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1. 发明申请

US20130025289A1 COMBUSTOR PORTION FOR A TURBOMACHINE AND METHOD OF OPERATING A TURBOMACHINE 有权
标题翻译：涡轮机的燃烧器部件和操作涡轮机的方法
公开(公告)号：US20130025289A1
公开(公告)日：2013-01-31
申请号：US13193865
申请日：2011-07-29
申请人： Joseph Citeno , Dmitry Alexandrovitch Lysenko , Sergey Anatolievich Meshkov , Valery Alexandrovich Mitrofanov , Almaz Valeev
发明人： Joseph Citeno , Dmitry Alexandrovitch Lysenko , Sergey Anatolievich Meshkov , Valery Alexandrovich Mitrofanov , Almaz Valeev
IPC分类号： F02C7/22
CPC分类号： F23R3/286 , F23R3/343 , F23R3/346
摘要： A turbomachine combustor portion includes a combustion chamber. A center injection nozzle is arranged within the combustion chamber and includes a center nozzle inlet and a center nozzle outlet. An outer premixed injection nozzle is positioned radially outward of the center injection nozzle and includes an outer nozzle inlet and an outer nozzle outlet that is arranged upstream of the center nozzle outlet. A late lean injector is positioned downstream of the center nozzle and the outer premixed nozzle. The combustor portion includes a first combustion zone arranged downstream of the outer nozzle outlet, a second combustion zone arranged downstream of the center nozzle outlet, and a third combustion zone arranged further downstream of the center nozzle outlet. The center injection nozzle, outer premixed injection nozzle, and late lean injector are selectively operated to establish a combustion flame front in the first, second, and third combustion zones.
摘要翻译：涡轮机燃烧器部分包括燃烧室。中心喷嘴设置在燃烧室内，并包括中心喷嘴入口和中心喷嘴出口。外部预混合喷嘴位于中心喷嘴的径向外侧，并且包括布置在中心喷嘴出口上游的外喷嘴入口和外喷嘴出口。后期的稀薄喷射器位于中心喷嘴和外部预混喷嘴的下游。燃烧器部分包括布置在外部喷嘴出口下游的第一燃烧区域，布置在中心喷嘴出口下游的第二燃烧区域和布置在中心喷嘴出口下游的第三燃烧区域。选择性地操作中心注射喷嘴，外部预混合喷嘴和后部稀薄喷射器，以在第一，第二和第三燃烧区域中建立燃烧火焰前沿。

2. 发明授权

US09297534B2 Combustor portion for a turbomachine and method of operating a turbomachine 有权
标题翻译：用于涡轮机的燃烧器部分和操作涡轮机的方法
公开(公告)号：US09297534B2
公开(公告)日：2016-03-29
申请号：US13193865
申请日：2011-07-29
申请人： Joseph Citeno , Dmitry Alexandrovitch Lysenko , Sergey Anatolievich Meshkov , Valery Alexandrovich Mitrofanov , Almaz Valeev
发明人： Joseph Citeno , Dmitry Alexandrovitch Lysenko , Sergey Anatolievich Meshkov , Valery Alexandrovich Mitrofanov , Almaz Valeev
IPC分类号： F23R3/34 , F23R3/28
CPC分类号： F23R3/286 , F23R3/343 , F23R3/346
摘要： A turbomachine combustor portion includes a combustion chamber. A center injection nozzle is arranged within the combustion chamber and includes a center nozzle inlet and a center nozzle outlet. An outer premixed injection nozzle is positioned radially outward of the center injection nozzle and includes an outer nozzle inlet and an outer nozzle outlet that is arranged upstream of the center nozzle outlet. A late lean injector is positioned downstream of the center nozzle and the outer premixed nozzle. The combustor portion includes a first combustion zone arranged downstream of the outer nozzle outlet, a second combustion zone arranged downstream of the center nozzle outlet, and a third combustion zone arranged further downstream of the center nozzle outlet. The center injection nozzle, outer premixed injection nozzle, and late lean injector are selectively operated to establish a combustion flame front in the first, second, and third combustion zones.
摘要翻译：涡轮机燃烧器部分包括燃烧室。中心喷嘴设置在燃烧室内，并包括中心喷嘴入口和中心喷嘴出口。外部预混合喷嘴位于中心喷嘴的径向外侧，并且包括布置在中心喷嘴出口上游的外喷嘴入口和外喷嘴出口。后期的稀薄喷射器位于中心喷嘴和外部预混喷嘴的下游。燃烧器部分包括布置在外部喷嘴出口下游的第一燃烧区域，布置在中心喷嘴出口下游的第二燃烧区域和布置在中心喷嘴出口下游的第三燃烧区域。选择性地操作中心注射喷嘴，外部预混合喷嘴和后部稀薄喷射器，以在第一，第二和第三燃烧区域中建立燃烧火焰前沿。

3. 发明申请

US20110197591A1 AXIALLY STAGED PREMIXED COMBUSTION CHAMBER 审中-公开
标题翻译：轴向预热燃烧室
公开(公告)号：US20110197591A1
公开(公告)日：2011-08-18
申请号：US13025307
申请日：2011-02-11
申请人： Almaz Valeev , Sergey Anatolievich Meshkov , Mark Hadley , Stanley Widener , Geoffrey Myers , Valery Alexandrovich Mitrofanov
发明人： Almaz Valeev , Sergey Anatolievich Meshkov , Mark Hadley , Stanley Widener , Geoffrey Myers , Valery Alexandrovich Mitrofanov
IPC分类号： F23R3/28
CPC分类号： F23R3/46 , F23R3/286 , F23R3/343
摘要： A combustor for a gas turbine includes a plurality of radially outer nozzles arranged in an annular array, each of the radially outer nozzles having an outlet end located to supply fuel and/or air to a first combustion chamber. A center nozzle has an outlet end located axially upstream of the outlet ends of the radially outer nozzles, and is configured and arranged to supply fuel and air to a second combustion chamber axially upstream of the first combustion chamber. The second combustion chamber opens into the first combustion chamber and has a length sufficient to maintain a center nozzle flame confined to the second combustion chamber.
摘要翻译：用于燃气涡轮机的燃烧器包括布置成环形阵列的多个径向外部喷嘴，每个径向外部喷嘴具有位于将燃料和/或空气供应到第一燃烧室的出口端。中心喷嘴具有位于径向外部喷嘴的出口端的轴向上游的出口端，并且构造和布置成将燃料和空气供应到在第一燃烧室的轴向上游的第二燃烧室。第二燃烧室通向第一燃烧室，并具有足以将中心喷嘴火焰保持在第二燃烧室中的长度。

4. 发明申请

US20110225948A1 APPARATUS FOR HIGH-FREQUENCY ELECTROMAGNETIC INITIATION OF A COMBUSTION PROCESS 审中-公开
标题翻译：燃烧过程高频电磁启动装置
公开(公告)号：US20110225948A1
公开(公告)日：2011-09-22
申请号：US13036040
申请日：2011-02-28
申请人： Almaz Kamilevich Valeev , Sergey Adolfovich Oskin , Sergey Anatolievich Meshkov , Valery Alexandrovich Mitrofanov , Dmitry Vladlenovich Tretvakov
发明人： Almaz Kamilevich Valeev , Sergey Adolfovich Oskin , Sergey Anatolievich Meshkov , Valery Alexandrovich Mitrofanov , Dmitry Vladlenovich Tretvakov
IPC分类号： F02C7/264
CPC分类号： F23R3/286 , F23C99/001 , F23D2900/00014 , F23D2900/00015 , F23R2900/00002
摘要： Apparatus for providing electromagnetic radiation to a combustor during a combustion process are disclosed. An electromagnetic radiation source delivers electromagnetic radiation through a first waveguide to a second waveguide that includes an electromagnetic radiation outlet positioned to deliver electromagnetic radiation to the interior of the combustor. Electromagnetic radiation is delivered to low temperature regions of a combustor to reduce carbon monoxide (CO) and unburned hydrocarbon (UHC) emissions. In addition, the electromagnetic radiation stimulates the combustion process so that lean air-fuel mixtures and low BTU gases can be burned at lower combustion temperatures leading to reduced NOx emissions.
摘要翻译：公开了一种在燃烧过程中向燃烧器提供电磁辐射的装置。电磁辐射源将电磁辐射通过第一波导传送到第二波导，该第二波导包括电磁辐射出口，定位成将电磁辐射传送到燃烧器的内部。电磁辐射被传送到燃烧器的低温区域以减少一氧化碳（CO）和未燃烧的烃（UHC）排放物。此外，电磁辐射刺激燃烧过程，使得稀薄的空气 - 燃料混合物和低BTU气体可以在较低的燃烧温度下燃烧，导致减少的NOx排放。

5. 发明申请

US20110173984A1 GAS TURBINE TRANSITION PIECE AIR BYPASS BAND ASSEMBLY 审中-公开
标题翻译：气体涡轮转换带空气旁路带总成
公开(公告)号：US20110173984A1
公开(公告)日：2011-07-21
申请号：US12917561
申请日：2010-11-02
申请人： Almaz Valeev , Leonid Ginessin , Sergey Anatolievich Meshkov
发明人： Almaz Valeev , Leonid Ginessin , Sergey Anatolievich Meshkov
IPC分类号： F01D25/24
CPC分类号： F01D9/023 , F01D17/141 , F02C9/18 , F05D2250/411
摘要： An air bypass band assembly includes a transition piece of a gas turbine, the transition piece having at least one opening therein to allow a flow of air to pass through the at least one opening. The air bypass band assembly also includes a band that is movable between at least two positions, a first one of the at least two positions being a closed position where the at least one opening is closed to prevent the flow of air from flowing through the at least one opening, a second one of the at least two positions being an open where the at least one opening is opened to allow the flow of air to flow through the at least one opening. The air bypass band assembly further includes a mechanism that moves the band between the at least two positions.
摘要翻译：空气旁路带组件包括燃气轮机的过渡件，所述过渡件在其中具有至少一个开口，以允许空气流通过所述至少一个开口。空气旁路带组件还包括能够在至少两个位置之间移动的带，所述至少两个位置中的第一位置是闭合位置，其中所述至少一个开口被封闭，以防止空气流通过至少一个开口，所述至少两个位置中的第二位置是开放的，其中所述至少一个开口被打开以允许空气流通过所述至少一个开口。空气旁通带组件还包括使带在至少两个位置之间移动的机构。

6. 发明授权

US08276386B2 Apparatus and method for a combustor 有权
标题翻译：燃烧器的装置和方法
公开(公告)号：US08276386B2
公开(公告)日：2012-10-02
申请号：US12889512
申请日：2010-09-24
申请人： Willy Steve Ziminsky , Christopher Edward Wolfe , Sergey Anatolievich Meshkov , Sergey Adolfovich Oskin
发明人： Willy Steve Ziminsky , Christopher Edward Wolfe , Sergey Anatolievich Meshkov , Sergey Adolfovich Oskin
IPC分类号： F02C7/08
CPC分类号： F23R3/16
摘要： A combustor includes an end cover and a combustion chamber downstream of the end cover. The combustor further includes nozzles disposed radially in the end cover and a shroud surrounding at least one of the nozzles and extending downstream into the combustion chamber. The shroud includes an inner wall surface and an outer wall surface. A method for operating a combustor includes flowing compressed working fluid through nozzles into a combustion chamber, flowing fuel through each nozzle in a first subset of the nozzles into the combustion chamber, and igniting the fuel from each nozzle in the first subset of nozzles in the combustion chamber. In addition, the method includes extending into the combustion chamber a separate shroud around each nozzle in a second subset of the nozzles and isolating fuel to each nozzle in the second subset of nozzles.
摘要翻译：燃烧器包括端盖和端盖下游的燃烧室。燃烧器还包括径向设置在端盖中的喷嘴和围绕至少一个喷嘴并在下游延伸到燃烧室中的护罩。护罩包括内壁表面和外壁表面。一种用于操作燃烧器的方法包括将压缩的工作流体通过喷嘴流入燃烧室，使燃料通过喷嘴的第一子集中的每个喷嘴流入燃烧室，并且从喷嘴的第一子集中的每个喷嘴点燃燃料燃烧室。此外，该方法包括在喷嘴的第二子集中的每个喷嘴周围延伸到燃烧室中的单独的护罩，并将燃料与第二喷嘴子集中的每个喷嘴隔离。

7. 发明申请

US20090049838A1 TURBINE FUEL DELIVERY APPARATUS AND SYSTEM 有权
标题翻译：涡轮燃油输送装置和系统
公开(公告)号：US20090049838A1
公开(公告)日：2009-02-26
申请号：US11842603
申请日：2007-08-21
申请人： Sergey Adolfovich Oskin , Mark Allan Hadley , Joel Meador Hall , Sergey Konstantinovich Yerokhin , Sergey Anatolievich Meshkov
发明人： Sergey Adolfovich Oskin , Mark Allan Hadley , Joel Meador Hall , Sergey Konstantinovich Yerokhin , Sergey Anatolievich Meshkov
IPC分类号： F02C7/22
CPC分类号： F23R3/14 , F23R3/28
摘要： A fuel nozzle for a turbine is disclosed. The fuel nozzle includes a housing, a plurality of fuel passages disposed within the housing, and a plurality of air passages disposed within the housing. A total flow area of the plurality of fuel passages is substantially equal to a total flow area of the plurality of air passages.
摘要翻译：公开了一种用于涡轮机的燃料喷嘴。燃料喷嘴包括壳体，设置在壳体内的多个燃料通道以及设置在壳体内的多个空气通道。多个燃料通道的总流动面积基本上等于多个空气通道的总流动面积。

8. 发明授权

US09822649B2 Integrated combustor and stage 1 nozzle in a gas turbine and method 有权
公开(公告)号：US09822649B2
公开(公告)日：2017-11-21
申请号：US12269411
申请日：2008-11-12
申请人： Lewis Berkley Davis, Jr. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
发明人： Lewis Berkley Davis, Jr. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
IPC分类号： F01C1/00 , F01D9/02 , F01D9/04 , F23R3/00 , F23R3/28 , F23R3/46
CPC分类号： F01D9/023 , F01D9/041 , F23R3/002 , F23R3/286 , F23R3/46 , Y02T50/675
摘要： An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.

9. 发明申请

US20100115953A1 Integrated Combustor and Stage 1 Nozzle in a Gas Turbine and Method 有权
标题翻译：燃气轮机中的一体化燃烧器和1级喷嘴及其方法
公开(公告)号：US20100115953A1
公开(公告)日：2010-05-13
申请号：US12269411
申请日：2008-11-12
申请人： Lewis Berkley Davis, JR. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
发明人： Lewis Berkley Davis, JR. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
IPC分类号： F23R3/42 , F02C7/22 , F02C3/14
CPC分类号： F01D9/023 , F01D9/041 , F23R3/002 , F23R3/286 , F23R3/46 , Y02T50/675
摘要： An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.
摘要翻译：在燃气轮机中的一体式燃烧器和一级喷嘴包括燃烧室，其在分开的轴向位置处接收来自至少一个燃料喷嘴组的预混燃料和空气。燃烧室包括将热燃烧气体输送到涡轮机的衬套和过渡件。一级喷嘴，衬管和过渡件集成在一个单一部件中。一个或多个燃料喷嘴组的至少一个轴向位置包括多个小型混合装置，其集中放热并减少火焰长度。

10. 发明申请

US20110232299A1 IMPINGEMENT STRUCTURES FOR COOLING SYSTEMS 审中-公开
标题翻译：冷却系统的冲击结构
公开(公告)号：US20110232299A1
公开(公告)日：2011-09-29
申请号：US13043760
申请日：2011-03-09
申请人： Sergey Aleksandrovich Stryapunin , Sergey Anatolievich Meshkov
发明人： Sergey Aleksandrovich Stryapunin , Sergey Anatolievich Meshkov
IPC分类号： F02C7/12 , F28D15/00
CPC分类号： F23R3/04 , F23R2900/03044
摘要： An impingement structure 204 in an impingement cooling system, wherein the impingement structure 204 comprises a plurality of impingement apertures 214 that are configured to impinge a flow of coolant and direct resulting coolant jets against a target-surface 210 that opposes the impingement structure 204 across an impingement cavity 212 formed therebetween, the impingement structure 204 comprising a corrugated configuration.
摘要翻译：冲击冷却系统中的冲击结构204，其中冲击结构204包括多个冲击孔214，其构造成冲击冷却剂流并将所产生的冷却剂喷射引导到目标表面210上，该目标表面210穿过冲击结构204穿过一个冲击腔212形成在其间，冲击结构204包括波纹状构造。

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