翻译： 一种罐环式燃气涡轮发动机，其包括限定用于接收来自压缩机的空气流的环的壳体。 燃烧器筐被支撑在壳体内，并且旋流器组件位于筐内并且包括位于燃烧室中的空气入口和出口。 旋流器组件构造成将燃料/空气混合物从下游的出口排出到燃烧室中。 提供了一种声学过滤器，其包括具有环形空间处的第一开口端的Herschel-Quincke管和邻近燃烧室内的旋流器组件的第二开口端。 声压振荡的分量沿着Herschel-Quincke管的一端的不同长度的两个路径行进到管的相对端，其中压力振荡的相异步分量相互作用以衰减压力振荡。

    Circumferential biasing and profiling of fuel injection in distribution ring
    6.
    发明授权
    Circumferential biasing and profiling of fuel injection in distribution ring 有权

    公开(公告)号：US09746185B2

    公开(公告)日：2017-08-29

    申请号：US12712522

    申请日：2010-02-25

    申请人： David M. Ritland ,  Timothy A. Fox

    发明人： David M. Ritland ,  Timothy A. Fox

    IPC分类号： F02C7/22 ,  F23R3/28

    CPC分类号： F23R3/286 ,  F02C7/22

    摘要： An annular fluid distribution device (20) for distributing fluid into a gaseous flow (14), that includes: a first fluid distribution manifold (30) having a first fluid inlet and first fluid outlets (24), wherein the first fluid outlets inject a first fluid into the gaseous flow; and a second fluid distribution manifold (32), having a second fluid inlet and second fluid outlets (26), wherein the second fluid outlets inject a second fluid into the gaseous flow. The second fluid manifold is isolated from the first fluid distribution manifold, and the first fluid outlets and the second fluid outlets are disposed on a common fluid outlet plane (43).

    Asymmetric Baseplate Cooling with Alternating Swirl Main Burners
    7.
    发明申请
    Asymmetric Baseplate Cooling with Alternating Swirl Main Burners 有权
    不对称基板冷却与交替涡流主燃烧器

    公开(公告)号：US20140360156A1

    公开(公告)日：2014-12-11

    申请号：US14140599

    申请日：2013-12-26

    申请人： Krishna C. Miduturi ,  David M. Ritland

    发明人： Krishna C. Miduturi ,  David M. Ritland

    IPC分类号： F23R3/16 ,  F23R3/00

    CPC分类号： F23R3/16 ,  F23R3/005 ,  F23R3/04 ,  F23R3/12 ,  F23R3/283 ,  F23R3/286 ,  F23R2900/03041 ,  F23R2900/03042

    摘要： A combustor arrangement (10) including a pilot burner (22) having a pilot cone (62); a plurality of clockwise (130) main swirlers interposed among a plurality of counterclockwise (132) main swirlers and disposed concentrically about the pilot burner, and a base plate (40) transverse to the main swirlers Inbound-zones (134) exist where adjacent portions (106) of adjacent flows (108) through main swirlers flow toward the pilot cone, and interposed between the inbound zones outbound zones (136) exist where adjacent portions of adjacent flows flow away from the pilot cone The arrangement is configured to preferentially deliver more cooling fluid to the inbound zones than the outbound zones.

    摘要翻译： 一种燃烧器装置（10），包括具有先导锥体（62）的引燃燃烧器（22）; 多个顺时针（130）主旋流器插入在多个逆时针（132）主旋流器中并且围绕引燃燃烧器同心地设置，并且横向于主旋流器入口区（134）的基板（40）存在，其中相邻部分 （106）通过主旋流器流向导向锥体，并且介于入口区域出站区域（136）之间，其中相邻流体的相邻部分远离导向锥体。该装置被配置为优先地输送更多 冷却流体到入境区域比出站区域。

    Combustor apparatus in a gas turbine engine
    10.
    发明授权
    Combustor apparatus in a gas turbine engine 有权
    燃气涡轮发动机中的燃烧器装置

    公开(公告)号：US08549859B2

    公开(公告)日：2013-10-08

    申请号：US12233903

    申请日：2008-09-19

    申请人： Timothy A. Fox ,  David J. Wiebe ,  David M. Ritland ,  John Carl Glessner

    发明人： Timothy A. Fox ,  David J. Wiebe ,  David M. Ritland ,  John Carl Glessner

    IPC分类号： F02C7/22

    CPC分类号： F23R3/16 ,  F23R3/283 ,  F23R3/346 ,  F23R2900/00005

    摘要： A combustion apparatus in a gas turbine engine comprises a combustor shell for receiving air, a fuel injection system associated with the combustor shell, a first fuel supply structure, and a shield structure. The fuel supply structure is in fluid communication with a source of fuel for delivering fuel from the source of fuel to the fuel injection system and comprises a first fuel supply elements including a first section extending along a first path having a component in an axial direction and a second section extending from the first section along a second path having a component in a circumferential direction. The shield structure is associated with at least a portion of the second section of the first fuel supply element.

    摘要翻译： 燃气涡轮发动机中的燃烧装置包括用于接收空气的燃烧器壳体，与燃烧器壳体相关联的燃料喷射系统，第一燃料供应结构和屏蔽结构。 燃料供应结构与燃料源流体连通，用于将燃料从燃料源输送到燃料喷射系统，并且包括第一燃料供应元件，其包括沿着沿轴向方向具有部件的第一路径延伸的第一部分，以及 第二部分沿着沿圆周方向具有部件的第二路径从第一部分延伸。 屏蔽结构与第一燃料供应元件的第二部分的至少一部分相关联。