公开(公告)号：US20110197591A1

公开(公告)日：2011-08-18

申请号：US13025307

申请日：2011-02-11

Applicant: Almaz Valeev ,  Sergey Anatolievich Meshkov ,  Mark Hadley ,  Stanley Widener ,  Geoffrey Myers ,  Valery Alexandrovich Mitrofanov

Inventor： Almaz Valeev ,  Sergey Anatolievich Meshkov ,  Mark Hadley ,  Stanley Widener ,  Geoffrey Myers ,  Valery Alexandrovich Mitrofanov

IPC: F23R3/28

CPC classification number: F23R3/46 ,  F23R3/286 ,  F23R3/343

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US08418468B2

公开(公告)日：2013-04-16

申请号：US12754813

申请日：2010-04-06

Applicant: Kevin Weston McMahan ,  Almaz Valeev ,  Chunyang Wu

Inventor： Kevin Weston McMahan ,  Almaz Valeev ,  Chunyang Wu

IPC: F02C1/00

CPC classification number: F23R3/286 ,  F23R3/34

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20130025289A1

公开(公告)日：2013-01-31

申请号：US13193865

申请日：2011-07-29

Applicant: Joseph Citeno ,  Dmitry Alexandrovitch Lysenko ,  Sergey Anatolievich Meshkov ,  Valery Alexandrovich Mitrofanov ,  Almaz Valeev

Inventor： Joseph Citeno ,  Dmitry Alexandrovitch Lysenko ,  Sergey Anatolievich Meshkov ,  Valery Alexandrovich Mitrofanov ,  Almaz Valeev

IPC: F02C7/22

CPC classification number: F23R3/286 ,  F23R3/343 ,  F23R3/346

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US09297534B2

公开(公告)日：2016-03-29

申请号：US13193865

申请日：2011-07-29

Applicant: Joseph Citeno ,  Dmitry Alexandrovitch Lysenko ,  Sergey Anatolievich Meshkov ,  Valery Alexandrovich Mitrofanov ,  Almaz Valeev

Inventor： Joseph Citeno ,  Dmitry Alexandrovitch Lysenko ,  Sergey Anatolievich Meshkov ,  Valery Alexandrovich Mitrofanov ,  Almaz Valeev

IPC: F23R3/34 ,  F23R3/28

CPC classification number: F23R3/286 ,  F23R3/343 ,  F23R3/346

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US08991187B2

公开(公告)日：2015-03-31

申请号：US12901648

申请日：2010-10-11

Applicant: Michael John Hughes ,  Jonathan Dwight Berry ,  Jason Thurman Stewart ,  Almaz Valeev ,  Chunyang Wu

Inventor： Michael John Hughes ,  Jonathan Dwight Berry ,  Jason Thurman Stewart ,  Almaz Valeev ,  Chunyang Wu

IPC: F02C1/00 ,  F02G3/00 ,  F23R3/28 ,  F23R3/36

CPC classification number: F23R3/286 ,  F23C2900/07001 ,  F23C2900/9901 ,  F23R3/36

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20110239653A1

公开(公告)日：2011-10-06

申请号：US12754803

申请日：2010-04-06

Applicant: Almaz Valeev ,  Chunyang Wu ,  Leonid Borisovich Zvedenuk

Inventor： Almaz Valeev ,  Chunyang Wu ,  Leonid Borisovich Zvedenuk

IPC: F02C7/22

CPC classification number: F23R3/34 ,  F23R3/286

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20110214428A1

公开(公告)日：2011-09-08

申请号：US12917784

申请日：2010-11-02

Applicant: Borys SHERSHNYOV ,  Leonid GINESSIN ,  Almaz VALEEV KAMILEVICH

Inventor： Borys SHERSHNYOV ,  Leonid GINESSIN ,  Almaz VALEEV KAMILEVICH

IPC: F02C3/00

CPC classification number: F23R3/06 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: A venturi device for a turbine combustor includes a substantially annular outer liner; a substantially annular inner liner; a venturi channel located between the substantially annular outer and inner liners; the substantially annular outer and inner liners being substantially V-shaped in axial cross-section, thereby defining a throat region; the substantially annular outer liner formed with an array of impingement holes and the substantially annular inner liner formed with a plurality of vortex generators facing the substantially annular outer liner.

Abstract translation: 用于涡轮机燃烧器的文氏管装置包括基本上环形的外衬套; 基本上环形的内衬; 文丘里通道，位于基本上环形的外衬垫和内衬之间; 基本环形的外衬里和内衬在轴向横截面上基本为V形，从而限定了喉部区域; 所述基本上环形的外衬套形成有冲击孔的阵列，并且所述大体上环形的内衬形成有面向所述基本上环形的外衬套的多个涡流发生器。

公开(公告)号：US08438852B2

公开(公告)日：2013-05-14

申请号：US12754803

申请日：2010-04-06

Applicant: Almaz Valeev ,  Chunyang Wu ,  Leonid Borisovich Zvedenuk

Inventor： Almaz Valeev ,  Chunyang Wu ,  Leonid Borisovich Zvedenuk

IPC: F23R3/36

CPC classification number: F23R3/34 ,  F23R3/286

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20120085100A1

公开(公告)日：2012-04-12

申请号：US12901648

申请日：2010-10-11

Applicant: Michael John Hughes ,  Jonathan Dwight Berry ,  Jason Thurman Stewart ,  Almaz Valeev ,  Chunyang Wu

Inventor： Michael John Hughes ,  Jonathan Dwight Berry ,  Jason Thurman Stewart ,  Almaz Valeev ,  Chunyang Wu

IPC: F02C7/22

CPC classification number: F23R3/286 ,  F23C2900/07001 ,  F23C2900/9901 ,  F23R3/36

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20110107765A1

公开(公告)日：2011-05-12

申请号：US12832014

申请日：2010-07-07

Applicant: Almaz Valeev ,  Sergey Meshkov ,  Garth Frederick ,  Valery Mitrofanov ,  Dmitry Lysenko

Inventor： Almaz Valeev ,  Sergey Meshkov ,  Garth Frederick ,  Valery Mitrofanov ,  Dmitry Lysenko

IPC: F02C7/22

CPC classification number: F23R3/286 ,  F02C7/228 ,  F23R3/14 ,  Y02T50/671 ,  Y02T50/675

Abstract: In certain embodiments, a system includes a gas turbine controller. The gas turbine controller includes a first operational mode enabling fuel flow only through a first plurality of fuel nozzles having a first swirl direction. The gas turbine controller also includes a second operational mode enabling fuel flow only through a second plurality of fuel nozzles having a second swirl direction opposite from the first swirl direction.

Abstract translation: 在某些实施例中，系统包括燃气轮机控制器。 燃气轮机控制器包括第一操作模式，其使能燃料流仅通过具有第一旋流方向的第一多个燃料喷嘴。 燃气轮机控制器还包括第二操作模式，使燃料仅能通过具有与第一旋转方向相反的第二旋转方向的第二多个燃料喷嘴。