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1. 发明授权

US09238976B2 Guide vane system for a turbomachine having segmented guide vane carriers 有权
标题翻译：具有分段导叶载体的涡轮机的导叶系统
公开(公告)号：US09238976B2
公开(公告)日：2016-01-19
申请号：US13145353
申请日：2010-01-05
申请人： Fathi Ahmad , Giuseppe Gaio , Holger Grote , Christian Lerner , Mirko Milazar , Mathias Stutt , Thomas-Dieter Tenrahm , Bernd Vonnemann
发明人： Fathi Ahmad , Giuseppe Gaio , Holger Grote , Christian Lerner , Mirko Milazar , Mathias Stutt , Thomas-Dieter Tenrahm , Bernd Vonnemann
IPC分类号： F01D9/04 , F01D25/24
CPC分类号： F01D25/246 , F01D9/023 , F05D2230/80
摘要： A turbine guide vane system, in particular for a gas turbine is provided. The turbine guide vane system includes a number of guide vane rows and a guide vane carrier, to enable particularly simple replacement of guide vanes, while maintaining a particularly high degree of efficiency, and thus designed for particularly short repair durations. For this purpose, the guide vane carrier has a number of segments, wherein a segment extends over the entire radial extension of the guide vane carrier and the connection of the remaining segments may be detached, and wherein the turbine guide vane carrier includes at least two sections along the axial extension thereof that are connected to one another and have a different number of segments.
摘要翻译：提供了一种特别用于燃气轮机的涡轮导叶系统。涡轮引导叶片系统包括多个导向叶片行和导向叶片载体，以便能够特别简单地更换导向叶片，同时保持特别高的效率，并因此设计为特别短的修理持续时间。为此目的，导向叶片承载件具有多个段，其中，一个段在导向叶片承载件的整个径向延伸部分上延伸，并且其余段的连接可以被拆卸，并且其中该涡轮导向叶片承载件包括至少两个其轴向延伸部分彼此连接并且具有不同数量的段。

2. 发明授权

US08865255B2 Method for assessing the coolant consumption within actively cooled components 有权
标题翻译：用于评估主动冷却部件内冷却液消耗量的方法
公开(公告)号：US08865255B2
公开(公告)日：2014-10-21
申请号：US13576405
申请日：2011-02-23
申请人： Fathi Ahmad , Knut Halberstadt , Christian Lerner
发明人： Fathi Ahmad , Knut Halberstadt , Christian Lerner
IPC分类号： C23C16/00 , B05D7/22 , C23C10/00 , C23C10/18 , C23C10/06 , C23C10/48
CPC分类号： C23C10/00 , C23C10/06 , C23C10/18 , C23C10/48 , Y02T50/67 , Y10T428/13
摘要： A process for setting the average flow rate within a hollow component is provided. The process includes setting a relatively small wall thickness in a first region with a relatively large flow cross section using a first diffusion coating process and setting a relatively large wall thickness by a second different diffusion process in a second region with a relatively small flow cross section. The use of different diffusion coatings in a component allows the flow of coolant through a component to be set in a controlled manner.
摘要翻译：提供了一种用于设定中空部件内的平均流量的方法。该方法包括使用第一扩散涂覆工艺在具有相对大的流动横截面的第一区域中设置相对小的壁厚，并且在具有相对小的流动横截面的第二区域中通过第二不同扩散过程设定相对较大的壁厚。在组件中使用不同的扩散涂层允许通过部件的冷却剂流以受控的方式设定。

3. 发明申请

US20120070310A1 AXIAL TURBOMACHINE ROTOR HAVING BLADE COOLING 审中-公开
标题翻译：具有叶片冷却的轴向涡轮转子
公开(公告)号：US20120070310A1
公开(公告)日：2012-03-22
申请号：US13258624
申请日：2010-03-25
申请人： Fathi Ahmad
发明人： Fathi Ahmad
IPC分类号： F01D5/18
CPC分类号： F01D5/087 , F01D25/12 , F05D2260/201
摘要： An axial turbomachine rotor is provided. The rotor includes a rotor disk and a rotor blade ring, which includes a plurality of rotor blades, each of which include a blade root, with which the rotor blade is fixed radially outward on the rotor disk, wherein the blade root is engaged with the rotor disk at the outer edge of the rotor disk in a form-closed manner in such a way that during operation of the rotor, a gap is formed between the rotor blade and the rotor disk at a predetermined surface area of the rotor disk, in which area, a plurality of impingement cooling openings is arranged, through which a cooling medium may flow from the interior of the rotor disk into the gap whereby the rotor blade is cooled using the cooling medium by means of impingement cooling.
摘要翻译：提供轴向涡轮机转子。转子包括转子盘和转子叶片环，其包括多个转子叶片，每个转子叶片包括叶片根部，转子叶片通过该叶片根部径向向外固定在转子盘上，其中叶片根部与叶片根部转子盘在转子盘的外边缘处以形式关闭的方式，使得在转子的操作期间，在转子叶片的预定表面区域处在转子叶片和转子盘之间形成间隙，设置多个冲击冷却开口，冷却介质可从转子盘的内部流动到间隙中，由此通过冲击冷却使用冷却介质冷却转子叶片。

4. 发明申请

US20120039716A1 Guide vane system for a turbomachine having segmented guide vane carriers 有权
标题翻译：具有分段导叶载体的涡轮机的导叶系统
公开(公告)号：US20120039716A1
公开(公告)日：2012-02-16
申请号：US13145353
申请日：2010-01-05
申请人： Fathi Ahmad , Giuseppe Gaio , Holger Grote , Christian Lerner , Mirko Milazar , Matthias Stutt , Thomas-Dieter Tenrahm , Bernd Vonnemann
发明人： Fathi Ahmad , Giuseppe Gaio , Holger Grote , Christian Lerner , Mirko Milazar , Matthias Stutt , Thomas-Dieter Tenrahm , Bernd Vonnemann
IPC分类号： F01D5/02
CPC分类号： F01D25/246 , F01D9/023 , F05D2230/80
摘要： A turbine guide vane system, in particular for a gas turbine is provided. The turbine guide vane system includes a number of guide vane rows and a guide vane carrier, to enable particularly simple replacement of guide vanes, while maintaining a particularly high degree of efficiency, and thus designed for particularly short repair durations. For this purpose, the guide vane carrier has a number of segments, wherein a segment extends over the entire radial extension of the guide vane carrier and the connection of the remaining segments may be detached, and wherein the turbine guide vane carrier includes at least two sections along the axial extension thereof that are connected to one another and have a different number of segments.
摘要翻译：提供了一种特别用于燃气轮机的涡轮引导叶片系统。涡轮引导叶片系统包括多个导向叶片行和导向叶片载体，以便能够特别简单地更换导向叶片，同时保持特别高的效率，并因此设计为特别短的修理持续时间。为此目的，导向叶片承载件具有多个段，其中，一个段在导向叶片承载件的整个径向延伸部分上延伸，并且其余段的连接可以被拆卸，并且其中该涡轮导向叶片承载件包括至少两个其轴向延伸部分彼此连接并且具有不同数量的段。

5. 发明申请

US20100129554A1 METHOD FOR THE PRODUCTION OF COATED TURBINE MOVING BLADES AND MOVING-BLADE RING FOR A ROTOR OF AN AXIAL-THROUGHFLOW TURBINE 有权
标题翻译：用于制造轴流式涡轮机转子的涂层涡轮叶片和移动叶片的方法
公开(公告)号：US20100129554A1
公开(公告)日：2010-05-27
申请号：US12596780
申请日：2008-04-10
申请人： Fathi Ahmad
发明人： Fathi Ahmad
IPC分类号： B05D3/12
CPC分类号： F01D5/288 , F01D5/16 , F01D5/187 , F05D2230/10 , F05D2230/80 , F05D2250/19 , Y10T29/49318 , Y10T29/49336 , Y10T29/49337 , Y10T29/49339 , Y10T29/49726
摘要： A method for producing a coated turbine blade, with which the frequency property thereof can be particularly easily adjusted to the required boundary conditions is provided. Recesses are introduced into a blade tip of the blade leaf of the turbine blade after coating of turbine blade. In one aspect a plurality of bores are made which are distributed along the blade leaf center line.
摘要翻译：提供一种用于制造涂覆的涡轮叶片的方法，其特征在于能够将其频率特性容易地调整到所需的边界条件。在涡轮叶片涂覆之后，将凹陷物引入涡轮机叶片叶片的叶片尖端。在一个方面，制成沿叶片叶中心线分布的多个孔。

6. 发明申请

US20090229101A1 Method of Repairing a Component, and a Component 审中-公开
标题翻译：修复组件和组件的方法
公开(公告)号：US20090229101A1
公开(公告)日：2009-09-17
申请号：US12227447
申请日：2007-02-15
申请人： Fathi Ahmad , Michael Dankert
发明人： Fathi Ahmad , Michael Dankert
IPC分类号： B22D19/10
CPC分类号： B23K1/0018 , B23K2101/001 , B23P6/005 , B23P6/045 , F01D5/005 , F05D2230/237 , F05D2230/238 , F05D2230/80 , Y02T50/67 , Y10T29/49746
摘要： A method for the crack repair of a component having a crack on a surface, including excavating a hollow around the crack, wherein the hollow has two recesses and the recesses are arranged at the height of the surface and are open at the height of the surface, and wherein the recesses are arranged around the circumference of the hollow and further including filling the hollow with a braze. A component having a crack on a surface is also provided with a hollow which is excavated around the crack, the hollow has two recesses and the recesses are arranged at the height of the surface and are open at the height of the surface, and the recesses are arranged around the circumference of the hollow, wherein the hollow is filled with the braze.
摘要翻译：一种用于在表面上具有裂缝的部件的裂纹修复的方法，包括在所述裂纹周围挖出一个中空部，其中所述中空部具有两个凹部，并且所述凹部布置在所述表面的高度处并且在所述表面的高度处开放并且其中所述凹部围绕所述中空部的圆周布置，并且还包括用钎焊填充所述中空部。在表面具有裂缝的部件还设置有围绕裂缝挖掘的中空部，中空部具有两个凹部，凹部布置在表面的高度处并且在表面的高度处开口，并且凹部围绕中空的圆周布置，其中中空部填充有钎焊。

7. 发明申请

US20090074572A1 COOLED GAS TURBINE GUIDE BLADE FOR A GAS TURBINE, USE OF A GAS TURBINE GUIDE BLADE AND METHOD FOR OPERATING A GAS TURBINE 审中-公开
标题翻译：用于气体涡轮的冷却气体涡轮机导叶，气体涡轮导向叶片的使用以及操作气体涡轮的方法
公开(公告)号：US20090074572A1
公开(公告)日：2009-03-19
申请号：US12269989
申请日：2008-11-13
申请人： FATHI AHMAD
发明人： FATHI AHMAD
IPC分类号： F01D19/02 , F01D21/12
CPC分类号： F01D25/10 , F01D5/18 , F01D9/041 , F05D2220/3212 , F05D2260/85 , F05D2270/114
摘要： Described is a cooled gas turbine guide blade for a gas turbine, with a hollow blade profile which comprises an onflow edge onto which a working medium is capable of flowing, and with, for guiding a cooling medium, an onflow edge duct running inside the blade profile along the onflow edge. Furthermore, to the use of such a gas turbine guide blade and to a method for operating a gas turbine with an abovementioned gas turbine guide blade. In order to provide a gas turbine guide blade with an increased lifetime by means of the invention, it is proposed that, in the onflow edge duct, an electrical heating element be provided, which extends approximately completely over the entire length of the onflow edge duct and through which a heating current flows, before the operation of the gas turbine, for the preheating of the gas turbine guide blade.
摘要翻译：描述了一种用于燃气轮机的冷却式燃气涡轮引导叶片，其具有中空叶片轮廓，该中空叶片轮廓包括流入工作介质能够流动的向上流动边缘，以及用于引导冷却介质，在叶片内运行的流出边缘管道沿着边缘的轮廓。此外，关于这种燃气轮机引导叶片的使用以及用于利用上述燃气轮机引导叶片操作燃气轮机的方法。为了通过本发明提供具有增加的寿命的燃气轮机引导叶片，提出在流出边缘管道中设置电加热元件，该电加热元件大致完全延伸在流出边缘管道的整个长度上并且在燃气轮机的运行之前加热电流通过其流动，用于燃气涡轮引导叶片的预热。

8. 发明授权

US07465150B2 Cooled gas turbine guide blade for a gas turbine, use of a gas turbine guide blade and method for operating a gas turbine 失效
标题翻译：用于燃气轮机的冷却燃气涡轮引导叶片，燃气轮机引导叶片的使用和用于操作燃气轮机的方法
公开(公告)号：US07465150B2
公开(公告)日：2008-12-16
申请号：US11479183
申请日：2006-06-30
申请人： Fathi Ahmad
发明人： Fathi Ahmad
IPC分类号： F01D9/06 , F01D25/10 , F01D25/12
CPC分类号： F01D25/10 , F01D5/18 , F01D9/041 , F05D2220/3212 , F05D2260/85 , F05D2270/114
摘要： Described is a cooled gas turbine guide blade for a gas turbine, with a hollow blade profile which comprises an onflow edge onto which a working medium is capable of flowing, and with, for guiding a cooling medium, an onflow edge duct running inside the blade profile along the onflow edge. Furthemore, to the use of such a gas turbine guide blade and to a method for operating a gas turbine with an abovementioned gas turbine guide blade. In order to provide a gas turbine guide blade with an increased lifetime by means of the invention, it is proposed that, in the onflow edge duct, an electrical heating element be provided, which extends approximately completely over the entire length of the onflow edge duct and through which a heating current flows, before the operation of the gas turbine, for the preheating of the gas turbine guide blade.
摘要翻译：描述了一种用于燃气轮机的冷却式燃气涡轮引导叶片，其具有中空叶片轮廓，该中空叶片轮廓包括流入工作介质能够流动的向上流动边缘，以及用于引导冷却介质，在叶片内运行的流出边缘管道沿着边缘的轮廓。对于使用这样的燃气轮机引导叶片以及使用上述燃气轮机引导叶片来操作燃气轮机的方法更是如此。为了通过本发明提供具有增加的寿命的燃气轮机引导叶片，提出在流出边缘管道中设置电加热元件，该电加热元件大致完全延伸在流出边缘管道的整个长度上并且在燃气轮机的运行之前加热电流通过其流动，用于燃气涡轮引导叶片的预热。

9. 发明授权

US09862002B2 Process for producing a layer system 有权
公开(公告)号：US09862002B2
公开(公告)日：2018-01-09
申请号：US14354573
申请日：2012-09-14
申请人： Fathi Ahmad , Christian Amann , Björn Beckmann , Björn Buchholz , Giuseppe Gaio , Thomas Hille , Eckart Schumann , Rostislav Teteruk
发明人： Fathi Ahmad , Christian Amann , Björn Beckmann , Björn Buchholz , Giuseppe Gaio , Thomas Hille , Eckart Schumann , Rostislav Teteruk
IPC分类号： B05D3/00 , C23C30/00 , F01D5/28 , F23R3/00
CPC分类号： B05D3/007 , C23C30/00 , F01D5/28 , F01D5/288 , F05D2250/294 , F23M2900/05003 , F23M2900/05004 , F23R3/007 , F23R2900/00018
摘要： A process for producing a layer system is provided wherein the layer system has at least a substrate, a ceramic layer, which is applied to a surface structured in a targeted manner, in which process the intermediate layer, in particular the metallic layer, is applied in such a way that the recesses form during the coating. By introducing recesses into a surface, the stresses in the ceramic layer on the metallic substrate are reduced in such a manner that a longer lifespan for the ceramic layer is achieved.

10. 发明申请

US20140248157A1 BLADE OR VANE OF DIFFERING ROUGHNESS AND PRODUCTION PROCESS 审中-公开
标题翻译：不同粗糙度和生产过程的叶片或叶片
公开(公告)号：US20140248157A1
公开(公告)日：2014-09-04
申请号：US14061870
申请日：2013-10-24
申请人： Fathi Ahmad
发明人： Fathi Ahmad
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F04D29/023 , F04D29/284 , F04D29/30 , F04D29/324 , F04D29/681 , F05B2250/60 , F05B2250/61 , F05B2250/611 , F05B2250/62 , F05B2250/621 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2240/31 , F05D2250/60 , F05D2250/61 , F05D2250/611 , F05D2250/62 , F05D2250/621 , F05D2300/516 , F05D2300/611 , Y02T50/673 , Y10T29/49336
摘要： A blade or vane of different roughness and a process for producing such a blade or vane are presented. The performance of the blade or vane of a compressor or of a turbine can be improved because of the different configuration of the roughness of the surfaces on the suction side and the pressure side of the blade or vane.
摘要翻译：提供了不同粗糙度的叶片或叶片以及用于生产这种叶片或叶片的方法。压缩机或涡轮机的叶片或叶片的性能可以被改善，因为在叶片或叶片的吸入侧和压力侧上的表面的粗糙度的不同构造。

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