公开(公告)号：US20100269509A1

公开(公告)日：2010-10-28

申请号：US11656723

申请日：2007-01-23

Applicant: Arthur J. Harris, JR. ,  Rajeev Ohri

Inventor： Arthur J. Harris, JR. ,  Rajeev Ohri

IPC: F02C3/14

CPC classification number: F23R3/286 ,  F23D14/82 ,  F23R3/04 ,  F23R3/343

Abstract: A gas turbine combustor (10) comprises a base plate (12) from which protrude a plurality of lips (36) that surround respective apertures (16) into which are positioned downstream ends (19) of main swirler assemblies (18). The apertures (16) are arranged about a centrally positioned pilot cone (22) that comprises an inner cone (23) and an outer cone (25), defining a space (31) there between. A number of laterally directed apertures (60) are disposed along the outer cone (25) so as to direct a flow of fluid toward a near portion (38) of each lip (36), thereby perturbing pockets of high fuel-to-air mixtures between the outer cone (25) and the near region (38). The provision of such laterally directed apertures (60) reduces or eliminates flashback between the outer cone (25) and the near region (38) through such action.

Abstract translation: 燃气涡轮机燃烧器（10）包括基板（12），所述底板（12）突出有围绕相应孔（16）的多个唇缘（36），所述唇部位于主旋流器组件（18）的下游端部（19）。 孔（16）围绕中心定位的先导锥体（22）布置，其包括内锥体（23）和外锥体（25），在其间限定空间（31）。 多个横向定向的孔（60）沿着外锥体（25）设置，以便将流体流引向每个唇缘（36）的近部分（38），从而扰乱高燃料空气的口袋 外锥体（25）和近区域（38）之间的混合物。 通过这种动作，提供这种侧向定向的孔（60）可减少或消除外锥体（25）和近区域（38）之间的回波。

公开(公告)号：US07805946B2

公开(公告)日：2010-10-05

申请号：US11298323

申请日：2005-12-08

Applicant: Rajeev Ohri ,  Arthur J. Harris, Jr. ,  Elliot G. Griffin ,  Michael H. Koenig ,  Herbert C. Reid ,  Paul D. Maples

Inventor： Rajeev Ohri ,  Arthur J. Harris, Jr. ,  Elliot G. Griffin ,  Michael H. Koenig ,  Herbert C. Reid ,  Paul D. Maples

IPC: F02C1/00 ,  F02G3/00

CPC classification number: F23R3/60

Abstract: Embodiments of the invention relate to a combustor flow sleeve for a turbine engine. According to aspects of the invention, the flow sleeve can be attached to one of the components in the combustor head-end by a plurality of fasteners. In one embodiment, the flow sleeve can be attached directly to the combustor head-end component by a plurality of bolts. The bolted flow sleeve can reduce the time to install or remove the flow sleeve. In certain areas, it may not be possible to directly attach the flow sleeve to the combustor component. A flow sleeve according to aspects of the invention can be adapted to facilitate indirect attachment to the combustor head-end component. The flow sleeve can further be adapted to include thermal relief slots to accommodate any differential thermal expansion or contraction between the flow sleeve and the component to which the flow sleeve is attached.

Abstract translation: 本发明的实施例涉及一种用于涡轮发动机的燃烧器流动套筒。 根据本发明的方面，流动套管可以通过多个紧固件附接到燃烧器头端中的一个部件。 在一个实施例中，流动套筒可以通过多个螺栓直接附接到燃烧器头端部件。 螺栓流动套筒可以减少安装或拆卸流动套管的时间。 在某些区域中，可能不可能将流动套筒直接附接到燃烧器部件。 根据本发明的方面的流动套筒可以适于促进间接地连接到燃烧器头端部件。 流动套管还可以适于包括热释放槽，以适应流动套筒与流动套筒所附接的部件之间的任何不同的热膨胀或收缩。

公开(公告)号：US07461719B2

公开(公告)日：2008-12-09

申请号：US11272357

申请日：2005-11-10

Applicant: Steven E. Tobik ,  Stanley S. Sattinger ,  Rajeev Ohri ,  Michael H. Koenig

Inventor： Steven E. Tobik ,  Stanley S. Sattinger ,  Rajeev Ohri ,  Michael H. Koenig

IPC: F01N1/02

CPC classification number: F01N1/02 ,  F01N1/023 ,  F23R2900/00014

Abstract: Aspects of the invention are directed to a system for improving the damping performance of an acoustic resonator. According to aspects of the invention, a resonator, such as a Helmholtz resonator, can be attached to a surface of a combustor component in a turbine engine. The combustor component includes a region in which a plurality of passages extend through the thickness of the component. The resonator is attached to the component so as to enclose at least some of the passages. The passages are in fluid communication with a cavity defined between the component surface and the resonator. Resonator performance is a function of the length of the passages in the component. According to aspects of the invention, resonator performance can be improved by reducing the length of the passages in the component by reducing the thickness of the component in a region that includes the plurality of passages.

Abstract translation: 本发明的方面涉及一种用于改善声谐振器的阻尼性能的系统。 根据本发明的方面，诸如亥姆霍兹共振器的谐振器可以附接到涡轮发动机中的燃烧器部件的表面。 燃烧器部件包括多个通道延伸穿过部件的厚度的区域。 谐振器附接到部件上以便封闭至少一些通道。 通道与组件表面和谐振器之间限定的空腔流体连通。 谐振器性能是组件中通道长度的函数。 根据本发明的方面，通过减少包括多个通道的区域中的部件的厚度，可以减少部件中的通道的长度来改善谐振器性能。

公开(公告)号：US20070130958A1

公开(公告)日：2007-06-14

申请号：US11298323

申请日：2005-12-08

Applicant: Rajeev Ohri ,  Arthur Harris ,  Elliot Griffin ,  Michael Koenig ,  Herbert Reid ,  Paul Maples

Inventor： Rajeev Ohri ,  Arthur Harris ,  Elliot Griffin ,  Michael Koenig ,  Herbert Reid ,  Paul Maples

IPC: F23R3/60

CPC classification number: F23R3/60

Abstract: Embodiments of the invention relate to a combustor flow sleeve for a turbine engine. According to aspects of the invention, the flow sleeve can be attached to one of the components in the combustor head-end by a plurality of fasteners. In one embodiment, the flow sleeve can be attached directly to the combustor head-end component by a plurality of bolts. The bolted flow sleeve can reduce the time to install or remove the flow sleeve. In certain areas, it may not be possible to directly attach the flow sleeve to the combustor component. A flow sleeve according to aspects of the invention can be adapted to facilitate indirect attachment to the combustor head-end component. The flow sleeve can further be adapted to include thermal relief slots to accommodate any differential thermal expansion or contraction between the flow sleeve and the component to which the flow sleeve is attached.

Abstract translation: 本发明的实施例涉及一种用于涡轮发动机的燃烧器流动套筒。 根据本发明的方面，流动套管可以通过多个紧固件附接到燃烧器头端中的一个部件。 在一个实施例中，流动套筒可以通过多个螺栓直接附接到燃烧器头端部件。 螺栓流动套筒可以减少安装或拆卸流动套管的时间。 在某些区域中，可能不可能将流动套筒直接附接到燃烧器部件。 根据本发明的方面的流动套筒可以适于促进间接地连接到燃烧器头端部件。 流动套管还可以适于包括热释放槽，以适应流动套筒与流动套筒所附接的部件之间的任何不同的热膨胀或收缩。

公开(公告)号：US06705087B1

公开(公告)日：2004-03-16

申请号：US10244068

申请日：2002-09-13

Applicant: Rajeev Ohri ,  David M. Parker

Inventor： Rajeev Ohri ,  David M. Parker

IPC: F02C722

CPC classification number: F23R3/14

Abstract: A turbo machinery assembly, having a natural frequency outside of the range of operational vibrational forces and further having increased damping capability, comprises a turbo machinery component and a plate having an elongated opening defining an inner surface. The turbo machinery component has a first end and a second end; the second end having an outer profile that extends inside the opening, contacting portions of the inner surface and extending peripherally to regions of clearance with the inner surface. The second end of the turbo machinery component may also extend beyond the inner surface. The turbo machinery component may further include a sleeve having a proximal end and a distal end. The second end of the turbo machinery component extends into the sleeve through the proximal end. The distal end of the sleeve defines the second end of the turbo machinery component extending inside the inner surface.

Abstract translation: 具有在操作振动力范围之外的固有频率并且还具有增加的阻尼能力的涡轮机械组件包括涡轮机械部件和具有限定内表面的细长开口的板。 涡轮机械部件具有第一端和第二端; 所述第二端具有在所述开口内部延伸的外部轮廓，所述外部轮廓在所述内表面中延伸，并且与所述内表面的间隙的周边延伸。 涡轮机械部件的第二端也可以延伸超过内表面。 涡轮机械部件还可以包括具有近端和远端的套筒。 涡轮机械部件的第二端通过近端延伸到套筒中。 套筒的远端限定在内表面内延伸的涡轮机械部件的第二端。

公开(公告)号：US07524167B2

公开(公告)日：2009-04-28

申请号：US11418065

申请日：2006-05-04

Applicant: Rajeev Ohri ,  Plum Boonsuan

Inventor： Rajeev Ohri ,  Plum Boonsuan

IPC: F01D25/24

CPC classification number: F01D9/023

Abstract: Aspects of the invention are directed to a sealing system for the interface between a combustor liner and transition duct. The system includes a spring clip seal. A first end of the spring clip seal operatively engages the inner peripheral surface of the transition duct. A second end of the spring clip seal is indirectly attached to the liner by an insert disposed therebetween. The spring clip seal can be attached to the insert by any kind of welding process that does not involve melting of the spring clip seal and the insert, such as fillet welding. The insert and the liner can be attached in a similar manner. Because fillet welds are relatively easy to cut, the spring clip, insert and liner can be separated without the need for cutting any of these individual components. Thus, the system can facilitate the repair, disassembly and reassembly of the interface.

Abstract translation: 本发明的方面涉及用于燃烧器衬套和过渡管道之间的界面的密封系统。 该系统包括弹簧夹密封。 弹簧夹密封件的第一端可操作地接合过渡管道的内周表面。 弹簧夹密封件的第二端通过设置在其间的插入件间接附接到衬套。 弹簧夹密封件可以通过不涉及弹簧夹密封件和插入件熔化的任何种类的焊接工艺附接到插入件，例如角焊。 插入件和衬垫可以以类似的方式附接。 由于角焊缝相对易于切割，所以可以分离弹簧夹，插件和衬垫，而不需要切割这些单独的部件。 因此，该系统可以促进界面的修复，拆卸和重新组装。

公开(公告)号：US07513098B2

公开(公告)日：2009-04-07

申请号：US11169478

申请日：2005-06-29

Applicant: Rajeev Ohri ,  Kristian I. Wetzl ,  Herbert C. Reid ,  Arthur J. Harris, Jr. ,  David M. Parker ,  Stephen E. Mumford

Inventor： Rajeev Ohri ,  Kristian I. Wetzl ,  Herbert C. Reid ,  Arthur J. Harris, Jr. ,  David M. Parker ,  Stephen E. Mumford

IPC: F02C3/14 ,  F23R3/30

CPC classification number: F23R3/14

Abstract: A fuel/air mixing apparatus, such as a main swirler assembly (400) comprising a sleeve (410), provides for additional air entry around the perimeter of a bore (440) through which passes a fuel/air mixture. The additional air reduces or eliminates flashback during operation of a gas turbine comprising the assembly (400). In some embodiments, a plurality of gaps (464) exists between spaced apart tabs (462) along a downstream end (460) of the sleeve (410). During gas turbine operation, air flows through both a flashback annulus (411) and the gaps (464). In other embodiments, a plurality of holes are placed upstream and in line with the tabs (1004) to supplement the air flow through gaps (1006). In yet other embodiments, rows (1102) of holes (1104) are provided to supplement the airflow. Downstream ends (460,1218) may interface with a downstream-oriented lip (460) or with an upstream-oriented lip (1224). The interfacing may comprise a fit effective to damp vibration and to increase the natural frequency.

Abstract translation: 诸如包括套筒（410）的主旋流器组件（400）的燃料/空气混合设备提供围绕通过燃料/空气混合物的孔（440）的周边的附加空气进入。 在包括组件（400）的燃气涡轮机的操作期间，附加空气减少或消除了回火。 在一些实施例中，沿着套筒（410）的下游端（460）的间隔开的突片（462）之间存在多个间隙（464）。 在燃气轮机操作期间，空气流过回流环（411）和间隙（464）。 在其他实施例中，多个孔被放置在上游并且与突片（1004）成一直线，以补充通过间隙（1006）的空气流。 在其它实施例中，提供孔（1104）的孔（1104）以补充气流。 下游端（460,1218）可以与下游定向的唇缘（460）或与上游取向唇缘（1224）相接触。 接口可以包括有效地阻尼振动并增加固有频率的配合。

公开(公告)号：US07325402B2

公开(公告)日：2008-02-05

申请号：US10910865

申请日：2004-08-04

Applicant: David Parker ,  Rajeev Ohri ,  Plum Boonsuan

Inventor： David Parker ,  Rajeev Ohri ,  Plum Boonsuan

IPC: F02C7/22

CPC classification number: F23D14/48 ,  F23D2214/00 ,  F23R3/283 ,  F23R3/343

Abstract: A pilot nozzle heat shield includes a generally cylindrical body having a first end for receiving a pilot nozzle. The body includes a plurality of radial retention pin cavities for receiving retention pins. A frustoconical flow tip is located at a second end of the body that includes a proximal periphery and a distal periphery. A plurality of flow jets are circumferentially spaced about the proximal periphery of the frustoconical flow tip which further includes a plurality of slots extending distally from the plurality of flow jets. The plurality of slots define a plurality of tangs and the plurality of tangs define an aperture at the distal periphery of the flow tip. At least two of the tangs are connected about the distal periphery of the flow tip and the pilot nozzle heat shield generally includes at least two sets of connected tangs.

Abstract translation: 导向喷嘴热屏蔽包括大致圆柱体，其具有用于接收引燃喷嘴的第一端。 主体包括用于接收保持销的多个径向固定销腔。 截头圆锥形流动尖端位于主体的第二端，其包括近端周边和远端周边。 多个流动射流围绕截头圆锥形流动尖端的近端周向周向间隔开，其还包括从多个流动射流向远侧延伸的多个槽。 多个狭槽限定多个柄脚，并且多个柄脚在流动尖端的远端周边限定一个孔。 至少两个柄脚围绕流动尖​​端的远端周边连接，并且引燃喷嘴隔热罩通常包括至少两组连接的柄脚。

公开(公告)号：US20060174625A1

公开(公告)日：2006-08-10

申请号：US11051799

申请日：2005-02-04

Applicant: Rajeev Ohri

Inventor： Rajeev Ohri

IPC: F23R3/14

CPC classification number: F23R3/14 ,  F23R3/286 ,  F23R3/343 ,  F23R2900/00005

Abstract: A gas turbine combustor (10) comprises a main swirler assembly (400) comprising an annulus casting (410) itself comprising a modified downstream end (418) fitted into an reversed-edge base plate (450) that comprises an opening (453) defined by a lip (452) oriented upstream. The lip (452) comprises an upstream surface (457), an outboard surface (458) and an inboard surface (459). In certain embodiments the modified downstream end (418) has a shape to fit against the upstream surface (457) and the outboard surface (458) so as to increase the natural frequency of the main swirler assembly (400) to above the natural frequency of the combustion in the gas turbine combustor (10).

Abstract translation: 燃气涡轮机燃烧器（10）包括主旋流器组件（400），主旋流器组件（400）包括环形铸件（410），其包括装配到反向边缘基板（450）中的改进的下游端（418），所述改进的下游端（418）包括限定的开口（453） 通过面向上游的唇缘（452）。 唇缘（452）包括上游表面（457），外侧表面（458）和内侧表面（459）。 在某些实施例中，改进的下游端（418）具有适合抵靠上游表面（457）和外侧表面（458）的形状，以便将主旋流器组件（400）的固有频率增加到高于固有频率 燃气轮机燃烧器（10）中的燃烧。

公开(公告)号：US08127550B2

公开(公告)日：2012-03-06

申请号：US11656723

申请日：2007-01-23

Applicant: Arthur J. Harris, Jr. ,  Rajeev Ohri

Inventor： Arthur J. Harris, Jr. ,  Rajeev Ohri

IPC: F02C1/00

CPC classification number: F23R3/286 ,  F23D14/82 ,  F23R3/04 ,  F23R3/343

Abstract: A gas turbine combustor (10) comprises a base plate (12) from which protrude a plurality of lips (36) that surround respective apertures (16) into which are positioned downstream ends (19) of main swirler assemblies (18). The apertures (16) are arranged about a centrally positioned pilot cone (22) that comprises an inner cone (23) and an outer cone (25), defining a space (31) there between. A number of laterally directed apertures (60) are disposed along the outer cone (25) so as to direct a flow of fluid toward a near portion (38) of each lip (36), thereby perturbing pockets of high fuel-to-air mixtures between the outer cone (25) and the near region (38). The provision of such laterally directed apertures (60) reduces or eliminates flashback between the outer cone (25) and the near region (38) through such action.

Abstract translation: 燃气涡轮机燃烧器（10）包括基板（12），所述底板（12）突出有围绕相应孔（16）的多个唇缘（36），所述唇部位于主旋流器组件（18）的下游端部（19）。 孔（16）围绕中心定位的先导锥体（22）布置，其包括内锥体（23）和外锥体（25），在其间限定空间（31）。 多个横向定向的孔（60）沿着外锥体（25）设置，以便将流体流引向每个唇缘（36）的近部分（38），从而扰乱高燃料空气的口袋 外锥体（25）和近区域（38）之间的混合物。 通过这种动作，提供这种侧向定向的孔（60）可减少或消除外锥体（25）和近区域（38）之间的回波。