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11. 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。

12. 发明授权

US07963746B2 Turbine blade and gas turbine equipped with a turbine blade 失效
标题翻译：配有涡轮叶片的涡轮叶片和燃气轮机
公开(公告)号：US07963746B2
公开(公告)日：2011-06-21
申请号：US12563369
申请日：2009-09-21
申请人： Stefan Baldauf , Hans-Thomas Bolms , Michael Händler , Christian Lerner
发明人： Stefan Baldauf , Hans-Thomas Bolms , Michael Händler , Christian Lerner
IPC分类号： F01D5/18 , F01D5/22
CPC分类号： F01D5/22 , F01D11/008 , F05D2240/80
摘要： The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.
摘要翻译：本发明涉及一种涡轮叶片，其包括沿叶片轴线延伸的叶片和位于叶片根部的平台区域，该平台区域具有横向延伸到叶片轴线的平台。本发明的目的是以最简单的方式配置燃气轮机的流动通道的定界。因此，平台由靠在叶片上的弹性金属板构成。所述部分通向燃气轮机，其包括沿燃气轮机的轴线延伸的流动管道，所述导管具有用于工作介质的环形横截面和位于第一叶片台的下游的第二叶片台，沿着轴。

13. 发明申请

US20060153685A1 Layer structure and method for producing such a layer structure 失效
标题翻译：用于制造这种层结构的层结构和方法
公开(公告)号：US20060153685A1
公开(公告)日：2006-07-13
申请号：US10563948
申请日：2004-06-17
申请人： Hans-Thomas Bolms , Andreas Heselhaus
发明人： Hans-Thomas Bolms , Andreas Heselhaus
IPC分类号： B64C27/46
CPC分类号： C23C28/3215 , C23C28/042 , C23C28/322 , C23C28/345 , C23C28/3455 , C23C30/00 , F01D5/183 , F01D5/288 , Y10T428/249954 , Y10T428/249955 , Y10T428/249956 , Y10T428/249961 , Y10T428/249967 , Y10T428/24997 , Y10T428/24999
摘要： The invention relates to a temperature resistant layered structure comprising a substrate and a porous layer arranged on the substrate having a pore defined by a wall, and a ceramic coating on an interior surface of the wall. The invention also relates to a layered turbine component arrangement comprising a substrate having a cooling passage adapted to allow a cooling gas medium to pass through the substrate and a porous layer arranged on the substrate, the porous layer having cooling passages formed by gas-permeable inter-connections between pores in the porous layer.
摘要翻译：本发明涉及一种耐温分层结构，其包括基板和布置在基板上的多孔层，其具有由壁限定的孔，以及在该壁的内表面上的陶瓷涂层。本发明还涉及一种层状涡轮机部件装置，其包括具有适于允许冷却气体介质通过基板的冷却通道的基板和布置在基板上的多孔层，多孔层具有通过气体可渗透相互间形成的冷却通道 - 多孔层中的孔之间的连接。

14. 发明授权

US06682300B2 Seal element for sealing a gap and combustion turbine having a seal element 失效
标题翻译：用于密封间隙的密封元件和具有密封元件的燃气轮机
公开(公告)号：US06682300B2
公开(公告)日：2004-01-27
申请号：US10117584
申请日：2002-04-04
申请人： Hans-Thomas Bolms
发明人： Hans-Thomas Bolms
IPC分类号： F01D1108
CPC分类号： F16J15/121 , F01D11/005
摘要： The invention pertains to a seal element (1) for sealing a gas-path leakage-gap (5) between spaced apart first and second components (2,3) of a turbo machinery (22), which first and second components (2,3) having opposing inner and outer surfaces (9, 10) situated outside the leakage-gap (5). The seal element (1) comprises a generally gas impervious sealing member (4) and a layer (6) comprising ceramic fibers. The layer (6) covers at least partially said sealing element (1) and defines a sealing surface (21) for contacting outside the gap (5) the outer surfaces (10) of the first and second components (2,3) of the turbo machinery (22). The inventions further pertains to a combustion turbine (22), which comprises plurality of components (2,3) disposed in axial and circumferential direction, said components including guide-blade plates (12) of guide blades (16) and wall components (13), which are spaced apart in the circumferential direction or the axial direction by a leakage-gap (5) sealed off by a seal element (1).
摘要翻译：本发明涉及用于密封涡轮机械（22）的间隔开的第一和第二部件（2,3）之间的气体通道泄漏间隙（5）的密封元件（1），该第一和第二部件（2， 3）具有位于泄漏间隙（5）外侧的相对的内表面和外表面（9,10）。密封元件（1）包括通常不透气的密封构件（4）和包括陶瓷纤维的层（6）。所述层（6）至少部分地覆盖所述密封元件（1）并且限定用于接触所述间隙（5）外部的所述第一和第二部件（2,3）的外表面（10）的密封表面（21）涡轮机械（22）。本发明还涉及一种燃气轮机（22），其包括沿轴向和圆周方向设置的多个部件（2,3），所述部件包括导向叶片（16）的引导叶片板（12）和壁部件（13）），其通过由密封元件（1）密封的泄漏间隙（5）在圆周方向或轴向上间隔开。

15. 发明申请

US20140133956A1 PROCESS FOR COOLING THE TURBINE STAGE AND GAS TURBINE HAVING A COOLED TURBINE STAGE 审中-公开
标题翻译：用于冷却涡轮机阶段和具有冷却涡轮机级的气体涡轮机的方法
公开(公告)号：US20140133956A1
公开(公告)日：2014-05-15
申请号：US14009905
申请日：2012-03-08
申请人： Hans-Thomas Bolms , Boris Dobrzynski
发明人： Hans-Thomas Bolms , Boris Dobrzynski
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D5/186 , F01D5/187 , F02C7/18 , F05D2260/202
摘要： A gas turbine having a turbine stage is presented. The gas turbine has a guide vane that can be operated cooled by a cooling medium, and a cooling medium feed device for feeding the cooling medium into the interior of the guide van, which, in the region of its rear edge, has on the pressure side at least one cooling medium outlet opening, through which the cooling medium can flow out of the interior of the guide vane into the main flow. The cooling medium feed device has a mass flow control device for controlling the mass flow through the at least one cooling medium outlet opening, with which the mass flow through the at least one cooling medium outlet opening can be increased during operation of the gas turbine under part-load compared to operation of the gas turbine under full load.
摘要翻译：提出了一种具有涡轮级的燃气轮机。燃气轮机具有可由冷却介质冷却的导向叶片，以及用于将冷却介质供给到导向面包车内部的冷却介质供给装置，该导向件在其后缘区域具有压力侧至少一个冷却介质出口开口，冷却介质可以通过该冷却介质出口开口流出导叶内部进入主流。冷却介质进料装置具有质量流量控制装置，用于控制通过至少一个冷却介质出口的质量流量，在燃气轮机的运行期间，通过该至少一个冷却介质出口的质量流可以增加与全负荷下燃气轮机的运行相比，部分负载。

16. 发明申请

US20110176930A1 Turbine vane for a gas turbine and casting core for the production of such 审中-公开
标题翻译：用于燃气轮机的涡轮叶片和用于生产的铸铁芯
公开(公告)号：US20110176930A1
公开(公告)日：2011-07-21
申请号：US13002986
申请日：2009-05-19
申请人： Fathi Ahmad , Hans-Thomas Bolms , Christian Lerner
发明人： Fathi Ahmad , Hans-Thomas Bolms , Christian Lerner
IPC分类号： F01D5/18 , B28B7/28
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2250/712 , F05D2260/2212 , F05D2260/22141
摘要： A turbine vane or blade including an interior structure is provided. In addition, turbulence elements connected directly upstream of openings disposed at the rear edge of the blade of the turbine vane or blade are also provided. These are disposed in a sequence, each having a flow side against which a coolant flows and which is at least partially arched in a concave manner. Preferably, the turbulence elements are configured in a crescent-shaped manner. This makes it possible to enlarge the openings without resulting in an increased consumption of coolant. A casting core is also provided. The openings required in the casting core for the production of the webs of a turbine vane or blade may now be placed at further distances than before.
摘要翻译：提供了包括内部结构的涡轮叶片或叶片。此外，还提供了连接在设置在涡轮机叶片或叶片的叶片的后边缘处的开口的上游的湍流元件。这些按顺序设置，每个具有流动侧，冷却剂流过该流动侧，并且至少部分地以凹形方式拱起。优选地，湍流元件被构造成月牙形。这使得可以扩大开口而不会导致冷却剂的消耗增加。还提供铸芯。用于生产涡轮叶片或叶片的腹板的铸造芯中所需的开口现在可以放置在比以前更远的距离处。

17. 发明授权

US07500823B2 Turbine blade 有权
标题翻译：涡轮叶片
公开(公告)号：US07500823B2
公开(公告)日：2009-03-10
申请号：US11174275
申请日：2005-07-01
申请人： Hans-Thomas Bolms , Ralf Müsgen
发明人： Hans-Thomas Bolms , Ralf Müsgen
IPC分类号： F01D25/12
CPC分类号： F01D5/186 , F05D2250/314 , F05D2250/34 , F05D2260/202
摘要： A turbine blade (2), with a root section (4), with a tip section (6) and with a blade leaf (12) which is provided with a number of coolant ducts (22) through which a coolant (K) is capable of flowing, outlet ducts (34) which issue in outlet ports (24) branching off, in the leading edge region (28) of the blade leaf (12), from a coolant duct (22) running essentially in the longitudinal direction (L) of the turbine blade (2) and spaced apart from the leading edge (14), the outlet ports (24) being arranged along at least two rows oriented essentially parallel to the leading edge (14), and the outlet ducts (34) being oriented, in the region of their respective outlet port (24), obliquely with respect to the longitudinal direction (L) of the turbine blade (2), in such a way that the coolant (K) flowing out in a root-side subsection (38) of each row possesses, in the region of the outlet ports (24), a velocity component pointing toward the tip section (6) of the turbine blade (2), and the coolant (K) flowing out in a tip-side subsection (42), continguous thereto, of each row has a velocity component pointing toward the root section (4), is designed for a particularly reliable and uniform cooling of the leading edge region (28), at the same time with the requirement for coolant (K) being kept particularly low. For this purpose, according to the invention, the transitional points (40) at which the orientation of the outlet ducts (34) changes are arranged so as to be offset relative to one another in the longitudinal direction (L) in each case for two adjacent rows.
摘要翻译：一种具有根部（4）的涡轮叶片（2），具有尖端部分（6）和叶片叶片（12），叶片叶片（12）设置有多个冷却剂管道（22），冷却剂（K）能够流动的出口管道（34）从在叶片叶片（12）的前缘区域（28）中分支出来的出口端口（24）从基本上在纵向方向上运行的冷却剂管道（22）涡轮叶片（2）的间隔开并与前缘（14）间隔开，出口端口（24）沿至少两排排列成基本上平行于前缘（14）排列，出口管道（34））在其各自的出口（24）的区域中相对于涡轮机叶片（2）的纵向方向（L）倾斜，使得冷却剂（K）以根部的方式流出，每排的侧部分（38）在出口端口（24）的区域中具有指向涡轮叶片（2）的尖端部分（6）的速度分量，每排排出的尖端侧部分（42）中流出的olant（K）具有指向根部（4）的速度分量，被设计成用于特别可靠和均匀地冷却前缘区域（ 28），同时对冷却剂（K）的要求保持特别低。为此，根据本发明，出口管道34的取向发生变化的过渡点40被布置成在纵向方向（L）上相对于彼此在每种情况下彼此偏移两个相邻行。

18. 发明申请

US20090016881A1 TURBINE BLADE AND GAS TURBINE EQUIPPED WITH A TURBINE BLADE 失效
标题翻译：涡轮叶片和燃气涡轮机配有涡轮叶片
公开(公告)号：US20090016881A1
公开(公告)日：2009-01-15
申请号：US10585955
申请日：2005-01-12
申请人： Stefan Baldauf , Hans-Thomas Bolms , Michael Handler , Christian Lerner
发明人： Stefan Baldauf , Hans-Thomas Bolms , Michael Handler , Christian Lerner
IPC分类号： F01D5/18
CPC分类号： F01D11/008 , F01D5/22 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, which is located at the root of the vane and has a platform that extends transversally to the blade axis. The aim of the invention is to guarantee the improved cooling of a platform region and the transition region from a turbine blade to a platform of a turbine blade, thus ensuring the cooling of the delimitation of a flow channel in a gas turbine. To achieve this, the platform comprises a first platform wall that does not support the vane and a second platform wall that supports said vane. According to the inventive concept, at the root of the vane and over the course of the transition region from the turbine blade to the platform, said first platform wall is aerodynamically curved and the course of the second platform wall has a receding shoulder in relation to the first platform wall, as a continuation of the vane.
摘要翻译：本发明涉及一种涡轮叶片，其包括沿叶片轴线延伸的叶片和位于叶片根部的平台区域，并且具有横向延伸到叶片轴线的平台。本发明的目的是确保平台区域和从涡轮叶片到涡轮叶片的平台的过渡区域的改进的冷却，从而确保冷却燃气涡轮机中的流动通道的定界。为了实现这一点，平台包括不支撑叶片的第一平台壁和支撑叶片的第二平台壁。根据本发明的概念，在叶片的根部处，并且在从涡轮机叶片到平台的过渡区域的过程中，所述第一平台壁是空气动力学弯曲的，并且第二平台壁的过程相对于第一个平台墙，作为叶片的延续。

19. 发明授权

US07201564B2 Turbine vane system 失效
标题翻译：涡轮叶片系统
公开(公告)号：US07201564B2
公开(公告)日：2007-04-10
申请号：US10344730
申请日：2001-08-03
申请人： Hans-Thomas Bolms , Michael Strassberger , Peter Tiemann
发明人： Hans-Thomas Bolms , Michael Strassberger , Peter Tiemann
IPC分类号： F01D5/08 , F01D5/18 , F01D5/20
CPC分类号： F01D5/189 , F01D5/187
摘要： A turbine vane, especially a turbine vane of the last stages, respectively includes a lower area which is radially and externally arranged, an upper area which is radially and internally arranged, and a radial cooling air channel extending between the upper area and the lower area. Cooling air can be introduced into the channel via an inlet in the lower area, and can be at least partially discharged via an outlet in the upper area. The cooling channel includes a radial inner channel through which the cooling air flows from the lower area to the upper area, and an outer channel which is adjacent to the inner channel on the circumferential side thereof. The outer channel communicates with the inner channel and includes an outlet which is arranged in the lower area. Part of the cooling air flows back in the direction of the lower area via the outer channel and emerges via the outlet.
摘要翻译：涡轮叶片，特别是最后阶段的涡轮叶片分别包括径向和外部布置的下部区域，径向和内部布置的上部区域，以及在上部区域和下部区域之间延伸的径向冷却空气通道。冷却空气可以通过下部区域中的入口引入通道，并且可以经由上部区域中的出口至少部分地排出。冷却通道包括冷却空气从下部区域流向上部区域的径向内部通道，以及在其周向侧与内部通道相邻的外部通道。外部通道与内部通道连通并且包括布置在下部区域中的出口。部分冷却空气经由外部通道沿着下部区域的方向回流并经由出口排出。

20. 发明授权

US06641362B1 Component that can be subjected to hot gas, especially in a turbine blade 有权
标题翻译：可能经受热气体的部件，特别是在涡轮叶片中
公开(公告)号：US06641362B1
公开(公告)日：2003-11-04
申请号：US10030236
申请日：2001-12-28
申请人： Dirk Anding , Hans-Thomas Bolms , Michael Scheurlen , Michael Strassberger , Peter Tiemann
发明人： Dirk Anding , Hans-Thomas Bolms , Michael Scheurlen , Michael Strassberger , Peter Tiemann
IPC分类号： F01D508
CPC分类号： F01D5/187 , F05D2260/2212
摘要： A component can be subjected to hot gas. At least one duct is provided which can be subjected to a cooling fluid. The duct is bounded by two first walls opposite to one another. The walls include turbulators with the same direction of inclination. In order to avoid constrictions, the turbulators of the first wall have a different angle of inclination relative to a flow direction of the cooling fluid to the turbulators of the second wall.
摘要翻译：组分可以经受热气体。提供至少一个可以经受冷却流体的管道。管道由彼此相对的两个第一壁限定。墙壁包括具有相同倾斜方向的扰流器。为了避免收缩，第一壁的紊流器相对于冷却流体流向第二壁的湍流器的流动方向具有不同的倾斜角。

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