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31. 发明申请

US20120297777A1 REHEAT BURNER INJECTION SYSTEM WITH FUEL LANCES 有权
标题翻译：燃料燃烧器燃烧器注射系统
公开(公告)号：US20120297777A1
公开(公告)日：2012-11-29
申请号：US13465544
申请日：2012-05-07
申请人： Madhavan Poyyapakkam , Urs Benz , Andre Theuer , Anton Winkler , Andrea Ciani
发明人： Madhavan Poyyapakkam , Urs Benz , Andre Theuer , Anton Winkler , Andrea Ciani
IPC分类号： F23R3/28 , F02C7/18
CPC分类号： F23D14/78 , F23C5/08 , F23R3/20 , F23R3/283 , F23R3/286 , F23R3/50 , F23R2900/03042 , F23R2900/03341
摘要： The disclosure relates to a burner such as for a secondary combustion chamber of a gas turbine with sequential combustion having a first and a second combustion chamber, with an injection device for introduction of at least one gaseous and/or liquid fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one gaseous fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. At least one nozzle has its outlet orifice downstream of a trailing edge of the streamlined body.
摘要翻译：本公开涉及一种燃烧器，例如用于具有顺序燃烧的燃气轮机的二次燃烧室，其具有第一和第二燃烧室，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。注射装置具有至少一个主体，该主体布置在具有至少一个用于将至少一种气体燃料引入燃烧器的喷嘴中的至少一个喷嘴中，该至少一个主体被配置为流线型主体，其具有流线型横截面轮廓并且其纵向方向垂直地或以与燃烧器中的主流动方向倾斜的方式延伸。至少一个喷嘴的出口孔在流线型体的后缘的下游。

32. 发明申请

US20120260657A1 COMBUSTOR OF A GAS TURBINE 有权
标题翻译：燃气轮机的燃烧器
公开(公告)号：US20120260657A1
公开(公告)日：2012-10-18
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： F23R3/26
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。

33. 发明申请

US20110265484A1 COMBUSTION DEVICE FOR A GAS TURBINE 有权
标题翻译：燃气涡轮机燃烧装置
公开(公告)号：US20110265484A1
公开(公告)日：2011-11-03
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： F23R3/42
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）。

34. 发明授权

US07937950B2 Device for fastening a sequentially operated burner in a gas turbine arrangement 有权
标题翻译：用于将顺序操作的燃烧器紧固在燃气轮机装置中的装置
公开(公告)号：US07937950B2
公开(公告)日：2011-05-10
申请号：US11692277
申请日：2007-03-28
申请人： Urs Benz , Thorsten Christoph Motzkus
发明人： Urs Benz , Thorsten Christoph Motzkus
IPC分类号： F02C7/20
CPC分类号： F23R3/283
摘要： A device for fastening a second burner (SEV burner) (1) in a sequentially operated gas turbine arrangement, in which a fuel/air mixture is burnt in a first burner, so as to form hot gases which can subsequently be supplied, partly expanded, for a second combustion to the SEV burner (1), in which the burner is designed essentially as a flow duct, with a flow duct wall, which has an orifice (2), through which a fuel supply (3) can be introduced into the interior of the SEV burner (1), and on which are provided in the axial direction of the orifice (2), in each case opposite one another, two fastening structures (5), into which in each case a carrying structure for the further fastening of the SEV burner (1) to an external carrier (8) can be introduced. The carrying structure includes a unitary carrier plate (10) on which countercontours for fastening to the two fastening structures (5) lying opposite the orifice (2) are provided and which provides a recess which corresponds at least to the size of the orifice (2) in the flow duct wall, so that, in the state fastened to the external carrier (8), the carrier plate (10) does not cover the orifice (2) of the flow duct wall.
摘要翻译：一种用于将第二燃烧器（SEV燃烧器）（1）紧固在依次操作的燃气轮机装置中的装置，其中燃料/空气混合物在第一燃烧器中燃烧，以便形成随后可供应的部分膨胀的热气体，用于对SEV燃烧器（1）的第二次燃烧，其中燃烧器基本上设计为流动管道，其中流动管道壁具有孔口（2），燃料供应源（3）可以通过该孔口引入在所述SEV燃烧器（1）的内部，并且在所述孔口（2）的轴向方向上设置在每个壳体中彼此相对的两个紧固结构（5），每个所述紧固结构（5）中分别具有用于可以引入SEV燃烧器（1）进一步紧固到外部载体（8）。承载结构包括一个整体式承载板（10），在其上设置有用于紧固到与孔口（2）相对的两个紧固结构（5）的反向轮廓，并且提供了至少对应于孔口（2）的尺寸的凹部），使得在固定到外部载体（8）的状态下，承载板（10）不覆盖流动管壁的孔口（2）。

35. 发明授权

US07726022B2 Method of dismantling a portion of a turbomachine 有权
标题翻译：拆卸涡轮机的一部分的方法
公开(公告)号：US07726022B2
公开(公告)日：2010-06-01
申请号：US11623778
申请日：2007-01-17
申请人： Bogdan Trbojevic , Stevica Furdek , Urs Benz , Anna Maria Olsson , Elisabetta Carrea
发明人： Bogdan Trbojevic , Stevica Furdek , Urs Benz , Anna Maria Olsson , Elisabetta Carrea
IPC分类号： B21K25/00 , F02C7/20
CPC分类号： F23R3/50 , F23R3/60 , Y10T29/4932
摘要： A method of dismantling a turbomachine includes opening a turbomachine casing in the region of a combustion chamber, releasing a top half shell from a bottom half shell, axially displacing the top half shell and thereafter removing the top half shell in essentially the radial direction, rotationally fixedly connecting an auxiliary tool to the rotor of the turbomachine, connecting the auxiliary tool to the bottom half shell via axially displaceable adapter slides arranged on said auxiliary tool, axially displacing the bottom half shell to release the bottom half shell from axial connecting contours, rotating the bottom half shell with the rotor by approximately 180° until the bottom half shell assumes essentially the position of the removed top half shell, and releasing the bottom half shell and removal of said bottom half shell.
摘要翻译：拆卸涡轮机的方法包括在燃烧室的区域中打开涡轮机壳体，从下半壳释放上半壳体，轴向移动上半壳体，然后基本沿径向方向移除上半壳体，旋转地将辅助工具固定地连接到涡轮机的转子，通过布置在所述辅助工具上的可轴向移动的适配器滑块将辅助工具连接到下半壳体，轴向移动底部半壳体以将下半壳体从轴向连接轮廓释放，底部半壳与转子一起大约180°，直到底部半壳基本上呈现出去除的上半壳的位置，并且释放下半壳并去除所述下半壳。

36. 发明申请

US20090071167A1 TURBOMACHINE, ESPECIALLY GAS TURBINE 有权
标题翻译：涡轮机，特别气体涡轮
公开(公告)号：US20090071167A1
公开(公告)日：2009-03-19
申请号：US12140094
申请日：2008-06-16
申请人： Urs Benz , Jonas Hurter , Thorsten Motzkus
发明人： Urs Benz , Jonas Hurter , Thorsten Motzkus
IPC分类号： F02C7/20
CPC分类号： F01D11/005 , F01D9/023
摘要： A turbomachine with at least one combustion chamber and at least one turbine which lies downstream of it. The turbine has at least one support element and a lining element connected to the support element and formed as a heat shield. A gap sealed by means of a seal, is formed between the at least one combustion chamber and the turbine, an exchangeable insert is arranged in the gap on the end face on the support element and protects at least the support element against hot gases which penetrate into the gap, and against oxidation which is associated with it.
摘要翻译：具有至少一个燃烧室的涡轮机和位于其下游的至少一个涡轮机。涡轮机具有至少一个支撑元件和连接到支撑元件并形成为隔热罩的衬里元件。在所述至少一个燃烧室和所述涡轮机之间形成有通过密封件密封的间隙，在所述支撑元件的端面上的所述间隙中布置有可交换的插入件，并且至少保护所述支撑元件免受穿透的热气体进入间隙，并防止与之相关的氧化。

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