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1. 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。

2. 发明授权

US06569492B2 Process for repairing a coated component 有权
标题翻译：修复涂层部件的方法
公开(公告)号：US06569492B2
公开(公告)日：2003-05-27
申请号：US09870502
申请日：2001-06-01
申请人： John Fernihough , Abdus S. Khan , Maxim Konter , Markus Oehl , Hans-Joachim Dorn
发明人： John Fernihough , Abdus S. Khan , Maxim Konter , Markus Oehl , Hans-Joachim Dorn
IPC分类号： B05D714
CPC分类号： F01D5/005 , C23C4/00 , C23C4/02 , C23C4/18 , C23C10/02 , F05D2230/80 , F05D2230/90 , F05D2300/121 , F05D2300/132 , F05D2300/611 , Y10T29/49318
摘要： The invention relates to a process of repairing a MCrAlY-coating of an article, which has being exposed to the hot gases of, for example, a gas turbine. The MCrAlY-coating is examined and repaired only locally where it is needed and then, subsequently, on top of the MCrAlY-coating the article is aluminized and/or chromized, avoiding the stripping of the whole coating and re-coating over the entire surface of the article. This is for replenishing the coating of Al and/or Cr that become depleted during engine operation, in an easy, cost and time saving manner.
摘要翻译：本发明涉及一种修复已经暴露于例如燃气轮机的热气体的物品的MCrAlY涂层的方法。 MCrAlY涂层仅在需要的地方进行局部检查和修复，然后再在MCrAlY涂层的顶部进行镀层和/或镀铬处理，避免了整个涂层的剥离和整个表面的再涂覆的文章。这是为了补充在发动机运行期间耗尽的Al和/或Cr的涂层，以简单，成本和时间的方式。

3. 发明授权

US06773753B2 Process for treating a coated gas turbine part, and coated gas turbine part 有权
标题翻译：用于处理涂覆的燃气轮机部件和涂覆的燃气轮机部件的方法
公开(公告)号：US06773753B2
公开(公告)日：2004-08-10
申请号：US10211352
申请日：2002-08-05
申请人： Gordon Anderson , Reinhard Fried , Michael Loetzerich , Markus Oehl , Stefan Schlechtriem , Joerg Stengele
发明人： Gordon Anderson , Reinhard Fried , Michael Loetzerich , Markus Oehl , Stefan Schlechtriem , Joerg Stengele
IPC分类号： B32B1500
CPC分类号： F01D5/288 , F01D5/145 , F01D5/286 , F05D2230/10 , F05D2230/90 , F05D2250/60 , F05D2250/62 , F05D2250/621 , F05D2260/221 , F05D2260/2214 , F05D2300/2118 , F05D2300/611 , Y10T428/12451 , Y10T428/24355 , Y10T428/24942 , Y10T428/31
摘要： The invention discloses a process for treating a ceramic protective layer (3) which is applied to the surface (2) of a gas turbine part (1). The roughness of the ceramic protective layer (3) is reduced at at least one first location (5), and the original roughness is retained at at least one second location (6). The roughness is advantageously retained at locations (6) on a turbine blade or vane (1) which are at risk of detachment, while the roughness of the remaining surface (2) is reduced in order to reduce the heat transfer to the surrounding hot-gas flow.
摘要翻译：本发明公开了一种处理燃气轮机部件（1）的表面（2）的陶瓷保护层（3）的处理方法。陶瓷保护层（3）的粗糙度在至少一个第一位置（5）处减小，并且原始粗糙度保持在至少一个第二位置（6）。有利地，粗糙度保持在涡轮叶片或叶片（1）上的位于有分离风险的位置（6）处，同时减少了剩余表面（2）的粗糙度，以便减少向周围热交换器气流。

4. 发明授权

US06589011B2 Device for cooling a shroud of a gas turbine blade 有权
标题翻译：用于冷却燃气轮机叶片的护罩的装置
公开(公告)号：US06589011B2
公开(公告)日：2003-07-08
申请号：US09996693
申请日：2001-11-30
申请人： Alexander Beeck , Reinhard Fried , Markus Oehl
发明人： Alexander Beeck , Reinhard Fried , Markus Oehl
IPC分类号： F04D3100
CPC分类号： F01D5/081 , F01D5/187 , F01D5/22 , F01D5/225 , F01D25/12 , F05D2240/81 , F05D2250/191
摘要： Described is a cooling device for a shroud of a gas turbine blade, having a cooling channel system provided in the shroud, which is provided radially to the gas turbine blade with cooling channels that are open on one side, and which is closed off with a cover plate. The invention is characterized in that, between the cover plate and the cooling channels that are open on one side, an impact cooling plate is provided in such a way that the impact cooling plate rests on the cooling channels that are open on one side, is pressed against them by force, and encloses a space with the cover plate.
摘要翻译：描述了一种用于燃气轮机叶片的护罩的冷却装置，其具有设置在护罩中的冷却通道系统，该冷却通道系统设置在燃气轮机叶片的径向上，其具有在一侧敞开的冷却通道，并且其被封闭盖盘。本发明的特征在于，在盖板和一侧开口的冷却通道之间，设置冲击冷却板，使得冲击冷却板支撑在一侧开口的冷却通道上，是用力压住它们，并用盖板封住一个空间。

5. 发明授权

US06499943B1 Friction-susceptible component of a thermal turbo machine 有权
标题翻译：热涡轮机的摩擦敏感部件
公开(公告)号：US06499943B1
公开(公告)日：2002-12-31
申请号：US09635529
申请日：2000-08-09
申请人： Alexander Beeck , Mohamed Nazmy , Markus Oehl , Christoph Tonnes
发明人： Alexander Beeck , Mohamed Nazmy , Markus Oehl , Christoph Tonnes
IPC分类号： F01D1100
CPC分类号： F01D11/008 , F01D5/28 , F01D11/12
摘要： A component such as a turbine blade (1) of a gas turbine is provided with an intermetallic felt (2). By providing the tip (11) of the turbine blade (1) with the intermetallic felt (2) and optionally a coating of a ceramic material (3), improved protection against thermal and mechanical effects and improved oxidation resistance can be achieved. Also conceivable would be an arrangement of the intermetallic felt (2) at the rotor (4, 4a) or stator (4, 4b) opposite from the turbine blade (1) or on the platform (12) of the turbine blade (1).
摘要翻译：诸如燃气轮机的涡轮叶片（1）的部件设置有金属间毡（2）。通过提供涡轮叶片（1）的尖端（11）与金属间毡（2）和任选的陶瓷材料（3）的涂层，可以实现改进的防热和机械效应的保护以及改进的耐氧化性。还可以想到的是，在与涡轮机叶片（1）相对的转子（4,4a）或定子（4,4b）处或在涡轮叶片（1）的平台（12）上的金属间毡（2）的布置，。

6. 发明授权

US06682304B2 Cooled gas turbine blade 失效
标题翻译：冷却燃气轮机叶片
公开(公告)号：US06682304B2
公开(公告)日：2004-01-27
申请号：US09996684
申请日：2001-11-30
申请人： Alexander Beeck , Reinhard Fried , Markus Oehl
发明人： Alexander Beeck , Reinhard Fried , Markus Oehl
IPC分类号： F01D508
CPC分类号： F01D5/081 , F01D5/187 , F01D5/22 , F01D5/225 , F01D25/12 , F05D2240/81 , F05D2250/191
摘要： A cooled gas turbine blade with a shroud in which a cooling channel system is provided, which is closed off radially to the gas turbine blade with a cover plate is characterized in that the cover plate has a circumferential edge, along the entire extension of which the cover plate enters into a continuous shape-mated connection or a plurality of locally limited shape-mated connections with the shroud.
摘要翻译：一种具有护罩的冷却式燃气轮机叶片，其中设有冷却通道系统，该冷却通道系统通过盖板径向封闭到燃气轮机叶片，其特征在于，所述盖板具有周向边缘，沿其整个延伸部分盖板进入与护罩的连续形状配合连接或多个局部限定的形状配合连接。

7. 发明授权

US06623790B2 Method of adjusting the size of cooling holes of a gas turbine component 有权
标题翻译：调整燃气轮机部件的冷却孔尺寸的方法
公开(公告)号：US06623790B2
公开(公告)日：2003-09-23
申请号：US09867625
申请日：2001-05-31
申请人： John Fernihough , Markus Oehl
发明人： John Fernihough , Markus Oehl
IPC分类号： C23C1608
CPC分类号： F01D5/186 , B23P2700/06 , C23C16/045 , C25D7/04 , F05D2230/11 , F05D2230/90
摘要： A method for adjusting the size of cooling holes of a gas turbine component is disclosed in which the component is shielded with an easily removable and non- conductive shielding material without shielding the cooling holes themselves. The cooling holes are then coated by a galvanic process and the size of the cooling holes is restored to within manufacturing tolerances. The shielding material is removed and, subsequently, a heat treatment for securing a bonding of the metallic coating is applied.
摘要翻译：公开了一种用于调节燃气轮机部件的冷却孔尺寸的方法，其中部件用易于拆卸和非导电的屏蔽材料屏蔽，而不会屏蔽冷却孔本身。然后通过电镀工艺涂覆冷却孔，并将冷却孔的尺寸恢复到制造公差内。去除屏蔽材料，随后进行用于确保金属涂层的粘结的热处理。

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