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1. 发明授权

US08414264B2 Method for producing a gas turbine component which is to be coated, with exposed holes, device for carrying out the method, and coatable turbine blade with film cooling holes 有权
标题翻译：用于制造待涂覆的燃气轮机部件，露出孔的方法，用于执行该方法的装置和具有膜冷却孔的可涂覆涡轮叶片
公开(公告)号：US08414264B2
公开(公告)日：2013-04-09
申请号：US11992526
申请日：2006-09-14
申请人： Hans-Thomas Bolms , Stefan Irmisch , Jan Münzer
发明人： Hans-Thomas Bolms , Stefan Irmisch , Jan Münzer
IPC分类号： B23K26/04
CPC分类号： F01D5/005 , B23P2700/06 , F05D2230/80 , F05D2260/80
摘要： There is described a method with which, on the basis of a three-dimensional recording of a component to be reworked, its surface configuration can be determined and stored temporarily so that, after it has been coated, it can be produced in its original surface form, or in its surface form then required, in certain regions, i.e. locally in the area of film-cooling openings. An especially precise and quick three-dimensional recording can be achieved by the use of the triangulation method. In this case, a reference pattern depicted on the component by a projector is recorded by two camera arranged at an angle. From the images from the cameras, the coordinates describing the surface three-dimensionally can then be determined by a control system using the triangulation method.
摘要翻译：描述了一种方法，其基于待加工的部件的三维记录，其表面构造可以被暂时确定和存储，使得在其被涂覆之后，可以在其原始表面形式或其表面形式，然后需要在某些区域，即局部在膜冷却开口的区域中。通过使用三角测量方法可以实现特别精确和快速的三维记录。在这种情况下，通过投影仪在组件上描绘的参考图案由以一定角度布置的两个相机记录。从摄像机的图像中，可以通过使用三角测量法的控制系统来确定三维地描述表面的坐标。

2. 发明申请

US20090220349A1 Method for Producing a Gas Turbine Component Which is to be Coated, With Exposed Holes, Device for Carrying Out the Method, and Coatable Turbine Blade with Film Cooling Holes 有权
标题翻译：用于制造待涂覆的燃气轮机部件的方法，具有暴露的孔，用于执行该方法的装置和具有膜冷却孔的涂覆涡轮机叶片
公开(公告)号：US20090220349A1
公开(公告)日：2009-09-03
申请号：US11992526
申请日：2006-09-14
申请人： Hans-Thomas Bolms , Stefan Irmisch , Jan Münzer
发明人： Hans-Thomas Bolms , Stefan Irmisch , Jan Münzer
IPC分类号： F01D5/18 , B05D3/12 , B24B49/00
CPC分类号： F01D5/005 , B23P2700/06 , F05D2230/80 , F05D2260/80
摘要： There is described a method with which, on the basis of a three-dimensional recording of a component to be reworked, its surface configuration can be determined and stored temporarily so that, after it has been coated, it can be produced in its original surface form, or in its surface form then required, in certain regions, i.e. locally in the area of film-cooling openings. An especially precise and quick three-dimensional recording can be achieved by the use of the triangulation method. In this case, a reference pattern depicted on the component by a projector is recorded by two camera arranged at an angle. From the images from the cameras, the coordinates describing the surface three-dimensionally can then be determined by a control system using the triangulation method.
摘要翻译：描述了一种方法，其基于待加工的部件的三维记录，其表面构造可以被暂时确定和存储，使得在其被涂覆之后，可以在其原始表面形式或其表面形式，然后需要在某些区域，即局部在膜冷却开口的区域中。通过使用三角测量方法可以实现特别精确和快速的三维记录。在这种情况下，通过投影仪在组件上描绘的参考图案由以一定角度布置的两个相机记录。从摄像机的图像中，可以通过使用三角测量法的控制系统来确定三维地描述表面的坐标。

3. 发明授权

US08206093B2 Gas turbine with a gap blocking device 失效
标题翻译：燃气轮机带间隙阻塞装置
公开(公告)号：US08206093B2
公开(公告)日：2012-06-26
申请号：US11920674
申请日：2006-03-21
申请人： Stefan Irmisch
发明人： Stefan Irmisch
IPC分类号： F01D25/24
CPC分类号： F01D9/023 , F01D11/005 , F02C7/28 , F05D2240/55 , F05D2250/41 , F16J15/46
摘要： There is described a gas turbine with a channel wall that limits a flow, said channel wall comprising first and second wall sections, one of the wall sections being part of a combustion chamber of the gas turbine and the other wall section being part of an annular hot gas channel of a turbine unit, and the two adjacent wall sections facing each other with a gap there between. In order to reduce the leakage quantities of blocking gas that protect the gap from the entry of hot gas, it is proposed that blocking element projects from the side of the first wall section into the gap and can be displaced transversely thereto, said blocking element comprising a piston face disposed in the first wall section and a sealing structure lying opposite the piston face, it being possible to press said sealing means against an end sealing section of the second wall section by means of a pressure medium that acts on the piston face.
摘要翻译：描述了具有限制流动的通道壁的燃气涡轮机，所述通道壁包括第一和第二壁部分，壁部分中的一个是燃气涡轮机的燃烧室的一部分，另一个壁部分是环形部分的一部分涡轮单元的热气体通道，以及彼此面对的两个相邻壁部分之间的间隙。为了减少保护间隙免受热气进入的阻塞气体的泄漏量，提出了阻挡元件从第一壁部分的侧面突出到间隙中并可以横向移位，所述阻挡元件包括设置在第一壁部分中的活塞面和与活塞面相对的密封结构，可以通过作用在活塞面上的压力介质将所述密封装置压靠第二壁部分的端部密封部分。

4. 发明申请

US20090166988A1 Gas turbine with a gap blocking device 失效
标题翻译：燃气轮机带间隙阻塞装置
公开(公告)号：US20090166988A1
公开(公告)日：2009-07-02
申请号：US11920674
申请日：2006-03-21
申请人： Stefan Irmisch
发明人： Stefan Irmisch
IPC分类号： F02C7/28 , F16J15/06
CPC分类号： F01D9/023 , F01D11/005 , F02C7/28 , F05D2240/55 , F05D2250/41 , F16J15/46
摘要： There is described a gas turbine with a channel wall that limits a flow, said channel wall comprising first and second wall sections, one of the wall sections being part of a combustion chamber of the gas turbine and the other wall section being part of an annular hot gas channel of a turbine unit, and the two adjacent wall sections facing each other with a gap there between. In order to reduce the leakage quantities of blocking gas that protect the gap from the entry of hot gas, it is proposed that blocking element projects from the side of the first wall section into the gap and can be displaced transversely thereto, said blocking element comprising a piston face disposed in the first wall section and a sealing structure lying opposite the piston face, it being possible to press said sealing means against an end sealing section of the second wall section by means of a pressure medium that acts on the piston face.
摘要翻译：描述了具有限制流动的通道壁的燃气涡轮机，所述通道壁包括第一和第二壁部分，壁部分中的一个是燃气涡轮机的燃烧室的一部分，另一个壁部分是环形部分的一部分涡轮单元的热气体通道，以及彼此面对的两个相邻壁部分之间的间隙。为了减少保护间隙免受热气进入的阻塞气体的泄漏量，提出了阻挡元件从第一壁部分的侧面突出到间隙中并可以横向移位，所述阻挡元件包括设置在第一壁部分中的活塞面和与活塞面相对的密封结构，可以通过作用在活塞面上的压力介质将所述密封装置压靠第二壁部分的端部密封部分。

5. 发明授权

US09255488B2 Sealing arrangement for a thermal machine 有权
标题翻译：热机的密封布置
公开(公告)号：US09255488B2
公开(公告)日：2016-02-09
申请号：US13355685
申请日：2012-01-23
申请人： Jaroslaw Leszek Szwedowicz , Stefan Irmisch , Alexey Mozharov
发明人： Jaroslaw Leszek Szwedowicz , Stefan Irmisch , Alexey Mozharov
IPC分类号： F01D11/00 , F16J15/08
CPC分类号： F01D11/006 , F05D2240/57 , F05D2300/505 , F16J15/0887
摘要： A sealing arrangement for sealing a gap (22) between two adjacent, thermally loaded components (14, 14′) of a thermal machine, especially a turbomachine or gas turbine, includes a seal (25) which is supported in a recess (23) which extends transversely to the gap (22) and traverses said gap (22). An efficient and simple improvement of the sealing arrangement is made by the seal (25) being formed at least partially of a shape memory alloy in such a way that, when a pre-specified temperature limit is exceeded, the seal changes its sealing behavior.
摘要翻译：用于密封热机器，特别是涡轮机或燃气涡轮机的两个相邻的热负荷部件（14,14'）之间的间隙（22）的密封装置包括一个密封件（25），该密封件支撑在凹部（23）中，其横向于所述间隙（22）延伸并且横过所述间隙（22）。密封装置的有效和简单的改进是通过密封件（25）至少部分地由形状记忆合金形成的，使得当超过预定温度极限时，密封件改变其密封性能。

6. 发明授权

US09022726B2 Thermally loaded, cooled component 有权
标题翻译：热负荷，冷却组件
公开(公告)号：US09022726B2
公开(公告)日：2015-05-05
申请号：US13167819
申请日：2011-06-24
申请人： Jaroslaw Leszek Szwedowicz , Stefan Irmisch
发明人： Jaroslaw Leszek Szwedowicz , Stefan Irmisch
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/221 , F05D2260/963 , Y02T50/676
摘要： A thermally loaded, cooled component thermally coupled to a cooling system configured to receive a gaseous cooling introduced in a forced manner from outside that flows through the cooling system so as to absorb and transport heat away from the component as a result of thermal contact with the component. The component includes at least one Helmholtz resonator configured to improve thermal contact between the cooling medium and the component.
摘要翻译：热联接到冷却系统的热负荷冷却部件，该冷却系统被配置为接收以强制方式从外部引入的气态冷却物，所述冷却系统从流过冷却系统的外部吸收并传输热量，从而与热量接触零件。该部件包括至少一个亥姆霍兹共振器，其构造成改善冷却介质和部件之间的热接触。

7. 发明授权

US07584669B2 Method for recording microstructural changes in a component 失效
标题翻译：用于记录组件中的微结构变化的方法
公开(公告)号：US07584669B2
公开(公告)日：2009-09-08
申请号：US10589791
申请日：2005-02-14
申请人： Michael Dankert , Martin Feldhege , Stefan Irmisch , Matthias Oechsner , Eckart Schumann , Werner Stamm
发明人： Michael Dankert , Martin Feldhege , Stefan Irmisch , Matthias Oechsner , Eckart Schumann , Werner Stamm
IPC分类号： G01N3/00
CPC分类号： F01D21/003 , F05D2260/80 , G01N25/18 , G01N27/20 , G01N27/24 , Y02T50/67
摘要： Method for recording microstructural changes in a layer system component. A specific material parameter of the component is measured. The layer system may include an alloy substrate and an alloy or porous ceramic layer. The material parameter may be measured a plurality of times. The measured material parameter may include electrical capacitance, specific heat capacity, peltier coefficient or magnetic susceptibility. The material parameter may first be measured on a new component and subsequent measurements may be performed at a time interval after operational use. The recorded material parameter is then used to determine microstructural changes in the substrate or the layer material of the component caused by changes in precipitation, cracks, or depletion of an alloying element.
摘要翻译：在层系统组件中记录微结构变化的方法。测量组件的具体材料参数。层系统可以包括合金基底和合金或多孔陶瓷层。可以多次测量材料参数。测量的材料参数可以包括电容，比热容，珀耳替系数或磁化率。材料参数可以首先在新组件上测量，并且可以在操作使用之后的时间间隔执行后续测量。然后记录的材料参数用于确定由沉淀，裂纹或合金元素的消耗的变化引起的基板或部件的层材料中的微结构变化。

8. 发明申请

US20110318191A1 THERMALLY LOADED, COOLED COMPONENT 有权
标题翻译：热装，冷却组件
公开(公告)号：US20110318191A1
公开(公告)日：2011-12-29
申请号：US13167819
申请日：2011-06-24
申请人： Jaroslaw Leszek Szwedowicz , Stefan Irmisch
发明人： Jaroslaw Leszek Szwedowicz , Stefan Irmisch
IPC分类号： F01D5/18 , F28D15/00
CPC分类号： F01D5/187 , F05D2260/221 , F05D2260/963 , Y02T50/676
摘要： A thermally loaded, cooled component thermally coupled to a cooling system configured to receive a gaseous cooling introduced in a forced manner from outside that flows through the cooling system so as to absorb and transport heat away from the component as a result of thermal contact with the component. The component includes at least one Helmholtz resonator configured to improve thermal contact between the cooling medium and the component.
摘要翻译：热联接到冷却系统的热负荷冷却部件，该冷却系统被配置为接收以强制方式从外部引入的气态冷却物，所述冷却系统从流过冷却系统的外部吸收并传输热量，从而与热量接触零件。该部件包括至少一个亥姆霍兹共振器，其构造成改善冷却介质和部件之间的热接触。

9. 发明授权

US07967568B2 Gas turbine component with reduced cooling air requirement 有权
标题翻译：燃气轮机组件，减少冷却空气需求
公开(公告)号：US07967568B2
公开(公告)日：2011-06-28
申请号：US11858998
申请日：2007-09-21
申请人： John P. Dalton , Tilmann Auf Dem Kampe , Frank A. Maichle , Rex A. Smith , Stuart P. Bishop , Stefan Irmisch
发明人： John P. Dalton , Tilmann Auf Dem Kampe , Frank A. Maichle , Rex A. Smith , Stuart P. Bishop , Stefan Irmisch
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D9/041 , F01D9/065 , F05D2250/241 , F05D2260/2212 , F05D2260/2214 , F05D2300/21 , F05D2300/60
摘要： Introducing a plurality of geometrically shaped members (27) into a cooling passage (16) of a gas turbine airfoil (10) will effectively reduce the cross-sectional flow area while simultaneously retaining a sufficiently thick external contour desired for proper gas path aerodynamic behavior. Small cooling sub-passages (18a, 18b) formed around the geometric members will create a preferentially higher coolant flow rate and heat transfer coefficient at the cooled surface (14) when compared to the interior of the cavity. The geometric shapes may be metal or ceramic spheres retained in the cooling cavity by a retaining structure such as a screen grid (30) or perforated plate (32). The openings (34) in the retaining structure may be unevenly distributed to preferentially allow more coolant to enter the cavity proximate the cooled walls. The size/shape of the geometrically shaped members may be varied to achieve a desired heat transfer coefficient along the cooled wall surface (17).
摘要翻译：将多个几何形状的构件（27）引入到燃气涡轮机翼型件（10）的冷却通道（16）中将有效地减小横截面流动面积，同时保持足够厚的外部轮廓，用于适当的气体路径空气动力学行为。形成在几何构件周围的小的冷却子通道（18a，18b）将在与空腔内部相比时在冷却表面（14）处产生优先更高的冷却剂流率和传热系数。几何形状可以是通过诸如筛网（30）或多孔板（32）的保持结构保持在冷却腔中的金属或陶瓷球。保持结构中的开口（34）可以不均匀地分布，以优先地允许更多的冷却剂进入靠近冷却壁的空腔。可以改变几何形状构件的尺寸/形状以实现沿着冷却的壁表面（17）的期望的热传递系数。

10. 发明授权

US07300253B2 Gas turbine blade or vane and platform element for a gas turbine blade or vane ring of a gas turbine, supporting structure for securing gas turbine blades or vanes arranged in a ring, gas turbine blade or vane ring and the use of a gas turbine blade or vane ring 失效
标题翻译：用于燃气轮机的燃气轮机叶片或叶片环的燃气涡轮叶片或叶片和平台元件，用于固定设置在环中的燃气轮机叶片或叶片的支撑结构，燃气涡轮叶片或叶片环以及燃气轮机叶片的使用或叶环
公开(公告)号：US07300253B2
公开(公告)日：2007-11-27
申请号：US11214303
申请日：2005-08-29
申请人： Alexander Ralph Beeck , Stefan Irmisch
发明人： Alexander Ralph Beeck , Stefan Irmisch
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F01D11/008 , F05D2240/80 , F05D2250/71 , F05D2250/711 , F05D2250/712
摘要： The invention relates to a gas turbine blade or vane ring having a supporting structure and gas turbine blades or vanes secured to it. The gas turbine blades or vanes have a blade or vane root, which is successively adjoined by a platform and then a blade profile which is curved in the longitudinal direction, the blade or vane root running in the longitudinal direction of the blade profile, and the platform having two platform longitudinal edges which are bent parallel and run in the longitudinal direction. To provide an alternative gas turbine blade or vane ring with simplified assembly, it is proposed that the blade or vane root be shaped in such a manner that the suction-side or pressure-side blade or vane root surface of the associated platform longitudinal edge be curved convexly or concavely, respectively. Moreover, the invention relates to the use of a gas turbine blade or vane ring of this type.
摘要翻译：本发明涉及一种具有支撑结构和固定在其上的燃气涡轮机叶片或叶片的燃气轮机叶片或叶片环。燃气轮机叶片或叶片具有叶片或叶片根部，其连续地邻接在平台上，然后是沿着纵向方向弯曲的叶片轮廓，叶片或叶片根部沿叶片轮廓的纵向方向延伸，并且平台具有两个平行的纵向边缘，其平行弯曲并在纵向方向上延伸。为了提供具有简化的组装的替代燃气轮机叶片或叶片环，建议叶片或叶片根部成形为使得相关联的平台纵向边缘的吸力侧或压力侧叶片或叶片根表面为分别弯曲或凹入。此外，本发明涉及这种类型的燃气轮机叶片或叶片环的使用。

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