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21. 发明授权

US07273347B2 Blade for a gas turbine 有权
标题翻译：燃气轮机叶片
公开(公告)号：US07273347B2
公开(公告)日：2007-09-25
申请号：US11549767
申请日：2006-10-16
申请人： Ulrich Rathmann
发明人： Ulrich Rathmann
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D11/10 , F01D5/186 , F01D5/187 , F01D5/225 , F05D2260/201 , F05D2260/202
摘要： A gas turbine blade (1) has a shroud (3) which is cooled by different cooling mechanisms in various regions (A, B, C) according to the different thermal load. In a first region (A), in a fin (8), bores are provided, by which a convective cooling of the fin and a film cooling of the hot gas side of the fin are implemented. A second region (B) is cooled by impingement cooling by a cooling air stream from a duct in the radially opposite stator housing. A third region (C) has a plurality of bores running parallel which run from a cooling duct of a cooling system for the blade leaf to the radially outer surface of the shroud. A cooling air stream flowing through these bores causes a convective cooling of this region.
摘要翻译：燃气轮机叶片（1）具有根据不同的热负荷在不同的区域（A，B，C）中被不同的冷却机构冷却的护罩（3）。在第一区域（A）中，在翅片（8）中，提供孔，通过该孔实现翅片的对流冷却和翅片的热气体侧的薄膜冷却。第二区域（B）通过来自径向相对的定子壳体中的管道的冷却空气流的冲击冷却来冷却。第三区域（C）具有平行延伸的多个孔，其从用于叶片叶片的冷却系统的冷却管道延伸到护罩的径向外表面。流过这些孔的冷却空气流使该区域对流冷却。

22. 发明申请

US20070071593A1 BLADE FOR A GAS TURBINE 有权
标题翻译：燃气轮机叶片
公开(公告)号：US20070071593A1
公开(公告)日：2007-03-29
申请号：US11549767
申请日：2006-10-16
申请人： Ulrich Rathmann
发明人： Ulrich Rathmann
IPC分类号： F03B11/00
CPC分类号： F01D11/10 , F01D5/186 , F01D5/187 , F01D5/225 , F05D2260/201 , F05D2260/202
摘要： A gas turbine blade (1) has a shroud (3) which is cooled by different cooling mechanisms in various regions (A, B, C) according to the different thermal load. In a first region (A), in a fin (8), bores are provided, by which a convective cooling of the fin and a film cooling of the hot gas side of the fin are implemented. A second region (B) is cooled by impingement cooling by a cooling air stream from a duct in the radially opposite stator housing. A third region (C) has a plurality of bores running parallel which run from a cooling duct of a cooling system for the blade leaf to the radially outer surface of the shroud. A cooling air stream flowing through these bores causes a convective cooling of this region.
摘要翻译：燃气轮机叶片（1）具有根据不同的热负荷在不同的区域（A，B，C）中被不同的冷却机构冷却的护罩（3）。在第一区域（A）中，在翅片（8）中，提供孔，通过该孔实现翅片的对流冷却和翅片的热气体侧的薄膜冷却。第二区域（B）通过来自径向相对的定子壳体中的管道的冷却空气流的冲击冷却来冷却。第三区域（C）具有平行延伸的多个孔，其从用于叶片叶片的冷却系统的冷却管道延伸到护罩的径向外表面。流过这些孔的冷却空气流使该区域对流冷却。

23. 发明申请

US20060137351A1 Wall structure for limiting a hot gas path 审中-公开
标题翻译：用于限制热气路径的壁结构
公开(公告)号：US20060137351A1
公开(公告)日：2006-06-29
申请号：US11188404
申请日：2005-07-25
申请人： Ulrich Rathmann
发明人： Ulrich Rathmann
IPC分类号： F23R3/42
CPC分类号： F01D11/005 , F01D11/02 , F01D25/12 , F02C7/12 , F02C7/28 , F05D2240/11 , F05D2240/57
摘要： A wall structure for restricting a hot-gas path in a gas turbine or in a combustion chamber includes a first wall segment having a first face and a second wall segment having a second face and disposed adjacent to each other in a connection area. A first face is disposed at a distance across from the second face so as to form a gap leading from an inside of the wall segments facing the hot-gas path to an outside of the wall segments facing away from the hot-gas path, wherein each of the first and second faces has a receiving groove having an opening, a bottom portion and two opposing groove walls open towards the gap. A sealing element having a thickness is disposed in the receiving grooves so as to bridge the gap. A first ratio of a distance measured at the groove bottom of each of the receiving grooves between the two respective opposing groove walls to a thickness of the sealing element is equal to or greater than 1.1.
摘要翻译：用于限制燃气轮机或燃烧室中的热气路径的壁结构包括具有第一面的第一壁段和具有第二面并且在连接区域中彼此相邻设置的第二壁段。第一面设置在与第二面相隔的距离处，以形成从面对热气路径的壁段的内部引导到远离热气路径的壁段的外侧的间隙，其中所述第一和第二表面中的每一个具有接收槽，所述接收槽具有开口，底部和朝向间隙开口的两个相对的槽壁。具有厚度的密封元件设置在接收槽中以便桥接间隙。在两个相对的槽壁之间的每个接收槽的槽底处测得的距离与密封元件的厚度的第一比率等于或大于1.1。

24. 发明授权

US06916021B2 Sealing arrangement 有权
标题翻译：密封安排
公开(公告)号：US06916021B2
公开(公告)日：2005-07-12
申请号：US10383735
申请日：2003-03-10
申请人： Alexander Beeck , Bruno Benedetti , Andreas Kieninger , Ulrich Rathmann
发明人： Alexander Beeck , Bruno Benedetti , Andreas Kieninger , Ulrich Rathmann
IPC分类号： F01D5/20 , F01D5/22 , F01D11/08 , F16J15/44
CPC分类号： F16J15/445 , F01D5/225 , F01D11/08 , F16J15/444
摘要： The present invention relates to a sealing arrangement which is formed between a rotating assembly (4, 6) and a static assembly (3, 14, 15). In this sealing arrangement, the rotating assembly (4, 6, 16) has at least one cutting element (1) which engages in a counterpart surface on the static component. The present sealing arrangement is distinguished by the fact that the cutting element (1) is designed as a chipping device with a geometrically determined cutting edge with respect to the counterpart surface (2) or forms a chipping device of this type when the rotating assembly is rotating. The proposed sealing arrangement reduces the wear to the cutting element even in the event of adverse rotation or temperature conditions.
摘要翻译：本发明涉及一种形成在旋转组件（4,6）和静态组件（3,14,15）之间的密封装置。在该密封装置中，旋转组件（4,6,16）具有至少一个切割元件（1），该切割元件（1）与静态部件上的配对表面接合。本密封装置的特征在于，切割元件（1）被设计为具有相对于配对表面（2）几何确定的切割边缘的切屑装置，或者当旋转组件为旋转。所提出的密封装置即使在不利的旋转或温度条件的情况下也减少了对切割元件的磨损。

25. 发明授权

US08303257B2 Shiplap arrangement 有权
标题翻译： Shiplap安排
公开(公告)号：US08303257B2
公开(公告)日：2012-11-06
申请号：US12572034
申请日：2009-10-01
申请人： Thomas Heinz-Schwarzmaier , Ulrich Rathmann , Carlos Simon-Delgado
发明人： Thomas Heinz-Schwarzmaier , Ulrich Rathmann , Carlos Simon-Delgado
IPC分类号： F01D11/02 , F01D5/22
CPC分类号： F01D11/02 , F01D11/005 , F01D11/04 , F05D2240/57
摘要： An arrangement between blade elements in a blade row in a turbine is described. Each blade element has at least one shroud element and a blade airfoil which abuts on, and is connected to, the shroud element, and essentially extends radially with regard to a principal axis of the blade row. When installed, the shroud element sides, which extend circumferentially, abut on the respectively adjacent shroud element of the respectively adjacent blade element, each forming an essentially radial gap. At least one blade element has a projection which projects into the shroud element of the abutting blade element and extends in the circumferential direction, and at least one blade element has a recess which accommodates such a projection. In the region of the projection or recess there is a stepped region of the radial gap, and the guiding of the radial gap in this stepped region is a labyrinth seal.
摘要翻译：描述了涡轮机中的叶片排中的叶片元件之间的布置。每个叶片元件具有至少一个护罩元件和叶片翼型件，其抵靠并连接到护罩元件，并且基本上相对于叶片排的主轴线径向延伸。当安装时，沿周向延伸的护罩元件侧邻接在相邻的相邻叶片元件的相邻的护罩元件上，每个形成基本上径向的间隙。至少一个叶片元件具有突出部，其突出到邻接叶片元件的护罩元件中并沿周向延伸，并且至少一个叶片元件具有容纳这种突起的凹部。在突起或凹槽的区域中，存在径向间隙的台阶区域，并且在该阶梯区域中的径向间隙的引导是迷宫式密封。

26. 发明申请

US20110284669A1 LANCE OF A GAS TURBINE BURNER 有权
标题翻译：燃气轮机燃烧器
公开(公告)号：US20110284669A1
公开(公告)日：2011-11-24
申请号：US13107135
申请日：2011-05-13
申请人： Ulrich Rathmann , Daniel Burri , Thorsten Motzkus
发明人： Ulrich Rathmann , Daniel Burri , Thorsten Motzkus
IPC分类号： B05B1/14
CPC分类号： F23D11/106 , F23C2900/07021 , F23C2900/07022 , F23D14/22 , F23D17/002 , F23R3/28
摘要： A lance of a gas turbine burner includes an inner duct having inner nozzles; an annular outer duct encircling the inner duct and having outer nozzles; and a spacer disposed between a terminal portion of the inner duct and a terminal portion of the outer duct, the spacer being fixed to both the inner duct and the outer duct.
摘要翻译：燃气轮机燃烧器的喷枪包括具有内喷嘴的内管; 围绕所述内部管道并具有外部喷嘴的环形外部管道; 以及间隔件，其设置在内部管道的端子部分和外部管道的端子部分之间，间隔件固定到内部管道和外部管道两者。

27. 发明申请

US20090155054A1 WALL STRUCTURE FOR LIMITING A HOT GAS PATH 有权
标题翻译：限制热气道的壁结构
公开(公告)号：US20090155054A1
公开(公告)日：2009-06-18
申请号：US12390901
申请日：2009-02-23
申请人： Ulrich Rathmann
发明人： Ulrich Rathmann
IPC分类号： F01D25/24
CPC分类号： F01D11/005 , F01D11/02 , F01D25/12 , F02C7/12 , F02C7/28 , F05D2240/11 , F05D2240/57
摘要： A wall structure for restricting a hot-gas path in a gas turbine or in a combustion chamber including a first wall segment having a first face, and a second wall segment having a second face. Each wall segment disposed adjacent to each other so as to define an inside of the wall segments and an outside of the wall segments. The first and second faces being disposed so as to form a gap leading from the inside to the outside. Each of the faces having a receiving groove. The wall structure further including a sealing element having a thickness and disposed in the receiving grooves so as to bridge the gap. The first face having a recess and the second wall segment having a projection that extends from the second face and protrudes into the recess in the first face. The projection having a conical cross section.
摘要翻译：一种用于限制燃气轮机或包括具有第一面的第一壁段的燃烧室中的热气路径的壁结构和具有第二面的第二壁段。每个壁段彼此相邻地设置，以便限定壁段的内部和壁段的外侧。第一和第二面设置成形成从内向外引导的间隙。每个面具有接收槽。所述壁结构还包括具有厚度的密封元件，并且设置在所述容纳槽中以便桥接所述间隙。所述第一面具有凹部，所述第二壁部分具有从所述第二面延伸并突出到所述第一面中的所述凹部中的突起。该突起具有圆锥形截面。

28. 发明授权

US07175387B2 Seal arrangement for reducing the seal gaps within a rotary flow machine 失效
标题翻译：用于减少旋转流动机器内的密封间隙的密封装置
公开(公告)号：US07175387B2
公开(公告)日：2007-02-13
申请号：US10808490
申请日：2004-03-25
申请人： Erhard Kreis , Markus Oehl , Ulrich Rathmann
发明人： Erhard Kreis , Markus Oehl , Ulrich Rathmann
IPC分类号： F01D11/00
CPC分类号： F01D5/22 , F01D11/008 , Y10S277/941
摘要： A seal arrangement for reducing the seal gaps within a rotary flow machine, preferably an axial turbomachine, has rotor blades and guide vanes, which are respectively arranged in at least one rotor blade row and guide vane row and have respective blade/vane roots (2,3) which protrude into fastening contours within the rotor blade and guide vane rows. A sealing element (4) of plastically deformable material is provided between at least two adjacent blade/vane roots (2,3) along a rotor blade row or guide vane row or between a blade/vane root (2,3) of a rotor blade or guide vane and a rotary flow machine component directly adjoining the blade/vane root.
摘要翻译：用于减小旋转流动机械，优选轴向涡轮机械中的密封间隙的密封装置具有转子叶片和导向叶片，其分别设置在至少一个转子叶片排和导向叶片排中并具有相应的叶片/叶片根部（2 ，3），其突出到转子叶片和导向叶片行内的紧固轮廓中。沿着转子叶片排或引导叶片排或在转子的叶片/叶根（2,3）之间的至少两个相邻叶片/叶根（2,3）之间提供可塑性变形材料的密封元件（4）叶片或导向叶片和直接邻接叶片/叶片根部的旋转流动机器部件。

29. 发明授权

US07052233B2 Base material with cooling air hole 失效
标题翻译：基材具有冷却空气孔
公开(公告)号：US07052233B2
公开(公告)日：2006-05-30
申请号：US10899031
申请日：2004-07-27
申请人： Reinhard Fried , Ulrich Rathmann
发明人： Reinhard Fried , Ulrich Rathmann
IPC分类号： F04D29/70
CPC分类号： F01D5/18 , B23P2700/06 , F01D5/186 , F01D25/12 , F05D2260/201 , F05D2260/202 , F05D2260/607
摘要： A base material (2) with a cooling air hole (1) is disclosed, means being present which prevent particles (5), which are located in the cooling air (4) which flows through the cooling air hole (1) during the operation of the cooling air hole (1), from closing the cooling air hole (1). In this arrangement, the means can consist in the edge of the cooling air hole (1) being uneven or having a ridge (3) or the cooling air hole (1) being star-shaped, ellipsoidal or linear or the cooling air hole (1) being circular and having lateral slots (7).
摘要翻译：公开了一种具有冷却空气孔（1）的基材（2），用于防止在操作期间流过冷却空气孔（1）的冷却空气（4）中的颗粒（5）的装置的冷却空气孔（1）的关闭。在这种布置中，装置可以包括不均匀或具有脊（3）的冷却空气孔（1）的边缘或冷却空气孔（1）是星形，椭圆形或直线的或冷却空气孔（ 1）为圆形并具有侧向槽（7）。

30. 发明授权

US06739594B2 Sealing arrangement between components of a rotating assembly as well as a method for producing a sealing joint 有权
标题翻译：旋转组件的部件之间的密封布置以及密封接头的制造方法
公开(公告)号：US06739594B2
公开(公告)日：2004-05-25
申请号：US09988313
申请日：2001-11-19
申请人： Alexander Beeck , Ulrich Rathmann
发明人： Alexander Beeck , Ulrich Rathmann
IPC分类号： F16J1500
CPC分类号： F16J15/164 , F01D5/08 , F01D9/06 , F01D11/005 , F05D2260/2322 , F05D2300/505 , F16J15/0887 , F16J15/104
摘要： A sealing arrangement between two radially adjoining components of an assembly that rotates during operation, in particular between the rotor and the rotating blade of a gas turbine component includes a sealing element in a depression of an inner one of the two components at the boundary surface to the outer one of the two components. The sealing element is designed in such a way that it does not or does only slightly project beyond the depression during assembly and that, during rotation of the assembly, the centrifugal force acting on it produces a sealing joint between the components. The present sealing arrangement permits an easy installation of rotating blades to the rotor of a gas turbine.
摘要翻译：在操作期间，特别是在转子和燃气轮机部件的旋转叶片之间旋转的组件的两个径向相邻的部件之间的密封装置包括密封元件，该密封元件位于边界表面的两个部件中的内部部分的凹部中，外部的两个组件之一。密封元件被设计成使得其在组装期间不会或仅仅稍微突出超过凹陷，并且在组件旋转期间，作用在其上的离心力在部件之间产生密封接头。本密封装置允许将旋转叶片容易地安装到燃气轮机的转子上。

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