公开(公告)号：US10907549B2

公开(公告)日：2021-02-02

申请号：US14576712

申请日：2014-12-19

Applicant: ALSTOM Technology Ltd

Inventor： Michael Düsing ,  Adnan Eroglu

IPC: F02C9/28 ,  F02C3/14 ,  F02C6/00 ,  F02C9/34 ,  F02C7/228 ,  F23C6/04

Abstract: The invention concerns a method for a part load CO reduction operation and a low-CO emissions operation of a gas turbine with sequential combustion. The gas turbine essentially includes at least one compressor, a first combustor which is connected downstream to the compressor. The hot gases of the first combustor are admitted at least to an intermediate turbine or directly or indirectly to a second combustor. The hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery. At least one combustor runs under a caloric combustion path having a can-architecture, and wherein the air ratio (λ) of the combustion at least of the second combustor is kept below a maximum air ratio (λmax).

公开(公告)号：US20140026586A1

公开(公告)日：2014-01-30

申请号：US13951507

申请日：2013-07-26

Applicant: ALSTOM Technology Ltd

Inventor： Michael Düsing

IPC: F23R3/34

CPC classification number: F23R3/346 ,  F23C3/002 ,  F23R3/20

Abstract: The invention refers to a reheat burner that includes a flow channel for a hot gas flow with a lance arranged along said flow channel, protruding into the flow channel for injecting a fuel over an injection plane perpendicular to a channel longitudinal axis, wherein the channel and lance define a vortex generation zone upstream of the injection plane and a mixing zone downstream of the injection plane in the hot gas flow direction. The mixing zone provides at least one axially region having different cross sectional areas along its longitudinal axis with continuously changing shape, or having non circular cross section areas which change location along its longitudinal axis by continuously rotation around the longitudinal axis.

Abstract translation: 本发明涉及一种再热燃烧器，其包括用于热气流的流动通道，其具有沿着所述流动通道布置的喷枪，突出到流动通道中，用于在与通道纵向轴线垂直的注入平面上喷射燃料，其中通道和 喷枪在喷射平面的上游定义涡流产生区，在热气流方向上限定喷射平面下游的混合区。 混合区提供沿其纵向轴线具有不同横截面积的至少一个轴向区域，其具有连续变化的形状，或具有非圆形横截面区域，其通过围绕纵向轴线的连续旋转沿其纵向轴线改变位置。

公开(公告)号：US09482106B2

公开(公告)日：2016-11-01

申请号：US14062091

申请日：2013-10-24

Applicant: ALSTOM Technology Ltd

Inventor： Michael Düsing ,  Mirko Ruben Bothien

IPC: F01D9/02 ,  F02C7/12 ,  F23R3/00

CPC classification number: F01D9/023 ,  F02C7/12 ,  F05D2250/52 ,  F23R3/002 ,  Y10T29/49229

Abstract: A combustor transition can be adapted to guide combustion gases in a hot gas flow path extending between a combustor and a first stage of a turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the combustor and a downstream end adapted for connection to a first stage of the turbine. The downstream end comprises an outer wall, an inner wall, a first side wall and a second side wall. At least one side wall has a side wall extension, which can extend in a downstream direction beyond the outlet. A gas turbine can be retrofitted with such a combustor transition and a gas turbine with such a combustor transition can also undergo a borescope inspection.

Abstract translation: 燃烧器过渡可以适于引导在燃气轮机中在燃烧器和涡轮机的第一级之间延伸的热气流路径中的燃烧气体。 燃烧器转变包括具有适于连接到燃烧器的上游端的管道和适于连接到涡轮机的第一级的下游端。 下游端包括外壁，内壁，第一侧壁和第二侧壁。 至少一个侧壁具有侧壁延伸部，其可以在下游方向上延伸超过出口。 燃气轮机可以用这样的燃烧器过渡进行改装，并且具有这样的燃烧器过渡的燃气轮机也可以进行孔镜检查。

公开(公告)号：US09541293B2

公开(公告)日：2017-01-10

申请号：US13951507

申请日：2013-07-26

Applicant: ALSTOM Technology Ltd

Inventor： Michael Düsing

IPC: F23R3/34 ,  F23C3/00 ,  F23R3/20

CPC classification number: F23R3/346 ,  F23C3/002 ,  F23R3/20

Abstract: The invention refers to a reheat burner that includes a flow channel for a hot gas flow with a lance arranged along said flow channel, protruding into the flow channel for injecting a fuel over an injection plane perpendicular to a channel longitudinal axis, wherein the channel and lance define a vortex generation zone upstream of the injection plane and a mixing zone downstream of the injection plane in the hot gas flow direction. The mixing zone provides at least one axially region having different cross sectional areas along its longitudinal axis with continuously changing shape, or having non circular cross section areas which change location along its longitudinal axis by continuously rotation around the longitudinal axis.

Abstract translation: 本发明涉及一种再热燃烧器，其包括用于热气流的流动通道，其具有沿着所述流动通道布置的喷枪，突出到流动通道中，用于在与通道纵向轴线垂直的注入平面上喷射燃料，其中通道和 喷枪在喷射平面的上游定义涡流产生区，在热气流方向上限定喷射平面下游的混合区。 混合区提供沿其纵向轴线具有不同横截面积的至少一个轴向区域，其具有连续变化的形状，或具有非圆形横截面区域，其通过围绕纵向轴线的连续旋转沿其纵向轴线改变位置。

公开(公告)号：US09429032B2

公开(公告)日：2016-08-30

申请号：US14062001

申请日：2013-10-24

Applicant: ALSTOM Technology Ltd

Inventor： Mirko Ruben Bothien ,  Michael Düsing

IPC: F01D9/02 ,  F23R3/00 ,  F02C7/24

CPC classification number: F01D9/023 ,  F02C7/24 ,  F05D2250/52 ,  F05D2260/963 ,  F23R3/002 ,  Y10T29/49229

Abstract: A combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine is disclosed. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and a downstream end adapted for connection to a first stage of a turbine, wherein the downstream end includes an outer wall, an inner wall, a first and a second side wall. At least one side wall has a side wall extension which extends in a downstream direction beyond the outlet. The side wall extension at least partly encloses a first resonator volume and at least one side wall extension includes a resonator hole, which is configured as a neck of a Helmholtz-damper. A method for retrofitting a gas turbine and method for borescope inspection of a GT are disclosed.

Abstract translation: 公开了一种适于引导在燃气轮机中在罐式燃烧器和涡轮机的第一级之间延伸的热气流动路径中的燃烧气体的燃烧器转变。 燃烧器过渡部分包括管道，其具有适于连接到罐式燃烧器的上游端和适于连接到涡轮机的第一级的下游端，其中下游端包括外壁，内壁，第一和第二 侧墙。 至少一个侧壁具有在下游方向上延伸超过出口的侧壁延伸部。 侧壁延伸部至少部分地包围第一谐振器体积，并且至少一个侧壁延伸部包括构造为亥姆霍兹阻尼器的颈部的谐振器孔。 公开了一种用于改装燃气轮机的方法和用于GT的孔镜检查方法。

公开(公告)号：US20140109578A1

公开(公告)日：2014-04-24

申请号：US14062001

申请日：2013-10-24

Applicant: Alstom Technology Ltd

Inventor： Mirko Ruben BOTHIEN ,  Michael Düsing

IPC: F23R3/00

CPC classification number: F01D9/023 ,  F02C7/24 ,  F05D2250/52 ,  F05D2260/963 ,  F23R3/002 ,  Y10T29/49229

Abstract: The disclosure relates to a combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and a downstream end adapted for connection to a first stage of a turbine, wherein the downstream end comprises an outer wall, an inner wall, a first and a second side wall. At least one side wall has a side wall extension, which extends in a downstream direction beyond the outlet. The side wall extension at least partly encloses a first resonator volume and at least one side wall extension includes a resonator hole, which is configured as a neck of a Helmholtz-damper. Besides the combustor transition a gas turbine comprising such a combustor transition, a method for retrofitting a gas turbine with such a combustor transition as well as a method for borescope inspection of a GT with such a combustor transition are disclosed.

Abstract translation: 本公开涉及一种适于引导在燃气轮机中在罐式燃烧器和涡轮机的第一级之间延伸的热气流动路径中的燃烧气体的燃烧器过渡。 燃烧器过渡部分包括具有适于连接到罐式燃烧器的上游端和适于连接到涡轮机的第一级的下游端的管道，其中下游端包括外壁，内壁，第一和第二 侧墙。 至少一个侧壁具有侧壁延伸部，其在下游方向上延伸超过出口。 侧壁延伸部至少部分地包围第一谐振器体积，并且至少一个侧壁延伸部包括构造为亥姆霍兹阻尼器的颈部的谐振器孔。 除了燃烧器转换之外，还公开了一种包括这种燃烧器过渡的燃气轮机，用于改变具有这种燃烧器过渡的燃气轮机的方法以及具有这种燃烧器转变的GT的管道检查方法。