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31. 发明申请

US20110016878A1 Systems and Methods for Gas Turbine Combustors 有权
标题翻译：燃气轮机燃烧器系统与方法
公开(公告)号：US20110016878A1
公开(公告)日：2011-01-27
申请号：US12508918
申请日：2009-07-24
申请人： Jonathan Dwight Berry , Geoffrey David Myers
发明人： Jonathan Dwight Berry , Geoffrey David Myers
IPC分类号： F02C6/04 , F02C7/22
CPC分类号： F02C9/52 , F02C7/222 , F02C9/54 , F23R3/005 , F23R3/10 , F23R3/26 , F23R2900/03044
摘要： A gas turbine system comprising, a diffuser operative to diffuse an airstream output from a compressor, a fuel nozzle operative to receive fuel and emit the fuel in a combustor, and at least one bleed duct operative to direct bleed air from down stream of the combustor to the fuel nozzle.
摘要翻译：一种燃气轮机系统，包括：扩散器，其用于扩散从压缩机输出的气流;燃料喷嘴，其可操作地接收燃料并在燃烧器中发射燃料;以及至少一个排放管，其可操作以从所述燃烧器的下游引导排放空气到燃料喷嘴。

32. 发明申请

US20100205972A1 ONE-PIECE CAN COMBUSTOR WITH HEAT TRANSFER SURFACE ENHACEMENTS 审中-公开
标题翻译：一体式可加热传热表面加强型
公开(公告)号：US20100205972A1
公开(公告)日：2010-08-19
申请号：US12372246
申请日：2009-02-17
申请人： Ronald James Chila , Ronald Scott Bunker , Kevin Weston McMahan , Jonathan Dwight Berry
发明人： Ronald James Chila , Ronald Scott Bunker , Kevin Weston McMahan , Jonathan Dwight Berry
IPC分类号： F02C7/12
CPC分类号： F23R3/005 , F23R3/002
摘要： A method, system, and apparatus is provided for transferring heat from a can combustor associated with a gas turbine by providing a one-piece can combustor body having surface features that facilitate the transfer of heat away from the can combustor body, and by directing air flow to the surface features so that heat from the can combustor body is transferred from the surface features to the air flow.
摘要翻译：提供了一种方法，系统和装置，用于通过提供具有便于将热量从罐式燃烧器主体传递的表面特征的一体式罐式燃烧器主体，以及通过引导空气流到表面特征，使得来自罐式燃烧器主体的热量从表面特征传递到气流。

33. 发明申请

US20100066035A1 REUSABLE WELD JOINT FOR SYNGAS FUEL NOZZLES 有权
标题翻译：可重复使用的焊接接头用于SYNGAS燃油喷嘴
公开(公告)号：US20100066035A1
公开(公告)日：2010-03-18
申请号：US12211791
申请日：2008-09-16
申请人： Jonathan Dwight Berry , James T. Brown
发明人： Jonathan Dwight Berry , James T. Brown
IPC分类号： F16J15/02
CPC分类号： F02C7/28 , F23R3/12 , F23R3/283 , F23R2900/00002 , F23R2900/00012 , F23R2900/00017 , Y02T50/675 , Y02T50/678
摘要： A system, one embodiment, includes an annular seal configured to seal a turbine fuel nozzle to a turbine combustor, wherein the annular seal includes a first annular seal portion having an inner annular surface, a first base portion, and a first peripheral portion opposite from the first base portion. The embodiment also includes the first annular seal portion configured to couple to a second annular seal portion having an outer annular surface, a second base portion, and a second peripheral portion opposite from the second base portion. Further, the embodiment includes the first and second peripheral portions sealable by a weld.
摘要翻译：一个实施例的系统包括环形密封件，其构造成将涡轮燃料喷嘴密封到涡轮机燃烧器，其中环形密封件包括具有内环形表面的第一环形密封部分，第一基部部分和与第一周边部分相对的第一周边部分第一基部。该实施例还包括第一环形密封部分，其构造成联接到具有外环形表面的第二环形密封部分，第二基部部分和与第二基部部分相对的第二周边部分。此外，该实施例包括可通过焊接密封的第一和第二周边部分。

34. 发明授权

US09212822B2 Fuel injection assembly for use in turbine engines and method of assembling same 有权
标题翻译：用于涡轮发动机的燃油喷射组件及其组装方法
公开(公告)号：US09212822B2
公开(公告)日：2015-12-15
申请号：US13483153
申请日：2012-05-30
申请人： Jonathan Dwight Berry , Thomas Edward Johnson , William David York , Jong Ho Uhm
发明人： Jonathan Dwight Berry , Thomas Edward Johnson , William David York , Jong Ho Uhm
IPC分类号： F02C7/22 , F23R3/28
CPC分类号： F23R3/283 , F23R3/286 , Y02E20/14
摘要： A fuel injection assembly for use in a turbine engine is provided. The fuel injection assembly includes an end cover, an endcap assembly, a fluid supply chamber, and a plurality of tube assemblies positioned at the endcap assembly. Each of the tube assemblies includes housing having a fuel plenum and a cooling fluid plenum. The cooling fluid plenum is positioned downstream from the fuel plenum and separated from the fuel plenum by an intermediate wall. The plurality of tube assemblies also include a plurality of tubes that extends through the housing. Each of the plurality of tubes is coupled in flow communication with the fluid supply chamber and a combustion chamber positioned downstream from the tube assembly. The plurality of tube assemblies further includes an aft plate at a downstream end of the cooling fluid plenum. The plate includes at least one aperture.
摘要翻译：提供了一种用于涡轮发动机的燃料喷射组件。燃料喷射组件包括端盖，端盖组件，流体供应室和位于端盖组件处的多个管组件。每个管组件包括具有燃料增压室和冷却液室的壳体。冷却流体通风室位于燃料增压室的下游并与燃料气室隔开中间壁。多个管组件还包括延伸穿过壳体的多个管。多个管中的每一个与流体供应室和位于管组件下游的燃烧室流动连通地联接。多个管组件还包括在冷却流体通风室的下游端的后板。板包括至少一个孔。

35. 发明授权

US08938978B2 Gas turbine engine combustor with lobed, three dimensional contouring 有权
标题翻译：燃气涡轮发动机燃烧器具有叶片，三维轮廓
公开(公告)号：US08938978B2
公开(公告)日：2015-01-27
申请号：US13099938
申请日：2011-05-03
申请人： Donald Mark Bailey , Jonathan Dwight Berry , Luis Manuel Flamand , Kwanwoo Kim , Patrick Benedict Melton , Robert Joseph Rohrssen , John Drake Vanselow
发明人： Donald Mark Bailey , Jonathan Dwight Berry , Luis Manuel Flamand , Kwanwoo Kim , Patrick Benedict Melton , Robert Joseph Rohrssen , John Drake Vanselow
IPC分类号： F23R3/28 , F23R3/46 , F23R3/54
CPC分类号： F23R3/283 , F23D2900/00003 , F23R3/286 , F23R3/46 , F23R3/54 , F23R2900/00017 , F23R2900/00018
摘要： A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring.
摘要翻译：提供了一种燃气涡轮发动机燃烧器，其包括燃料喷嘴阵列，围绕燃料喷嘴阵列设置的燃烧壳体组件和设置在燃烧壳体组件内的端盖组件，以便与燃烧壳体组件形成轴对称的环通过所述流体行进到每个燃料喷嘴中，燃烧壳体组件和端盖组件中的至少一个形成有叶状的三维轮廓。

36. 发明授权

US08522555B2 Multi-premixer fuel nozzle support system 有权
标题翻译：多预混合燃料喷嘴支撑系统
公开(公告)号：US08522555B2
公开(公告)日：2013-09-03
申请号：US12469507
申请日：2009-05-20
申请人： Jonathan Dwight Berry , Kevin Weston McMahan , Carl Robert Barker
发明人： Jonathan Dwight Berry , Kevin Weston McMahan , Carl Robert Barker
IPC分类号： F23R3/14
CPC分类号： F23R3/10 , F23R3/286
摘要： A system comprising a fuel nozzle. The fuel nozzle includes a mounting base and an inlet flow conditioner extending directly from the mounting base in a downstream direction. Moreover, the inlet flow conditioner structurally supports the fuel nozzle without a central support member extending directly from the mounting base inside the inlet flow conditioner.
摘要翻译：一种包括燃料喷嘴的系统。燃料喷嘴包括安装基座和沿着下游方向从安装基座直接延伸的入口流动调节器。此外，入口流动调节器结构地支撑燃料喷嘴，而没有直接从入口流动调节器内的安装基座延伸的中心支撑构件。

37. 发明申请

US20130167539A1 FUEL NOZZLES FOR INJECTING FUEL IN A GAS TURBINE COMBUSTOR 有权
标题翻译：燃油喷嘴用于燃气涡轮机燃油喷射
公开(公告)号：US20130167539A1
公开(公告)日：2013-07-04
申请号：US13343417
申请日：2012-01-04
申请人： Jonathan Dwight Berry
发明人： Jonathan Dwight Berry
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F23D2900/00008 , Y02E20/16
摘要： Fuel nozzles for gas turbines are provided that include liquid fuel cartridges. In one embodiment, a fuel nozzle includes a fuel plenum plate separating an air plenum from a fuel plenum. The fuel nozzle also includes a plurality of mixing tubes extending through the fuel plenum from the fuel plenum plate to a face plate. Each mixing tube includes an air inlet configured to receive air from the air plenum, a fuel inlet disposed in a tube wall within the fuel plenum to direct fuel from the fuel plenum into the mixing tube to produce a fuel-air mixture, and a fuel-air outlet configured to discharge the fuel-air mixture away from the face plate into a combustion region. The fuel nozzle further includes a liquid fuel cartridge extending through the air plenum and the fuel plenum to the face plate. The liquid fuel cartridge includes a liquid fuel passage.
摘要翻译：提供了用于燃气轮机的燃料喷嘴，其包括液体燃料盒。在一个实施例中，燃料喷嘴包括将空气增压室与燃料增压室分开的燃料增压板。燃料喷嘴还包括多个混合管，其通过燃料增压室从燃料增压板延伸到面板。每个混合管包括被配置为从空气压力室接收空气的空气入口，设置在燃料增压室内的管壁中的燃料入口以将来自燃料增压室的燃料引导到混合管中以产生燃料 - 空气混合物，以及燃料空气出口构造成将燃料 - 空气混合物从面板排出到燃烧区域中。燃料喷嘴还包括延伸穿过空气压力室和燃料增压室到液面板的液体燃料盒。液体燃料盒包括液体燃料通道。

38. 发明申请

US20130086912A1 SYSTEM FOR COOLING A MULTI-TUBE FUEL NOZZLE 有权
标题翻译：用于冷却多管燃料喷嘴的系统
公开(公告)号：US20130086912A1
公开(公告)日：2013-04-11
申请号：US13267828
申请日：2011-10-06
申请人： Jonathan Dwight Berry
发明人： Jonathan Dwight Berry
IPC分类号： F02C7/22 , B05B7/00
CPC分类号： F23R3/283 , F23D2214/00 , F23R3/286 , F23R2900/03043 , F23R2900/03044 , Y02T50/675
摘要： A system includes a multi-tube fuel nozzle including a fuel nozzle head that includes an outer wall surrounding a chamber. The outer wall includes a downstream wall portion configured to face a combustion region. The multi-tube fuel nozzle also includes multiple tubes extending through the chamber to the downstream wall portion. Each tube of the multiple tubes includes an upstream portion, a downstream portion, and at least one fuel inlet disposed at the upstream portion, and is configured to receive air and mix the air with fuel from the at least one fuel inlet. The multi-tube fuel nozzle includes a fuel conduit extending through the chamber crosswise to and around the multiple tubes. The fuel conduit includes multiple impingement cooling orifices. A fuel flow path extends through the fuel conduit, through the impingement cooling orifices, through the chamber, and into the at least one fuel inlet of each tube.
摘要翻译：一种系统包括多管燃料喷嘴，其包括燃料喷嘴头，燃料喷嘴头包括围绕室的外壁。外壁包括构造成面对燃烧区域的下游壁部分。多管燃料喷嘴还包括多个管，其延伸穿过室至下游壁部分。多个管的每个管包括上游部分，下游部分和设置在上游部分处的至少一个燃料入口，并且构造成接收空气并将空气与来自至少一个燃料入口的燃料混合。该多管燃料喷嘴包括一个燃料管道，该燃料管道横跨多个管道并围绕多个管道延伸穿过该腔室。燃料管道包括多个冲击冷却孔。燃料流动路径延伸穿过燃料管道，穿过冲击冷却孔通过室，并且进入每个管的至少一个燃料入口。

39. 发明申请

US20120279223A1 Fuel Injector and Support Plate 有权
标题翻译：燃油喷射器和支撑板
公开(公告)号：US20120279223A1
公开(公告)日：2012-11-08
申请号：US13099853
申请日：2011-05-03
申请人： Carl Robert Barker , Thomas Edward Johnson , Jonathan Dwight Berry
发明人： Carl Robert Barker , Thomas Edward Johnson , Jonathan Dwight Berry
IPC分类号： F02C7/22 , F23R3/28 , B23P17/00
CPC分类号： F23R3/283 , F23R3/286 , F23R3/34 , F23R3/46 , F23R2900/00014 , F23R2900/00017
摘要： An integrated plate is provided for use with a combustor including a casing, a fuel plenum extending circumferentially about the casing, and a fuel nozzle extending axially through the casing. The integrated plate includes a plurality of fuel injection pegs that extend radially between the fuel plenum and the fuel nozzle.
摘要翻译：提供了一种集成板，其用于燃烧器，所述燃烧器包括壳体，围绕壳体周向延伸的燃料增压室和沿轴向延伸穿过壳体的燃料喷嘴。集成板包括在燃料室和燃料喷嘴之间径向延伸的多个燃料喷射栓。

40. 发明授权

US08276391B2 Combustor liner cooling at transition duct interface and related method 有权
标题翻译：过渡管道界面的燃烧器衬管冷却及相关方法
公开(公告)号：US08276391B2
公开(公告)日：2012-10-02
申请号：US12762842
申请日：2010-04-19
申请人： Jonathan Dwight Berry , Kara Johnston Edwards , Heath Michael Ostebee
发明人： Jonathan Dwight Berry , Kara Johnston Edwards , Heath Michael Ostebee
IPC分类号： F02C7/18 , F23R3/46
CPC分类号： F23R3/002 , F23R3/04
摘要： A resilient annular seal structure is disposed radially between an aft end portion of a combustor liner and a forward end portion of a transition piece, the resilient annular seal structure configured to form a first annular cavity radially between the forward end portion of the transition piece and the aft end portion of said combustor. At least one transfer tube radially extends from the second flow sleeve through the second flow annulus to the transition piece, and is arranged to supply compressor discharge cooling air radially from an area outside the first and second substantially axially extending flow annuli directly to the resilient annular seal structure and to the aft end of the combustor liner.
摘要翻译：弹性环形密封结构径向设置在燃烧器衬套的后端部分与过渡件的前端部分之间，该弹性环形密封结构构造成在过渡件的前端部分和所述燃烧器的后端部分。至少一个传送管从第二流动套管径向地延伸穿过第二流动环到过渡件，并且被布置成将压缩机排出冷却空气从第一和第二大致轴向延伸的流动环的外部径向径向地供应到弹性环密封结构和燃烧器衬套的后端。

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