公开(公告)号：US20160123597A1

公开(公告)日：2016-05-05

申请号：US14925527

申请日：2015-10-28

Applicant: ALSTOM Technology Ltd

Inventor： Douglas Anthony PENNELL ,  Urs BENZ ,  Adnan EROGLU ,  Ewald FREITAG ,  Mirko Ruben BOTHIEN ,  Andrea CIANI

IPC: F23R3/34 ,  F23R3/36

CPC classification number: F23R3/346 ,  F23C6/042 ,  F23C6/045 ,  F23C6/047 ,  F23C2900/07021 ,  F23D2900/14004 ,  F23R3/06 ,  F23R3/283 ,  F23R3/34 ,  F23R3/36 ,  F23R2900/03341

Abstract: A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner.

Abstract translation: 用于燃气轮机的燃烧器装置包括第一燃烧器，第一燃烧室，混合器，用于将稀释气体混合到在运行期间离开第一燃烧室的气体;第二燃烧器和第二燃烧室，其依次布置在流体流中 连接。 燃烧器装置的这些元件被排列成一行以形成在第一燃烧室和第二燃烧器之间延伸的流路。 燃烧器装置包括设置在流动路径内并且从第一燃烧器通过第一燃烧室延伸到混合器中并进入第二燃烧器的中心喷枪体，其中喷枪体包括用于为第一燃烧器提供燃料的燃料管道和/或 为第二个燃烧器。

公开(公告)号：US20140116059A1

公开(公告)日：2014-05-01

申请号：US14067257

申请日：2013-10-30

Applicant: ALSTOM Technology Ltd

Inventor： Urs BENZ ,  Christoph Appel ,  Oliver Konradt ,  Ivan Lenuzzi ,  Alen Markovic

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F23M5/085 ,  F23R3/005 ,  F23R3/06 ,  F23R2900/00012 ,  F23R2900/03044

Abstract: A hot gas segment arrangement, especially for a combustion chamber of a gas turbine, that includes at least one hot gas segment, which is removably mounted on a carrier, and is subjected at its outside to hot gas and impingement-cooled at its inside, whereby an impingement plate with a plurality of distributed impingement holes is arranged in a distance at the inside of the impingement plate. A cooling air supply means is provided for loading the impingement plate with pressurized cooling air in order to generate through the impingement holes jets of cooling air, which impinge on the inside of the hot gas segment. The cooling efficiency and lifetime are increased by the impingement plate being part of a closed receptacle, which is supplied with the pressurized cooling air, and by the receptacle with the impingement plate being mounted on the carrier independently of the hot gas segment.

Abstract translation: 特别是用于燃气轮机的燃烧室的热气体段装置，其包括至少一个热气体段，其可移除地安装在载体上，并在其外部经受热气体并在其内部进行冲击冷却， 由此具有多个分布式冲击孔的冲击板在冲击板的内部一定距离地布置。 提供冷却空气供应装置，用于将冲击板加载有加压的冷却空气，以便通过撞击在热气体段内部的冷却空气的冲击孔产生。 冲击板是被提供加压冷却空气的封闭容器的一部分，以及独立于热气体段的冲击板安装在载体上的容器，从而提高了冷却效率和使用寿命。

公开(公告)号：US20150361889A1

公开(公告)日：2015-12-17

申请号：US14732070

申请日：2015-06-05

Applicant: ALSTOM TECHNOLOGY LTD

Inventor： Michael Thomas MAURER ,  Urs BENZ ,  Felix BAUMGARTNER

IPC: F02C7/18 ,  F02C3/04

CPC classification number: F02C7/18 ,  F02C3/04 ,  F05D2220/32 ,  F05D2260/201 ,  F05D2260/2212 ,  F23R3/002 ,  F23R2900/03044

Abstract: An impingement cooled wall arrangement includes a flow diverter arranged in the cooling flow path between the cooled wall and a sleeve to divert a cross flow away from a second aperture. The flow diverter extends in downstream direction of the cross flow beyond the second aperture with a first leg extending along one side of the second aperture in downstream direction of the cross flow and a second leg extending along the other side of the second aperture. No impingement cooling aperture is arranged in a first convective cooling section of the wall between the upstream end and downstream end of the flow diverter outside the section shielded by the diverter.

Abstract translation: 冲击冷却壁布置包括布置在冷却流动路径中的冷却壁和套筒之间的分流器，以将横流从第二孔转出。 流动分流器在交叉流的下游方向上延伸超过第二孔，第一腿在第二孔的下游方向上沿着第二孔的一侧延伸，第二腿沿着第二孔的另一侧延伸。 在分流器屏蔽的部分之外的分流器的上游端和下游端之间的第一对流冷却部分中没有设置冲击冷却孔。

公开(公告)号：US20150354826A1

公开(公告)日：2015-12-10

申请号：US14727977

申请日：2015-06-02

Applicant: ALSTOM Technology Ltd

Inventor： Uwe RÜDEL ,  Urs BENZ ,  Christoph APPEL ,  Ivan LENUZZI

IPC: F23R3/50 ,  F23R3/00 ,  F23R3/60 ,  F02C3/14 ,  F02C7/18 ,  F23R3/16 ,  F02C3/04

CPC classification number: F23R3/50 ,  F01D9/023 ,  F02C3/04 ,  F02C3/14 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/30 ,  F23R3/002 ,  F23R3/16 ,  F23R3/48 ,  F23R3/60 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02E20/16

Abstract: The invention relates to an annular combustion chamber of a gas turbine having a machine axis. The combustion chamber includes at least two zones. A first zone receives the fuel/air mixture of a plurality of burners. A second zone guides the hot gases being produced by the burners from the first zone to an entrance of a turbine section of said gas turbine. An annular transition liner includes a plurality of liner segments located at the transition between said first zone and second zone. Each of the liner segments includes with respect to the axial hot gas flow a leading edge, a trailing edge, and two sidewalls, and is provided with axial mounting means at the leading and trailing edges, such that the liner segment can be installed in axial direction and is axially fixed by respective segments of the neighboring first zone. Local spacer ribs are provided at the leading edge of the liner segments in order to establish a gap of minimum width between the liner segments and the fixing segments of the neighboring first zone.

Abstract translation: 本发明涉及具有机器轴线的燃气轮机的环形燃烧室。 燃烧室包括至少两个区域。 第一区域接收多个燃烧器的燃料/空气混合物。 第二区域将由燃烧器产生的热气体从第一区域引导到所述燃气涡轮机的涡轮机部分的入口。 环形过渡衬套包括位于所述第一区和第二区之间的过渡处的多个衬垫段。 每个衬里段相对于轴向热气流包括前缘，后缘和两个侧壁，并且在前缘和后缘处设置有轴向安装装置，使得衬套段可以安装在轴向 方向并且由邻近的第一区的相应段轴向地固定。 局部间隔肋设置在衬垫段的前缘处，以便建立衬垫段与相邻第一区的固定段之间的最小宽度的间隙。

公开(公告)号：US20150267918A1

公开(公告)日：2015-09-24

申请号：US14660269

申请日：2015-03-17

Applicant: ALSTOM Technology Ltd

Inventor： Michael Thomas MAURER ,  Urs BENZ ,  Birute BUNKUTE

IPC: F23R3/26 ,  F02C7/18 ,  F02C3/04

CPC classification number: F23R3/26 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/30 ,  F05D2260/232 ,  F23R3/005 ,  F23R3/06 ,  F23R3/46 ,  F23R2900/03043 ,  F23R2900/03045

Abstract: The invention refers to a combustion chamber having a sleeve section which is at least partly enclosing a duct wall for guiding a cooling gas in a channel between the sleeve section and the duct wall along the outer surface of the duct wall. The sleeve section has one main inlet opening facing away from the duct wall wherein the cross sectional area of the main inlet opening is larger than 70% of the sum of the cross sections of all cooling openings to the sleeve section. The disclosure further refers to a gas turbine comprising such combustion chamber.

Abstract translation: 本发明涉及一种具有套筒部分的燃烧室，该套筒部分至少部分地包围导管壁，用于沿管道壁的外表面在套管部分和管道壁之间的通道中引导冷却气体。 套管部分具有一个主导管开口，其背向导管壁，其中主入口开口的横截面积大于所有冷却开口至套筒部分的横截面总和的70％。 本发明还涉及包括这种燃烧室的燃气轮机。

公开(公告)号：US20150159870A1

公开(公告)日：2015-06-11

申请号：US14623841

申请日：2015-02-17

Applicant: ALSTOM Technology Ltd

Inventor： Andreas HUBER ,  Nicolas NOIRAY ,  Bruno SCHUERMANS ,  Urs BENZ

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F23M20/005 ,  F23R2900/00014 ,  F23R2900/03041 ,  F23R2900/03043

Abstract: A combustion device (1) for a gas turbine includes portions (12) having an inner and an outer wall (13, 14) with an interposed noise absorption plate (15) having a plurality of holes (16). The combustion device (1) further has first passages (17) connecting zones between the inner wall (13) and the plate (15) to the inside of the combustion device (1) and second passages (21) for cooling the inner wall (13). The portions (12) also have an inner layer (22) between the inner wall (13) and the plate (15) defining inner chambers (23), each connected to at least a first passage (17), and an outer layer (24) between the outer wall (14) and the plate (15) defining outer chambers (25) connected to the inner chambers (23) via the holes (16) of the plate (15).

Abstract translation: 一种用于燃气轮机的燃烧装置（1）包括具有内壁和外壁（13,14）的部分（12），其具有带有多个孔（16）的插入式吸声板（15）。 燃烧装置（1）还具有将内壁（13）和板（15）之间的区域连接到燃烧装置（1）的内部的第一通道（17）和用于冷却内壁的第二通道（21） 13）。 部分（12）还在内壁（13）与限定内腔（23）之间的内层（22）之间具有内层（22），每个内层连接至少一第一通道（17）和外层 外壁（14）和板（15）之间通过板（15）的孔（16）限定连接到内室（23）的外室（25）。

公开(公告)号：US20150047313A1

公开(公告)日：2015-02-19

申请号：US14445413

申请日：2014-07-29

Applicant: ALSTOM Technology Ltd

Inventor： Michael Thomas MAURER ,  Urs BENZ ,  Slawomir SWIATEK ,  Oliver KONRADT ,  Maurice MALLM

IPC: F23R3/00 ,  F02C3/00

CPC classification number: F23R3/002 ,  F02C3/00 ,  F23R3/04 ,  F23R3/06 ,  F23R2900/00018 ,  F23R2900/03041 ,  F23R2900/03045

Abstract: A design for an effectively cooling a liner of a gas turbine combustor by means of convective cooling is disclosed.

Abstract translation: 公开了一种通过对流冷却来有效地冷却燃气轮机燃烧器的衬套的设计。

公开(公告)号：US20140345285A1

公开(公告)日：2014-11-27

申请号：US14279888

申请日：2014-05-16

Applicant: ALSTOM TECHNOLOGY LTD

Inventor： Urs BENZ ,  Nicolas Noiray

IPC: F23R3/16

CPC classification number: F23R3/16 ,  F23M20/005 ,  F23M2900/05002 ,  F23R3/002 ,  F23R3/60 ,  F23R2900/00005 ,  F23R2900/00014

Abstract: The invention relates to a damper for reducing the pulsations in a combustion chamber of a gas turbine. The damper includes a resonator cavity with an inlet and a neck tube in flow communication with the interior of the combustion chamber and resonator cavity, and a compensation assembly pivotably connected with the neck tube. The compensation assembly is inserted between the resonator cavity and the combustion chamber to permit relative rotation between the combustion chamber and the resonator cavity. With the damper according to the present invention, by way of providing the compensation assembly, it is assured the relative rotation between the combustion chamber and the resonator cavity is compensated, hence operation life is elongated.

Abstract translation: 本发明涉及一种用于减少燃气轮机的燃烧室中的脉动的阻尼器。 阻尼器包括谐振器腔，其具有与燃烧室和谐振腔的内部流动连通的入口和颈管，以及与颈管可枢转地连接的补偿组件。 补偿组件插入在谐振器腔和燃烧室之间以允许燃烧室和谐振器腔之间的相对旋转。 利用根据本发明的阻尼器，通过提供补偿组件，确保补偿燃烧室和谐振腔之间的相对旋转，从而延长了操作寿命。