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1. 发明授权

US09182123B2 Combustor fuel nozzle and method for supplying fuel to a combustor 有权
标题翻译：燃烧器燃料喷嘴和用于向燃烧器供应燃料的方法
公开(公告)号：US09182123B2
公开(公告)日：2015-11-10
申请号：US13344033
申请日：2012-01-05
申请人： Gregory Allen Boardman , Ronald James Chila , Johnie F. McConnaughhay
发明人： Gregory Allen Boardman , Ronald James Chila , Johnie F. McConnaughhay
IPC分类号： F23R3/14 , F23R3/28
CPC分类号： F23R3/14 , F23R3/286
摘要： A combustor fuel nozzle includes a center body and an inner shroud that circumferentially surrounds at least a portion of the center body. The inner shroud has a downstream surface. The fuel nozzle includes an inner passage between the center body and the inner shroud, an outer passage that circumferentially surrounds at least a portion of the inner shroud and a first plurality of fuel ports extending substantially radially outward through the center body. The first plurality of fuel ports is upstream from the downstream surface of the inner shroud. A method for supplying fuel to a combustor fuel nozzle includes flowing a working fluid through an inner passage between a center body and an inner shroud, injecting a fuel from the center body against the inner shroud, and flowing a portion of the working fluid through an outer passage that surrounds at least a portion of the inner shroud.
摘要翻译：燃烧器燃料喷嘴包括中心体和周向围绕中心体的至少一部分的内护罩。内护罩具有下游表面。燃料喷嘴包括在中心体和内护罩之间的内通道，周向围绕内护罩的至少一部分的外通道和基本上径向向外延伸穿过中心体的第一多个燃料口。第一多个燃料口在内护罩的下游表面上游。向燃烧器燃料喷嘴供给燃料的方法包括使工作流体流过中心体和内护罩之间的内部通道，将燃料从中心体喷射到内护罩上，并使工作流体的一部分流过外通道围绕内护罩的至少一部分。

2. 发明申请

US20130174563A1 COMBUSTOR FUEL NOZZLE AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR 有权
标题翻译：燃烧器燃料喷嘴和向燃烧器供应燃料的方法
公开(公告)号：US20130174563A1
公开(公告)日：2013-07-11
申请号：US13344033
申请日：2012-01-05
申请人： Gregory Allen Boardman , Ronald James Chila , Johnie F. McConnaughhay
发明人： Gregory Allen Boardman , Ronald James Chila , Johnie F. McConnaughhay
IPC分类号： F23R3/28 , F02C7/22
CPC分类号： F23R3/14 , F23R3/286
摘要： A combustor fuel nozzle includes a center body and an inner shroud that circumferentially surrounds at least a portion of the center body. The inner shroud has a downstream surface. The fuel nozzle includes an inner passage between the center body and the inner shroud, an outer passage that circumferentially surrounds at least a portion of the inner shroud and a first plurality of fuel ports extending substantially radially outward through the center body. The first plurality of fuel ports is upstream from the downstream surface of the inner shroud. A method for supplying fuel to a combustor fuel nozzle includes flowing a working fluid through an inner passage between a center body and an inner shroud, injecting a fuel from the center body against the inner shroud, and flowing a portion of the working fluid through an outer passage that surrounds at least a portion of the inner shroud.
摘要翻译：燃烧器燃料喷嘴包括中心体和周向围绕中心体的至少一部分的内护罩。内护罩具有下游表面。燃料喷嘴包括在中心体和内护罩之间的内通道，周向围绕内护罩的至少一部分的外通道和基本上径向向外延伸穿过中心体的第一多个燃料口。第一多个燃料口在内护罩的下游表面上游。向燃烧器燃料喷嘴供给燃料的方法包括使工作流体流过中心体和内护罩之间的内部通道，将燃料从中心体喷射到内护罩上，并使工作流体的一部分流过外通道围绕内护罩的至少一部分。

3. 发明授权

US09212823B2 Systems and methods for suppressing combustion driven pressure fluctuations with a premix combustor having multiple premix times 有权
标题翻译：用具有多个预混时间的预混合燃烧器抑制燃烧驱动的压力波动的系统和方法
公开(公告)号：US09212823B2
公开(公告)日：2015-12-15
申请号：US13604952
申请日：2012-09-06
申请人： Gregory Allen Boardman , Ronald James Chila , Mark Allan Hadley , Johnie Franklin McConnaughhay , Sarah Lori Crothers
发明人： Gregory Allen Boardman , Ronald James Chila , Mark Allan Hadley , Johnie Franklin McConnaughhay , Sarah Lori Crothers
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F23R2900/00014 , F23R2900/03043 , F23R2900/03045
摘要： A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the combustor liner and a plurality of nozzles are disposed at predetermined locations on the flow channels. The locations of the nozzles are selected to provide different mixing times for fuel injected through the nozzles.
摘要翻译：具有燃烧室的燃烧器设置有外部流动套筒和围绕燃烧室的燃烧室衬套。多个流动通道设置在燃烧器衬套上，并且多个喷嘴设置在流动通道上的预定位置处。选择喷嘴的位置以为通过喷嘴喷射的燃料提供不同的混合时间。

4. 发明申请

US20140060063A1 Systems and Methods For Suppressing Combustion Driven Pressure Fluctuations With a Premix Combustor Having Multiple Premix Times 有权
标题翻译：用具有多个预混时间的预混合燃烧器抑制燃烧驱动的压力波动的系统和方法
公开(公告)号：US20140060063A1
公开(公告)日：2014-03-06
申请号：US13604952
申请日：2012-09-06
申请人： Gregory Allen Boardman , Ronald James Chila , Mark Allan Hadley , Johnie Franklin McConnaughhay , Sarah Lori Crothers
发明人： Gregory Allen Boardman , Ronald James Chila , Mark Allan Hadley , Johnie Franklin McConnaughhay , Sarah Lori Crothers
IPC分类号： F23R3/28 , F23R3/00 , F02C7/22
CPC分类号： F23R3/286 , F23R2900/00014 , F23R2900/03043 , F23R2900/03045
摘要： A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the combustor liner and a plurality of nozzles are disposed at predetermined locations on the flow channels. The locations of the nozzles are selected to provide different mixing times for fuel injected through the nozzles.
摘要翻译：具有燃烧室的燃烧器设置有外部流动套筒和围绕燃烧室的燃烧室衬套。多个流动通道设置在燃烧器衬套上，并且多个喷嘴设置在流动通道上的预定位置处。选择喷嘴的位置以为通过喷嘴喷射的燃料提供不同的混合时间。

5. 发明申请

US20110113783A1 PREMIXING APPARATUS FOR FUEL INJECTION IN A TURBINE ENGINE 有权
标题翻译：涡轮发动机燃油喷射优先装置
公开(公告)号：US20110113783A1
公开(公告)日：2011-05-19
申请号：US12618636
申请日：2009-11-13
申请人： Gregory Allen Boardman , David Martin Johnson , Ronald James Chila , Nishant Govindbhai Parsania , Hasan Karim , Joseph Citeno
发明人： Gregory Allen Boardman , David Martin Johnson , Ronald James Chila , Nishant Govindbhai Parsania , Hasan Karim , Joseph Citeno
IPC分类号： F02C7/00 , F02C7/22
CPC分类号： F23R3/40 , F23C13/06 , F23R3/286
摘要： In one embodiment, a system includes a fuel nozzle that includes a fuel injector that includes a fuel port and a premixer tube. The premixer tube includes a wall disposed about a central passage, multiple air ports extending through the wall into the central passage, and a catalytic region. The catalytic region includes a catalyst, disposed inside the wall along the central passage, configured to increase a reaction of fuel and air.
摘要翻译：在一个实施例中，系统包括燃料喷嘴，其包括燃料喷射器，燃料喷射器包括燃料口和预混合管。预混合管包括围绕中心通道设置的壁，多个空气端口延伸穿过壁进入中心通道，以及催化区域。催化区域包括沿着中心通道设置在壁内的催化剂，构造成增加燃料和空气的反应。

6. 发明申请

US20110289933A1 Hybrid Prefilming Airblast, Prevaporizing, Lean-Premixing Dual-Fuel Nozzle for a Gas Turbine Combustor 有权
标题翻译：用于燃气轮机燃烧器的混合预吹风机，预蒸发，预混合双燃料喷嘴
公开(公告)号：US20110289933A1
公开(公告)日：2011-12-01
申请号：US12787990
申请日：2010-05-26
申请人： Gregory Allen Boardman , Ronald James Chila , Michael John Hughes , Jason Thurman Stewart
发明人： Gregory Allen Boardman , Ronald James Chila , Michael John Hughes , Jason Thurman Stewart
IPC分类号： F02C7/26 , F02C7/22
CPC分类号： F23R3/36 , F23D2900/11101 , F23D2900/14004 , F23R3/14 , F23R3/286
摘要： A dual fuel nozzle for a gas turbine combustor includes a hub defining a fuel inlet and a plurality of liquid fuel jets disposed at a downstream end of the hub. The fuel jets are oriented to eject liquid fuel radially outward from the hub. An annular air passage includes a swirler that imparts swirl to air flowing in the annular air passage, and a splitter ring is disposed in the annular air passage and surrounds the plurality of liquid fuel jets. The nozzle allows liquid fuels to be injected into a swirling annular airstream and then atomized, dispersed and vaporized inside a lean premixing dual fuel nozzle for a gas turbine combustor.
摘要翻译：用于燃气轮机燃烧器的双燃料喷嘴包括限定燃料入口的轮毂和设置在轮毂的下游端的多个液体燃料喷嘴。燃料喷嘴被定向成从轮毂径向向外喷射液体燃料。环形空气通道包括向在环形空气通道中流动的空气产生漩涡的旋流器，并且分离环设置在环形空气通道中并围绕多个液体燃料喷嘴。喷嘴允许将液体燃料注入旋转的环形空气流中，然后在用于燃气轮机燃烧器的贫预混合双燃料喷嘴内雾化，分散和蒸发。

7. 发明授权

US08683804B2 Premixing apparatus for fuel injection in a turbine engine 有权
标题翻译：用于在涡轮发动机中燃料喷射的预混合装置
公开(公告)号：US08683804B2
公开(公告)日：2014-04-01
申请号：US12618636
申请日：2009-11-13
申请人： Gregory Allen Boardman , David Martin Johnson , Ronald James Chila , Nishant Govindbhai Parsania , Hasan Karim , Joseph Citeno
发明人： Gregory Allen Boardman , David Martin Johnson , Ronald James Chila , Nishant Govindbhai Parsania , Hasan Karim , Joseph Citeno
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/40 , F23C13/06 , F23R3/286
摘要： In one embodiment, a system includes a fuel nozzle that includes a fuel injector that includes a fuel port and a premixer tube. The premixer tube includes a wall disposed about a central passage, multiple air ports extending through the wall into the central passage, and a catalytic region. The catalytic region includes a catalyst, disposed inside the wall along the central passage, configured to increase a reaction of fuel and air.
摘要翻译：在一个实施例中，系统包括燃料喷嘴，其包括燃料喷射器，燃料喷射器包括燃料口和预混合管。预混合管包括围绕中心通道设置的壁，多个空气端口延伸穿过壁进入中心通道，以及催化区域。催化区域包括沿着中心通道设置在壁内的催化剂，构造成增加燃料和空气的反应。

8. 发明授权

US08671691B2 Hybrid prefilming airblast, prevaporizing, lean-premixing dual-fuel nozzle for gas turbine combustor 有权
标题翻译：用于燃气轮机燃烧器的混合预吹风机，预蒸发，预混合双燃料喷嘴
公开(公告)号：US08671691B2
公开(公告)日：2014-03-18
申请号：US12787990
申请日：2010-05-26
申请人： Gregory Allen Boardman , Ronald James Chila , Michael John Hughes , Jason Thurman Stewart
发明人： Gregory Allen Boardman , Ronald James Chila , Michael John Hughes , Jason Thurman Stewart
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/36 , F23D2900/11101 , F23D2900/14004 , F23R3/14 , F23R3/286
摘要： A dual fuel nozzle for a gas turbine combustor includes a hub defining a fuel inlet and a plurality of liquid fuel jets disposed at a downstream end of the hub. The fuel jets are oriented to eject liquid fuel radially outward from the hub. An annular air passage includes a swirler that imparts swirl to air flowing in the annular air passage, and a splitter ring is disposed in the annular air passage and surrounds the plurality of liquid fuel jets. The nozzle allows liquid fuels to be injected into a swirling annular airstream and then atomized, dispersed and vaporized inside a lean premixing dual fuel nozzle for a gas turbine combustor.
摘要翻译：用于燃气轮机燃烧器的双燃料喷嘴包括限定燃料入口的轮毂和设置在轮毂的下游端的多个液体燃料喷嘴。燃料喷嘴被定向成从轮毂径向向外喷射液体燃料。环形空气通道包括向在环形空气通道中流动的空气产生漩涡的旋流器，并且分离环设置在环形空气通道中并围绕多个液体燃料喷嘴。喷嘴允许将液体燃料注入旋转的环形空气流中，然后在用于燃气轮机燃烧器的贫预混合双燃料喷嘴内雾化，分散和蒸发。

9. 发明授权

US08646276B2 Combustor assembly for a turbine engine with enhanced cooling 有权
标题翻译：用于具有增强冷却的涡轮发动机的燃烧器组件
公开(公告)号：US08646276B2
公开(公告)日：2014-02-11
申请号：US12616304
申请日：2009-11-11
申请人： Lewis Berkley Davis, Jr. , Ronald James Chila
发明人： Lewis Berkley Davis, Jr. , Ronald James Chila
IPC分类号： F02C1/00
CPC分类号： F23R3/005 , F23R3/06 , F23R3/54 , F23R2900/03043 , F23R2900/03044
摘要： A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A plurality of cooling holes are formed through the flow sleeve to allow compressed air to flow from a position outside the flow sleeve, through the cooling holes, and into the annular space. The height of the annular space may vary along the length of the combustor assembly. Thus, the flow sleeve may have reduced diameter portions which result in the height of the annular space being smaller in certain locations than at other locations along the length of the combustor assembly.
摘要翻译：用于涡轮发动机的燃烧器组件包括燃烧器衬套和围绕燃烧器衬套的流动套管。压缩空气流过位于燃烧器衬套的外表面和流动套管的内表面之间的环形空间。通过流动套筒形成多个冷却孔，以允许压缩空气从流动套筒外部的位置流过冷却孔并进入环形空间。环形空间的高度可以沿着燃烧器组件的长度而变化。因此，流动套管可以具有减小的直径部分，这导致环形空间的高度在某些位置比沿着燃烧器组件的长度的其它位置更小。

10. 发明申请

US20130086915A1 FILM COOLED COMBUSTION LINER ASSEMBLY 审中-公开
标题翻译：薄膜冷却燃料内衬组件
公开(公告)号：US20130086915A1
公开(公告)日：2013-04-11
申请号：US13267994
申请日：2011-10-07
申请人： David William Cihlar , Ronald James Chila , Patrick Benedict Melton , William David York
发明人： David William Cihlar , Ronald James Chila , Patrick Benedict Melton , William David York
IPC分类号： F02C7/18
CPC分类号： F23R3/002 , F01D9/023 , F05D2240/55 , F23R3/06 , F23R3/46 , F23R2900/00012 , F23R2900/03042 , F23R2900/03044
摘要： A combustion liner assembly is provided and includes a combustion liner and a transition piece. A portion of the transition piece is circumferentially disposed around a portion of the combustion liner. A seal is attached to the transition piece, and the seal is configured to apply a compressive force to an aft end of the combustion liner.
摘要翻译：提供燃烧衬套组件并且包括燃烧衬套和过渡件。过渡件的一部分周向地布置在燃烧衬套的一部分周围。密封件附接到过渡件，并且密封件构造成对燃烧衬套的后端施加压缩力。

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