专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US09097118B2 Transitional region for a combustion chamber of a gas turbine 有权
标题翻译：燃气轮机燃烧室的过渡区域
公开(公告)号：US09097118B2
公开(公告)日：2015-08-04
申请号：US13226020
申请日：2011-09-06
申请人： Martin Schnieder , Jörg Krückels , Uwe Rüdel , Christoph Appel , Urs Benz
发明人： Martin Schnieder , Jörg Krückels , Uwe Rüdel , Christoph Appel , Urs Benz
IPC分类号： F02C7/24 , F23R3/04 , F01D9/02 , F23R3/00
CPC分类号： F01D9/023 , F02C7/24 , F23R3/002 , F23R3/007 , F23R2900/00005 , F23R2900/03042 , Y02T50/67 , Y02T50/675
摘要： A gas turbine including a combustion chamber and a first row of guide vanes, arranged essentially directly downstream thereof, of a turbine. The outer and/or inner limitation of the combustion chamber defined by at least one outer and/or inner heat shield, mounted on at least one combustion chamber structure arranged radially outside and/or inside. The hot gases flow path in the region of the guide vane row being restricted radially on the outside and/or inside by an outer and/or inner vane platform, mounted at least indirectly on at least one turbine carrier. A minimal gap size directly upstream of the first row of guide vanes is achieved by mounting at least indirectly on the turbine carrier at least one mini heat shield, arranged upstream of the first row of guide vanes and essentially adjacent the vane platform and in the flow direction between the heat shield and the vane platform.
摘要翻译：一种燃气轮机，包括燃烧室和第一排导叶，基本上直接布置在涡轮的下游。由至少一个外部和/或内部热屏蔽限定的燃烧室的外部和/或内部限制，其安装在径向外侧和/或内部布置的至少一个燃烧室结构上。引导叶片排的区域中的热气体流动通道至少间接地安装在至少一个涡轮机载体上的外部和/或内部叶片平台的外侧和/或内部径向限制。通过至少间接地安装在涡轮机载体上至少一个微型隔热罩来实现第一排导叶直接上游的最小间隙尺寸，其布置在第一排导叶的上游并且基本上邻近叶片平台和流体隔热板和叶片平台之间的方向。

2. 发明授权

US08635874B2 Gas turbine combustor including an acoustic damper device 有权
标题翻译：包括声阻尼装置的燃气轮机燃烧器
公开(公告)号：US08635874B2
公开(公告)日：2014-01-28
申请号：US13424839
申请日：2012-03-20
申请人： Adnan Eroglu , Ewald Freitag , Uwe Rüdel , Urs Benz , Andreas Huber
发明人： Adnan Eroglu , Ewald Freitag , Uwe Rüdel , Urs Benz , Andreas Huber
IPC分类号： F02C7/24
CPC分类号： F23R3/002 , F23M20/005 , F23R2900/00014
摘要： An exemplary combustor includes at least a portion having an inner liner and an outer cover plate, which together form an interposed cooling chamber. A plurality of hollow elements extend from the liner and protrude into the cooling chamber. Each hollow element defines a damping volume connected to an inner volume of the combustion chamber via a calibrated duct. During operation, the hollow elements damp pressure pulsations and, in addition, also transfer heat.
摘要翻译：示例性燃烧器包括至少一部分，其具有内衬和外盖板，它们一起形成插入的冷却室。多个中空元件从衬套延伸并突出到冷却室中。每个中空元件通过校准的管道限定连接到燃烧室的内部容积的阻尼体积。在操作过程中，中空元件阻尼压力脉动，另外也传递热量。

3. 发明申请

US20090044539A1 FUEL LANCE FOR A GAS TURBINE INSTALLATION AND A METHOD FOR OPERATING A FUEL LANCE 有权
标题翻译：用于燃气涡轮机安装的燃料和操作燃油的方法
公开(公告)号：US20090044539A1
公开(公告)日：2009-02-19
申请号：US12240268
申请日：2008-09-29
申请人： Adnan Eroglu , Felix Guethe , Urs Benz
发明人： Adnan Eroglu , Felix Guethe , Urs Benz
IPC分类号： F02C7/22 , F23R3/28
CPC分类号： F23R3/36 , F23L7/00 , F23L2900/07002 , F23L2900/07009 , Y02E20/16
摘要： A fuel lance for a gas turbine installation with sequential combustion, in which hot gas is produced in a first combustion chamber and expanded in a subsequent turbine, and then flows through a subsequent second combustion chamber in which the fuel lance for injecting fuel into the hot gas is arranged. The fuel lance has a lance section which extends in the flow direction of the hot gas and includes at least an outer tube which is arranged concentrically to a lance axis, and a center tube which is concentrically arranged in the outer tube and in which the fuel is guided to the lance tip and is injected through first injection openings in the region of the lance tip into the hot gas. The fuel lance is modified for operation with syngas by the first injection openings being arranged directly on the lance tip, and by the first injection openings being oriented so that the fuel jets which emerge from them include an acute angle with the lance axis.
摘要翻译：一种用于具有顺序燃烧的燃气轮机装置的燃料喷枪，其中在第一燃烧室中产生热气体并在随后的涡轮机中膨胀，然后流过随后的第二燃烧室，其中燃料喷枪用于将燃料喷射到热排气。燃料喷枪具有沿着热气体的流动方向延伸的喷枪部分，并且至少包括与喷枪轴线同心设置的外管，以及同心地布置在外管中的中心管，其中燃料被引导到喷枪尖端，并且通过喷枪尖端的区域中的第一喷射孔注入热气体中。燃料喷枪通过第一喷射开口被直接设置在喷枪尖端上而被修改以用合成气操作，并且第一喷射开口被定向成使得从它们出来的燃料射流与喷枪轴线成锐角。

4. 发明授权

US07104065B2 Damping arrangement for reducing combustion-chamber pulsation in a gas turbine system 有权
标题翻译：用于减少燃气轮机系统中的燃烧室脉动的阻尼装置
公开(公告)号：US07104065B2
公开(公告)日：2006-09-12
申请号：US10488595
申请日：2002-08-28
申请人： Urs Benz , Jaan Hellat , Franz Joos
发明人： Urs Benz , Jaan Hellat , Franz Joos
IPC分类号： F02C7/24
CPC分类号： F23R3/002 , F23M20/005 , F23R2900/00014
摘要： A description is given of a damping arrangement for reducing resonant vibrations in a combustion chamber (1), with a combustion-chamber wall (2), which is of double-walled design and, with an outer wall-surface part (22) and an inner wall-surface part (21) facing the combustion chamber (1), gastightly encloses an intermediate space (3), into which cooling air can be fed for purposes of convective cooling of the combustion-chamber wall (2).The invention is distinguished by the fact that at least one third wall-surface part (4) is provided, which, with the outer wall-surface part (22), encloses a gastight volume (5), and that the gastight volume (5) is connected gastightly to the combustion chamber (1) by at least one connecting line (6).
摘要翻译：给出了一种用于减少燃烧室（1）中的共振振动的阻尼装置，其具有双壁设计的燃烧室壁（2）和外壁表面部分（22）和朝向燃烧室（1）的内壁表面部分（21），气密地包围中间空间（3），冷却空气可以被供给到中间空间（3）中，以用于燃烧室壁（2）的对流冷却。本发明的区别在于，提供至少一个第三壁表面部分（4），其中外壁表面部分（22）包围气密体积（5），并且气密体积（5））通过至少一个连接线（6）气密地连接到燃烧室（1）。

5. 发明授权

US06718773B2 Method for igniting a thermal turbomachine 有权
标题翻译：点燃热涡轮机的方法
公开(公告)号：US06718773B2
公开(公告)日：2004-04-13
申请号：US10095519
申请日：2002-03-13
申请人： Marcel Stalder , Urs Benz , Franz Joos , Pirmin Schiessel , Jaan Hellat , Guenter Sybon
发明人： Marcel Stalder , Urs Benz , Franz Joos , Pirmin Schiessel , Jaan Hellat , Guenter Sybon
IPC分类号： F02C7264
CPC分类号： F23R3/343 , F02C7/264 , F23D11/404 , F23D11/42 , F23D17/002 , F23D2207/00
摘要： In a method for igniting a thermal turbomachine, the turbomachine containing a combustion chamber (30), an ignition device (10), a fuel supply (60) and an air supply (70), and the ignition device (10) consisting of an ignition space (50) and of an ignitor (51) arranged in the ignition space (50), the fuel supply (60) and the air supply (70) discharging into the ignition space (50), and the ignition space (50) being connected to the combustion chamber (30) via a flame tube (40), prior to the ignition of the combustion chamber (30), an overall fuel/air mixture ratio &PHgr;overall=1/&lgr;overall greater than 1, with &lgr;overall being the overall air ratio, is set in the flame tube (40) of the ignition device (10).
摘要翻译：在用于点燃热涡轮机的方法中，包含燃烧室（30），点火装置（10），燃料供应（60）和空气供应（70）的涡轮机和由点火空间（50）和布置在点火空间（50）中的点火器（51），燃料供应（60）和排放到点火空间（50）中的空气供应（70）和点火空间（50）在燃烧室（30）点火之前，通过火焰管（40）连接到燃烧室（30），总燃料/空气混合比Phioverall = 1 /λ超过大于1，其中λ为整体空气比设置在点火装置（10）的火焰管（40）中。

6. 发明授权

US5497611A Process for the cooling of an auto-ignition combustion chamber 失效
标题翻译：自动点火燃烧室的冷却过程
公开(公告)号：US5497611A
公开(公告)日：1996-03-12
申请号：US383438
申请日：1995-02-03
申请人： Urs Benz , David Walhood , Burkhard Schulte-Werning
发明人： Urs Benz , David Walhood , Burkhard Schulte-Werning
IPC分类号： F23R3/06 , F02C7/16 , F23R3/02 , F23R3/12 , F23R3/54
CPC分类号： F23R3/12 , F23R3/02 , F23R3/54 , F23R2900/03041 , F23R2900/03341
摘要： In a combustion chamber which consists essentially of an inflow zone and a combustion zone, the working gases flowing at high temperature into the combustion chamber are mixed with a fuel, in such a way that the latter initiates auto-ignition. Whilst the inflow zone is cooled by effusion cooling, convective cooling is adopted in the combustion zone, the cooling air for the last-mentioned cooling being used at the same time as cooling air for the effusion cooling.
摘要翻译：在基本上由流入区域和燃烧区域组成的燃烧室中，将高温流入燃烧室的工作气体与燃料混合，使燃料室开始自动点火。在流入区域通过喷射冷却来冷却时，在燃烧区域采用对流冷却，最后一次冷却的冷却空气与冷却空气一起用于渗出冷却。

7. 发明授权

US08991185B2 Combustion device for a gas turbine configured to suppress thermo-acoustical pulsations 有权
标题翻译：用于燃气轮机的燃烧装置，其构造成抑制热声脉动
公开(公告)号：US08991185B2
公开(公告)日：2015-03-31
申请号：US13097221
申请日：2011-04-29
申请人： Andreas Huber , Nicolas Noiray , Bruno Schuermans , Urs Benz
发明人： Andreas Huber , Nicolas Noiray , Bruno Schuermans , Urs Benz
IPC分类号： F02C7/24 , F23R3/00
CPC分类号： F23R3/002 , F23M20/005 , F23R2900/00014 , F23R2900/03041 , F23R2900/03043
摘要： 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).
摘要翻译：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）。

8. 发明授权

US08978382B2 Combustion device with a layered wall structure for a gas turbine 有权
标题翻译：具有用于燃气轮机的分层壁结构的燃烧装置
公开(公告)号：US08978382B2
公开(公告)日：2015-03-17
申请号：US13031654
申请日：2011-02-22
申请人： Andreas Huber , Nicolas Noiray , Urs Benz , Felix Reinert , Diane Lauffer
发明人： Andreas Huber , Nicolas Noiray , Urs Benz , Felix Reinert , Diane Lauffer
IPC分类号： F02C7/24 , F23R3/00
CPC分类号： F23R3/002 , F23M20/005 , F23R2900/00014
摘要： A combustion device for a gas turbine includes an interior portion, an inner wall having a plurality of first passages and an outer wall having a plurality of second passages configured to cool the inner wall, each of the plurality of second passages having an outlet opening into a third passage. An intermediate layer is disposed between the inner wall and the outer wall and defines a plurality of chambers, each chamber forming a Helmholtz damper and being connected to the interior portion by at least one of the plurality of first passages and being connected to at least one of the plurality of second passages by at least one of the plurality of third passages.
摘要翻译：一种用于燃气轮机的燃烧装置，包括内部部分，具有多个第一通道的内壁和具有多个第二通道的外壁，该第二通道构造成冷却内壁，多个第二通道中的每一个具有出口开口第三段。中间层设置在内壁和外壁之间并且限定多个室，每个室形成亥姆霍兹阻尼器，并通过多个第一通道中的至少一个连接到内部部分，并连接至至少一个的所述多个第二通道中的至少一个通过所述多个第三通道中的至少一个。

9. 发明申请

US20120324863A1 COOLING SCHEME FOR AN INCREASED GAS TURBINE EFFICIENCY 有权
标题翻译：提高燃气效率的冷却方案
公开(公告)号：US20120324863A1
公开(公告)日：2012-12-27
申请号：US13465830
申请日：2012-05-07
申请人： Anton WINKLER , Urs BENZ , Andre THEUER , Diane LAUFFER , Madhavan POYYAPAKKAM
发明人： Anton WINKLER , Urs BENZ , Andre THEUER , Diane LAUFFER , Madhavan POYYAPAKKAM
IPC分类号： F23R3/36 , F02C7/18
CPC分类号： F23R3/283 , F23D2214/00 , F23R3/20 , F23R3/34
摘要： A burner for a combustion chamber of a turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner is proposed. The injection device has at least one body arranged in the burner with at least two nozzles for introducing the at least one fuel into the burner, the body being configured with a streamlined cross-sectional profile which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The carrier air plenum is provided with holes such that carrier air exiting through the holes impinges an inner side of a leading edge portion of the body.
摘要翻译：提出了一种用于涡轮机燃烧室的燃烧器，其具有用于将至少一种气体和/或液体燃料引入燃烧器的注射装置。注射装置具有布置在燃烧器中的至少一个主体，其具有至少两个用于将至少一种燃料引入燃烧器的喷嘴，该主体构造成流线型的横截面轮廓，其纵向方向垂直地或以倾斜方向延伸到燃烧器中主要的流动方向。承载空气通风孔设置有孔，使得通过孔排出的载气侵入本体前缘部分的内侧。

10. 发明申请

US20120060503A1 TRANSITIONAL REGION FOR A COMBUSTION CHAMBER OF A GAS TURBINE 有权
标题翻译：燃气轮机燃烧室过渡区
公开(公告)号：US20120060503A1
公开(公告)日：2012-03-15
申请号：US13226020
申请日：2011-09-06
申请人： Martin SCHNIEDER , Jörg Krückels , Uwe Rüdel , Christoph APPEL , Urs BENZ
发明人： Martin SCHNIEDER , Jörg Krückels , Uwe Rüdel , Christoph APPEL , Urs BENZ
IPC分类号： F23R3/42
CPC分类号： F01D9/023 , F02C7/24 , F23R3/002 , F23R3/007 , F23R2900/00005 , F23R2900/03042 , Y02T50/67 , Y02T50/675
摘要： A gas turbine including a combustion chamber and a first row of guide vanes, arranged essentially directly downstream thereof, of a turbine. The outer and/or inner limitation of the combustion chamber defined by at least one outer and/or inner heat shield, mounted on at least one combustion chamber structure arranged radially outside and/or inside. The hot gases flow path in the region of the guide vane row being restricted radially on the outside and/or inside by an outer and/or inner vane platform, mounted at least indirectly on at least one turbine carrier. A minimal gap size directly upstream of the first row of guide vanes is achieved by mounting at least indirectly on the turbine carrier at least one mini heat shield, arranged upstream of the first row of guide vanes and essentially adjacent the vane platform and in the flow direction between the heat shield and the vane platform.
摘要翻译：一种燃气轮机，包括燃烧室和第一排导叶，基本上直接布置在涡轮的下游。由至少一个外部和/或内部热屏蔽限定的燃烧室的外部和/或内部限制，其安装在径向外侧和/或内部布置的至少一个燃烧室结构上。引导叶片排的区域中的热气体流动通道至少间接地安装在至少一个涡轮机载体上的外部和/或内部叶片平台的外侧和/或内部径向限制。通过至少间接地安装在涡轮机载体上至少一个微型隔热罩来实现第一排导叶直接上游的最小间隙尺寸，其布置在第一排导叶的上游并且基本上邻近叶片平台和流体隔热板和叶片平台之间的方向。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式