公开(公告)号：US20140109588A1

公开(公告)日：2014-04-24

申请号：US14060931

申请日：2013-10-23

Applicant: ALSTOM Technology Ltd

Inventor： Andrea Ciani ,  John Philip Wood ,  Douglas Anthony Pennell ,  Ewald Freitag ,  Urs Benz ,  Andre Theuer

IPC: F23R3/28

CPC classification number: F23R3/16 ,  F02C6/003 ,  F02C9/26 ,  F02C9/32 ,  F02C9/34 ,  F05B2260/222 ,  F23R3/20 ,  F23R3/286 ,  F23R3/34 ,  F23R3/346 ,  F23R3/36 ,  F23R3/46 ,  F23R2900/03341

Abstract: The present invention relation to a burner for a combustion chamber of a gas turbine with a mixing and injection device. The mixing and injection device includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies, each extending in a first transverse direction into the gas-flow channel. Each streamlined body has two lateral surfaces that are arranged essentially parallel to the main-flow direction, the lateral surfaces being joined to one another at their upstream side to form a leading edge of the body and joined at their downstream side to form a trailing edge of the body. Each streamlined body has a cross-section perpendicular to the first transverse direction that is shaped as a streamlined profile. At least one of the streamlined bodies is provided with a mixing structure and with at least one fuel nozzle located at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel, wherein at least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor. The invention also relates to a method of using said burner in a gas turbine.

Abstract translation: 本发明涉及一种具有混合和注射装置的燃气轮机燃烧室的燃烧器。 混合和注入装置包括界定气流通道的限制壁和至少两个流线型的主体，每个流体线体在第一横向方向上延伸到气体流动通道中。 每个流线型体具有基本上平行于主流动方向布置的两个侧表面，侧表面在其上游侧彼此连接以形成主体的前缘并在其下游侧接合以形成后缘 的身体。 每个流线型本体具有垂直于第一横向方向的横截面，其形状为流线型轮廓。 流线型主体中的至少一个设置有混合结构，并且具有位于其后缘处的至少一个燃料喷嘴，用于将基本上平行于主流动方向的至少一个燃料引入流动通道中，其中至少两个 流线型主体沿着第一横向方向具有不同的长度，使得它们可以用于罐式燃烧器。 本发明还涉及在燃气轮机中使用所述燃烧器的方法。

公开(公告)号：US09664390B2

公开(公告)日：2017-05-30

申请号：US13936424

申请日：2013-07-08

Applicant: ALSTOM Technology Ltd

Inventor： Stefano Bernero ,  Ennio Pasqualotto ,  Ewald Freitag

IPC: F23R3/14 ,  F23R3/12 ,  F23R3/54 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23R3/12 ,  F23R3/28 ,  F23R3/54 ,  F23R2900/03043

Abstract: The invention refers to burner arrangement for producing hot gases to be expanded in a gas turbine, including a burner inside a plenum, where the burner has means for fuel injection, means for air supply and means for generating an ignitable fuel/air mixture inside the burner, and a combustion chamber following downstream said burner having an outlet being fluidly connected to the gas turbine. The invention is characterized in that the means for air supply includes at least two separate flow passages, and that the one of the two flow passages is fed by a first supply pressure and the other flow passage is fed by a second supply pressure.

公开(公告)号：US20140109583A1

公开(公告)日：2014-04-24

申请号：US14059876

申请日：2013-10-22

Applicant: ALSTOM Technology Ltd.

Inventor： Franklin Marie GENIN ,  Marcel Riker ,  Stefano Bernero ,  Bettina Paikert ,  Ewald Freitag

IPC: F23R3/28

CPC classification number: F23R3/286 ,  F23C2900/07001 ,  F23C2900/07002 ,  F23D11/402 ,  F23R3/14 ,  F23R3/343

Abstract: The burner includes a swirl chamber. The swirl chamber has a substantially conical shape defining a central axis. The swirl chamber is defined by a plurality of wall elements. A combination of nozzles at the pressure, suction side and trailing edge of the wall element are placed for fuel injection. The wall elements define slots between each other. The slots have different widths (w) in consecutive planes in the axial direction, wherein said planes are perpendicular to the central axis.

Abstract translation: 燃烧器包括旋流室。 涡流室具有限定中心轴线的大致圆锥形形状。 涡流室由多个壁元件限定。 在壁元件的压力，吸力侧和后缘处的喷嘴的组合被放置用于燃料喷射。 壁元件在彼此之间限定槽。 狭槽在轴向方向上的连续平面中具有不同的宽度（w），其中所述平面垂直于中心轴线。

公开(公告)号：US09890955B2

公开(公告)日：2018-02-13

申请号：US14626003

申请日：2015-02-19

Applicant: ALSTOM Technology Ltd

Inventor： Ewald Freitag ,  Adnan Eroglu ,  Michael Maurer ,  Peter Stuttaford

IPC: F02C7/22 ,  F23R3/34 ,  F02C7/228 ,  F23R3/06 ,  F23R3/20 ,  F23R3/42

CPC classification number: F23R3/34 ,  F02C7/22 ,  F02C7/228 ,  F23R3/06 ,  F23R3/20 ,  F23R3/346 ,  F23R3/42 ,  F23R2900/00014 ,  F23R2900/03042 ,  F23R2900/03341

Abstract: The invention refers to a sequential combustor arrangement comprising a first burner, a first combustion chamber, a mixer for admixing a dilution gas via a dilution gas inlet to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The sequential combustor arrangement further includes four cooling zones with a cooling channel. During operation a cooling gas flows through the cooling channels. The disclosure further refers to a method for operating a gas turbine with such a sequential combustor arrangement.

公开(公告)号：US09551491B2

公开(公告)日：2017-01-24

申请号：US13974611

申请日：2013-08-23

Applicant: ALSTOM Technology Ltd

Inventor： Adnan Eroglu ,  Ewald Freitag

IPC: F02C7/22 ,  F23R3/34 ,  F23R3/06 ,  F23R3/20 ,  F02C7/228 ,  F23R3/42

CPC classification number: F23R3/34 ,  F02C7/22 ,  F02C7/228 ,  F23R3/06 ,  F23R3/20 ,  F23R3/26 ,  F23R3/346 ,  F23R3/42 ,  F23R2900/00014 ,  F23R2900/03042 ,  F23R2900/03341 ,  Y02E20/14

Abstract: The invention relates a method for mixing a dilution air with a hot main flow in a sequential combustion system of a gas turbine, wherein the gas turbine essentially comprises at least one compressor, a first combustor which is connected downstream to the compressor, and a second combustor. The hot gases of the first combustor are admitted to at least one intermediate turbine or directly or indirectly to at least one second combustor, wherein the hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery device. The method comprises a coaxial injection of first combustor liner cooling air with second combustor liner cooling air, the first combustor liner cooling air having a sufficient excess pressure margin with respect to the second combustor liner cooling air.

Abstract translation: 本发明涉及一种用于在燃气轮机的顺序燃烧系统中混合稀释空气与热主流的方法，其中所述燃气轮机基本上包括至少一个压缩机，连接在压缩机下游的第一燃烧室和第二燃烧器 燃烧器。 第一燃烧器的热气体被允许进入至少一个中间涡轮机，或者直接或间接地接纳到至少一个第二燃烧器，其中第二燃烧器的热气体被允许进一步涡轮机，或直接地或间接地接纳到能量回收装置。 该方法包括：第一燃烧器衬套冷却空气与第二燃烧器衬套冷却空气的同轴喷射，第一燃烧器衬套冷却空气相对于第二燃烧器衬套冷却空气具有足够的过剩压力裕度。

公开(公告)号：US09518511B2

公开(公告)日：2016-12-13

申请号：US14060065

申请日：2013-10-22

Applicant: ALSTOM Technology Ltd

Inventor： Andrea Ciani ,  Adnan Eroglu ,  Douglas Anthony Pennell ,  Nicolas Tran ,  Ewald Freitag

IPC: F02C7/141 ,  F02C7/12 ,  F02C7/228 ,  F02C9/28

CPC classification number: F02C7/12 ,  F02C7/141 ,  F02C7/228 ,  F02C9/28 ,  F05D2270/08 ,  Y02E20/16

Abstract: The invention discloses a method for operating a gas turbine with sequential combustion, which gas turbine includes a compressor, a first combustor with a first combustion chamber and first burners, which receives compressed air from the compressor, a second combustor with a second combustion chamber and second burners, which receives hot gas from the first combustor with a predetermined second combustor inlet temperature, and a turbine, which receives hot gas from the second combustor. The CO emission for part-load operation is reduced by reducing the second combustor inlet temperature for base-load operation of the gas turbine, and increasing the second combustor inlet temperature when decreasing the gas turbine load (RLGT) from base-load to part-load.

Abstract translation: 本发明公开了一种用于操作具有顺序燃烧的燃气轮机的方法，该燃气轮机包括压缩机，具有第一燃烧室的第一燃烧器和从压缩机接收压缩空气的第一燃烧器，具有第二燃烧室的第二燃烧器， 第二燃烧器，其以预定的第二燃烧器入口温度从第一燃烧器接收热气体;以及涡轮机，其接收来自第二燃烧器的热气体。 通过降低燃气轮机的基本负载运行的第二燃烧器入口温度，并且当将燃气轮机负载（RLGT）从基本负载降低到部分负载时，增加第二燃烧器入口温度， 加载。

公开(公告)号：US09464810B2

公开(公告)日：2016-10-11

申请号：US14059876

申请日：2013-10-22

Applicant: ALSTOM Technology Ltd

Inventor： Franklin Marie Genin ,  Marcel Rieker ,  Stefano Bernero ,  Bettina Paikert ,  Ewald Freitag

IPC: F23R3/14 ,  F23R3/28 ,  F23R3/34 ,  F23D11/40

CPC classification number: F23R3/286 ,  F23C2900/07001 ,  F23C2900/07002 ,  F23D11/402 ,  F23R3/14 ,  F23R3/343

Abstract: The burner includes a swirl chamber. The swirl chamber has a substantially conical shape defining a central axis. The swirl chamber is defined by a plurality of wall elements. A combination of nozzles at the pressure, suction side and trailing edge of the wall element are placed for fuel injection. The wall elements define slots between each other. The slots have different widths (w) in consecutive planes in the axial direction, wherein said planes are perpendicular to the central axis.

Abstract translation: 燃烧器包括旋流室。 涡流室具有限定中心轴线的大致圆锥形形状。 涡流室由多个壁元件限定。 在壁元件的压力，吸力侧和后缘处的喷嘴的组合被放置用于燃料喷射。 壁元件在彼此之间限定槽。 狭槽在轴向方向上的连续平面中具有不同的宽度（w），其中所述平面垂直于中心轴线。

公开(公告)号：US20150159876A1

公开(公告)日：2015-06-11

申请号：US14626003

申请日：2015-02-19

Applicant: ALSTOM Technology Ltd

Inventor： Ewald Freitag ,  Adnan Eroglu ,  Michael Maurer ,  Peter Stuttaford

IPC: F23R3/34 ,  F23R3/06 ,  F23R3/42 ,  F02C7/228

CPC classification number: F23R3/34 ,  F02C7/22 ,  F02C7/228 ,  F23R3/06 ,  F23R3/20 ,  F23R3/346 ,  F23R3/42 ,  F23R2900/00014 ,  F23R2900/03042 ,  F23R2900/03341

Abstract: The invention refers to a sequential combustor arrangement comprising a first burner, a first combustion chamber, a mixer for admixing a dilution gas via a dilution gas inlet to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The sequential combustor arrangement further includes four cooling zones with a cooling channel. During operation a cooling gas flows through the cooling channels. The disclosure further refers to a method for operating a gas turbine with such a sequential combustor arrangement.

Abstract translation: 本发明涉及连续的燃烧器装置，其包括第一燃烧器，第一燃烧室，用于将稀释气体经由稀释气体入口混合到在运行期间离开第一燃烧室的热气体的混合器，第二燃烧器和第二燃烧器 腔室依次布置在流体流动连接中。 顺序燃烧器装置还包括具有冷却通道的四个冷却区。 在运行期间，冷却气体流过冷却通道。 本发明还涉及一种用这种连续燃烧器装置操作燃气轮机的方法。

公开(公告)号：US20140109586A1

公开(公告)日：2014-04-24

申请号：US14060065

申请日：2013-10-22

Applicant: ALSTOM Technology Ltd

Inventor： Andrea CIANI ,  Adnan Eroglu ,  Douglas Anthony Pennell ,  Nicolas Tran ,  Ewald Freitag

IPC: F02C7/228 ,  F02C7/12

CPC classification number: F02C7/12 ,  F02C7/141 ,  F02C7/228 ,  F02C9/28 ,  F05D2270/08 ,  Y02E20/16

Abstract: The invention discloses a method for operating a gas turbine with sequential combustion, which gas turbine includes a compressor, a first combustor with a first combustion chamber and first burners, which receives compressed air from the compressor, a second combustor with a second combustion chamber and second burners, which receives hot gas from the first combustor with a predetermined second combustor inlet temperature, and a turbine, which receives hot gas from the second combustor. The CO emission for part-load operation is reduced by reducing the second combustor inlet temperature for base-load operation of the gas turbine, and increasing the second combustor inlet temperature when decreasing the gas turbine load (RLGT) from base-load to part-load.

Abstract translation: 本发明公开了一种用于操作具有顺序燃烧的燃气轮机的方法，该燃气轮机包括压缩机，具有第一燃烧室的第一燃烧器和从压缩机接收压缩空气的第一燃烧器，具有第二燃烧室的第二燃烧器， 第二燃烧器，其以预定的第二燃烧器入口温度从第一燃烧器接收热气体;以及涡轮机，其接收来自第二燃烧器的热气体。 通过降低燃气轮机的基本负载运行的第二燃烧器入口温度，并且当将燃气轮机负载（RLGT）从基本负载降低到部分负载时，增加第二燃烧器入口温度， 加载。