公开(公告)号：US20150247426A1

公开(公告)日：2015-09-03

申请号：US14631945

申请日：2015-02-26

Applicant: ALSTOM Technology Ltd

Inventor： Franklin Marie GENIN ,  Devis TONON ,  Mirko Ruben BOTHIEN ,  Douglas Anthony PENNELL

IPC: F01D25/30

CPC classification number: F01D25/30 ,  F05D2220/32 ,  F05D2260/96 ,  F23R3/06 ,  F23R2900/00014

Abstract: An acoustic damping device is provided which includes at least one opening for a sealing gas to deflect a grazing gas flow away from the mouth of an acoustic damper.

Abstract translation: 提供了一种声阻尼装置，其包括用于密封气体的至少一个开口，以使放电气流偏离声阻尼器的口。

公开(公告)号：US20150226122A1

公开(公告)日：2015-08-13

申请号：US14693045

申请日：2015-04-22

Applicant: ALSTOM Technology Ltd

Inventor： Michael DUESING ,  Luis TAY WO CHONG HILARES ,  Mirko Ruben BOTHIEN ,  Jaan HELLAT ,  Bruno SCHUERMANS

IPC: F02C7/141 ,  F02C3/04 ,  F23R3/42

CPC classification number: F23R3/06 ,  F02C6/02 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/964 ,  F23M20/005 ,  F23R3/002 ,  F23R2900/00014 ,  F23R2900/03341 ,  Y02E20/16

Abstract: The invention refers to a sequential combustor arrangement including a first burner, a first combustion chamber, a mixer for admixing a dilution gas 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 mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber with a low pressure drop. The disclosure further refers to a method for operating a gas turbine with such a combustor arrangement.

Abstract translation: 本发明涉及一种连续的燃烧器装置，其包括第一燃烧器，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热气体，第二燃烧器和第二燃烧室， 流体流动连接。 混合器包括从混合器的侧壁向内指向的多个注入管，用于混合稀释气体以以低压降将离开第一燃烧室的热烟道气冷却。 本发明还涉及一种用这种燃烧器装置操作燃气轮机的方法。

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。