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1.发明申请公开(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
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。
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2.发明授权公开(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
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。
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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
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。
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公开(公告)号：US20110173984A1
公开(公告)日：2011-07-21
申请号：US12917561
申请日：2010-11-02
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。
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公开(公告)号：US08418468B2
公开(公告)日：2013-04-16
申请号：US12754813
申请日：2010-04-06
申请人： Kevin Weston McMahan , Almaz Valeev , Chunyang Wu
发明人： Kevin Weston McMahan , Almaz Valeev , Chunyang Wu
IPC分类号： F02C1/00
摘要： A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.
摘要翻译： 提供了燃烧器部分，并且包括分段的环形歧管，其在燃料喷嘴支撑件的上游位于通道的部分中，氧化剂通过该部分流动，歧管的每个部分基本上轴向对齐并且包括主体以容纳内部形成的燃料 以限定喷射孔，燃料通过该喷射孔注入到燃料喷嘴支撑件上游的氧化剂流过的通道中。
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公开(公告)号：US08991187B2
公开(公告)日：2015-03-31
申请号：US12901648
申请日：2010-10-11
申请人： Michael John Hughes , Jonathan Dwight Berry , Jason Thurman Stewart , Almaz Valeev , Chunyang Wu
发明人： Michael John Hughes , Jonathan Dwight Berry , Jason Thurman Stewart , Almaz Valeev , Chunyang Wu
CPC分类号： F23R3/286 , F23C2900/07001 , F23C2900/9901 , F23R3/36
摘要： The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air.
摘要翻译： 本申请提供了一种用于燃烧燃料流和空气流的燃烧器。 燃烧器可以包括多个燃料喷嘴，位于燃料喷嘴上游的稀薄预喷嘴燃料喷射系统以及位于燃料喷嘴和稀薄预喷嘴燃料喷射系统之间的预混合环，以预混合燃料流和 空气流动。
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公开(公告)号：US20110239653A1
公开(公告)日：2011-10-06
申请号：US12754803
申请日：2010-04-06
IPC分类号： F02C7/22
摘要： A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through which air and/or a fuel/air mixture flows upstream from a fuel nozzle support, the manifold including a body to accommodate quaternary fuel therein, the body defining injection holes through which the quaternary fuel is injected into a section of the passage at a location upstream from the fuel nozzle support.
摘要翻译： 设置燃烧器部分并且包括一个或多个环形四元燃料歧管，其安装在限定在燃烧器的壳体和盖组件之间的环形通道内，空气和/或燃料/空气混合物通过燃烧器部分从燃料喷嘴支架上游流动， 歧管，其包括容纳四元燃料的主体，所述主体限定了喷射孔，通过所述喷射孔将所述四元燃料通过所述喷射孔注入到所述通道的在所述燃料喷嘴支撑件上游的位置处的一部分中。
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公开(公告)号：US20120031098A1
公开(公告)日：2012-02-09
申请号：US13196968
申请日：2011-08-03
申请人： Leonid Ginessin , Borys Shershnyov , Almaz Valeev
发明人： Leonid Ginessin , Borys Shershnyov , Almaz Valeev
IPC分类号： F02C7/12
CPC分类号： F23R3/283 , F23C2900/07001 , F23D2214/00 , F23R3/14
摘要： A fuel nozzle for turbine engine includes a cooling shroud located at the downstream end of the fuel nozzle to help cool the downstream end of the fuel nozzle. The cooling shroud surrounds the exterior circumference of the downstream end of the fuel nozzle. A flow of air is admitted into the cooling shroud and the flow of air travels in the downstream direction through a first passageway which covers the exterior of the fuel nozzle. The cooling air flow then turns 180° and travels in the upstream direction through a second passageway which is located concentrically outside the first passageway. The airflow then leaves the upstream end of the cooling shroud and enters the interior of the fuel nozzle.
摘要翻译： 用于涡轮发动机的燃料喷嘴包括位于燃料喷嘴的下游端的冷却罩，以帮助冷却燃料喷嘴的下游端。 冷却罩围绕燃料喷嘴的下游端的外周。 空气流进入冷却护罩，空气流沿下游方向通过覆盖燃料喷嘴外部的第一通道。 然后，冷却空气流转动180°并沿上游方向通过位于第一通道同心位置的第二通道。 气流然后离开冷却罩的上游端并进入燃料喷嘴的内部。
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公开(公告)号：US20110239652A1
公开(公告)日：2011-10-06
申请号：US12754813
申请日：2010-04-06
申请人： Kevin Weston McMahan , Almaz Valeev , Chunyang Wu
发明人： Kevin Weston McMahan , Almaz Valeev , Chunyang Wu
IPC分类号： F02C7/22
摘要： A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.
摘要翻译： 提供了燃烧器部分，并且包括分段的环形歧管，其在燃料喷嘴支撑件的上游位于通道的部分中，氧化剂通过该部分流动，歧管的每个部分基本上轴向对齐并且包括主体以容纳内部形成的燃料 以限定喷射孔，燃料通过该喷射孔注入到燃料喷嘴支撑件上游的氧化剂流过的通道中。
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公开(公告)号：US08438852B2
公开(公告)日：2013-05-14
申请号：US12754803
申请日：2010-04-06
IPC分类号： F23R3/36
摘要： A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through which air and/or a fuel/air mixture flows upstream from a fuel nozzle support, the manifold including a body to accommodate quaternary fuel therein, the body defining injection holes through which the quaternary fuel is injected into a section of the passage at a location upstream from the fuel nozzle support.
摘要翻译： 设置燃烧器部分并且包括一个或多个环形四元燃料歧管，其安装在限定在燃烧器的壳体和盖组件之间的环形通道内，空气和/或燃料/空气混合物通过燃烧器部分从燃料喷嘴支架上游流动， 歧管，其包括容纳四元燃料的主体，所述主体限定了喷射孔，通过所述喷射孔将所述四元燃料通过所述喷射孔注入到所述通道的在所述燃料喷嘴支撑件上游的位置处的一部分中。
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