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1.发明申请HELMHOLTZ DAMPER AND GAS TURBINE WITH SUCH A HELMHOLTZ DAMPER 审中-公开HELMHOLTZ阻尼器和带有这种HELMHOLTZ阻尼器的气体涡轮公开(公告)号：US20160153661A1
公开(公告)日：2016-06-02
申请号：US14934277
申请日：2015-11-06
发明人： Mirko Ruben BOTHIEN , Andre THEUER , Jost IMFELD
IPC分类号： F23R3/16
CPC分类号： F23R3/16 , F23R3/002 , F23R2900/00013 , F23R2900/00014
摘要： A Helmholtz damper, especially for damping pulsations in a combustor of a gas turbine, including a damper volume, which can be connected to a damped space by means of a neck tube. The Helmholtz damper further includes a piston, which is moveable within the damper volume and divides the damper volume into a variable first part (V1) on one side of said piston. The variable first part (V1) is connected to the neck tube, and a correspondingly variable second part (V2) on the other side of said piston. The control mechanism is substantially simplified in a more compact design by the piston being driven by a pressure drop (Δp) between the first and second part (V1, V2) of the damper volume.
摘要翻译： 亥姆霍兹阻尼器，特别是用于阻尼燃气涡轮机的燃烧器中的脉动，包括阻尼器体积，其可以通过颈管连接到阻尼空间。 亥姆霍兹阻尼器还包括活塞，该活塞可在阻尼器容积内移动，并将阻尼器体积分成在所述活塞的一侧上的可变第一部分（V1）。 可变第一部分（V1）连接到颈管和在所述活塞的另一侧上的相应可变的第二部分（V2）。 通过由减震器容积的第一和第二部分（V1，V2）之间的压降（＆Dgr; p）驱动活塞，更紧凑的设计大大简化了控制机构。
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2.发明申请公开(公告)号：US20150101332A1
公开(公告)日：2015-04-16
申请号：US14510501
申请日：2014-10-09
IPC分类号： F23R3/26
CPC分类号： F23R3/26 , F23R3/00 , F23R3/002 , F23R2900/00014
摘要： A combustion chamber of a gas turbine includes an optimized arrangement of acoustic dampers.
摘要翻译： 燃气涡轮机的燃烧室包括声阻尼器的优化布置。
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公开(公告)号：US20130125547A1
公开(公告)日：2013-05-23
申请号：US13683061
申请日：2012-11-21
CPC分类号： F23R3/28 , F02C9/26 , F05D2270/31 , F23N1/00 , F23N5/242 , F23N2041/20 , F23R3/36
摘要： A method and apparatus are disclosed for operating a combustion device during a transient operation. The combustion device is fed with at least a fuel. The transient operation includes a period having a period length (T) during which the fuel is fed in an amount lower that a designated (e.g., critical) amount (Mc). A limit value (L) is defined for the period length (T), and fuel feed is regulated to keep the period length (T) smaller or equal to the limit value (L).
摘要翻译： 公开了用于在瞬态操作期间操作燃烧装置的方法和装置。 燃烧装置供给至少一种燃料。 瞬态操作包括具有以低于指定（例如临界）量（Mc）的量供给燃料的周期长度（T）的周期。 对于周期长度（T）定义极限值（L），并且调节燃料供给以使周期长度（T）小于或等于极限值（L）。
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公开(公告)号：US20160123597A1
公开(公告)日：2016-05-05
申请号：US14925527
申请日：2015-10-28
发明人： Douglas Anthony PENNELL , Urs BENZ , Adnan EROGLU , Ewald FREITAG , Mirko Ruben BOTHIEN , Andrea CIANI
CPC分类号： F23R3/346 , F23C6/042 , F23C6/045 , F23C6/047 , F23C2900/07021 , F23D2900/14004 , F23R3/06 , F23R3/283 , F23R3/34 , F23R3/36 , F23R2900/03341
摘要： 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.
摘要翻译： 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。
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公开(公告)号：US20140109591A1
公开(公告)日：2014-04-24
申请号：US14061954
申请日：2013-10-24
摘要： The invention concerns a damper arrangement for reducing combustion-chamber pulsation arising inside a gas turbine, wherein the gas turbine includes at least one compressor, a primary combustor which is connected downstream to the compressor, and the hot gases of the primary combustor are admitted at least to an intermediate turbine or directly or indirectly to a secondary combustor. The hot gases of the secondary combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner includes air passages, wherein at least one of the air passages is formed as a damper neck. The damper neck being actively connected to a damper volume, and the damper volume is part of a connecting duct extending between a compressor air plenum and the combustor.
摘要翻译： 本发明涉及一种用于减少在燃气轮机内部产生的燃烧室脉动的阻尼装置，其中燃气轮机包括至少一个压缩机，连接在压缩机下游的主燃烧器和主燃烧室的热气体 至少到中间涡轮机，或直接或间接地连接到二级燃烧器。 次级燃烧器的热气体被允许进一步涡轮机，或直接地或间接地进入能量回收，其中至少一个燃烧器以罐式结构设置。 至少一个燃烧器衬套包括空气通道，其中至少一个空气通道形成为阻尼颈部。 阻尼器颈部主动地连接到阻尼器体积，并且阻尼器体积是在压缩机空气室和燃烧器之间延伸的连接管道的一部分。
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公开(公告)号：US20140109579A1
公开(公告)日：2014-04-24
申请号：US14062091
申请日：2013-10-24
IPC分类号： F23R3/00
CPC分类号： F01D9/023 , F02C7/12 , F05D2250/52 , F23R3/002 , Y10T29/49229
摘要： The disclosure relates 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 an 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. The combustor transition is, characterized in that at least one side wall has a side wall extension, which is extending in a downstream direction beyond the outlet. Besides the combustor transition a gas turbine includes 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.
摘要翻译： 本公开涉及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。 燃烧器转变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。 燃烧器过渡的特征在于，至少一个侧壁具有侧向延伸部，该侧壁延伸部沿下游方向延伸超过出口。 除了燃烧器过渡之外，还公开了一种燃气轮机包括这样的燃烧器过渡，用于改变具有这种燃烧器过渡的燃气轮机的方法以及用于具有这种燃烧器过渡的GT的管道检查方法。
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公开(公告)号：US20140069738A1
公开(公告)日：2014-03-13
申请号：US13689926
申请日：2012-11-30
IPC分类号： F02C7/24
CPC分类号： F02C7/24 , F23M20/005 , F23R3/08 , F23R2900/00014
摘要： An acoustic damper arrangement for a combustor which has an inner liner configured for use at a first temperature during operation and an outer liner configured for operation at a second temperature lower than the first temperature during operation is disclosed, the acoustic damper arrangement comprising: a plurality of flexible sheets; and at least one hollow body having an interior volume, each of said at least one hollow body being fixed to one of the plurality of flexible sheets, wherein the acoustic damper arrangement is configured to be fixed to both the inner liner and the outer liner such that the interior volume of the at least one hollow body is in communication with a chamber formed by the inner liner, and the plurality of flexible sheets accommodate expansion and contraction of the inner liner relative to the outer liner.
摘要翻译： 公开了一种用于燃烧器的声音阻尼器装置，其具有构造成在操作期间在第一温度下使用的内衬套和被构造成在操作期间低于第一温度的第二温度下操作的外衬套，所述声阻尼器装置包括：多个 的柔性片; 以及具有内部容积的至少一个空心体，所述至少一个中空体中的每一个固定到所述多个柔性片中的一个，其中所述声阻尼装置被构造成固定到所述内衬层和所述外衬套上， 所述至少一个中空体的内部体积与由所述内衬层形成的腔室连通，并且所述多个柔性片材适应所述内衬套相对于所述外衬套的膨胀和收缩。
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公开(公告)号：US20150047357A1
公开(公告)日：2015-02-19
申请号：US14444177
申请日：2014-07-28
CPC分类号： F23R3/04 , F02C3/14 , F05D2260/963 , F23R3/002 , F23R2900/00014
摘要： The invention relating to a A damper for combustion oscillation damping for a gas turbine, includes a resonator cavity with a box or cylinder shape, a neck in flow communication with the resonator cavity and a combustion chamber. The length Lneck of the neck is equal or greater than a maximum distance lmax that a hot gas ingested from the combustion chamber reaches in the neck. The maximum distance lmax is determined according to the following equation: l max = ∫ t 1 t 2 U - p ^ ρ U ζ sin ( ω t ) t . With the solution of the present invention, the damper used to damping combustion oscillation may prevent hot gas ingestion during normal operations by uniquely determining the dimensions of the neck connecting the resonator cavity and the combustion chamber.
摘要翻译： 本发明涉及一种用于燃气轮机的燃烧振动阻尼的阻尼器，包括具有箱形或圆筒形状的谐振腔，与谐振器腔流动连通的颈部和燃烧室。 颈部的长度Lneck等于或大于从燃烧室吸入的热气体到达颈部的最大距离lmax。 最大距离lmax根据以下等式确定：l max =∫t 1 t 2 U - p ^＆rgr; 呃ζζ。。。。。。。。。。。 利用本发明的解决方案，用于抑制燃烧振荡的阻尼器可以通过唯一地确定连接谐振器腔和燃烧室的颈部的尺寸来防止正常操作期间的热气体摄取。
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公开(公告)号：US20150096829A1
公开(公告)日：2015-04-09
申请号：US14505564
申请日：2014-10-03
IPC分类号： F02C7/24
CPC分类号： F02C7/24 , F23M20/005 , F23R3/16 , F23R2900/00014
摘要： An acoustic damper includes a neck and a damping volume. The neck has a mouth being in fluid connection with a chamber. The chamber is limited by an inner surface of at least one wall. The acoustic damper device includes a recess located between the mouth of the neck and the inner surface of the wall.
摘要翻译： 声阻尼器包括颈部和阻尼体积。 颈部具有与腔室流体连接的口。 该室由至少一个壁的内表面限制。 声阻尼装置包括位于颈部的口部和壁的内表面之间的凹部。
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公开(公告)号：US20140345284A1
公开(公告)日：2014-11-27
申请号：US14279767
申请日：2014-05-16
IPC分类号： F23R3/16
CPC分类号： F23M20/005 , F23R3/002 , F23R2900/00014
摘要： The invention relates to a damper for reducing pulsations in a gas turbine, which includes an enclosure, a main neck extending from the enclosure, a spacer plate disposed in the enclosure to separate the enclosure into a first cavity and a second cavity and an inner neck with a first end and a second end, extending through the spacer plate to interconnect the first cavity and the second cavity. The first end of the inner neck remains in the first cavity and the second end remains in the second cavity. A flow deflecting member is disposed proximate the second end of the inner neck to deflect a flow passing through the inner neck.With the solution of the present invention, as a damper according to embodiments of the present invention operates, flow field hence damping characteristic in the second cavity constant regardless the adjustment of the spacer plate in the enclosure.
摘要翻译： 本发明涉及一种用于减少燃气涡轮机中的脉动的阻尼器，其包括外壳，从外壳延伸的主颈部，设置在外壳中的间隔板，以将外壳分隔成第一空腔，第二空腔和内颈部 第一端和第二端延伸穿过间隔板以互连第一腔和第二腔。 内颈部的第一端保持在第一腔中，第二端保持在第二腔中。 流动偏转构件设置在内颈部的第二端附近以偏转通过内颈部的流动。 利用本发明的解决方案，作为根据本发明的实施例的阻尼器，无论调节外壳中的间隔板如何，流动场因此第二腔中的阻尼特性恒定。
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