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1. 发明授权

US07758309B2 Vane wheel of turbine comprising a vane and at least one cooling channel 有权
标题翻译：涡轮的叶轮包括叶片和至少一个冷却通道
公开(公告)号：US07758309B2
公开(公告)日：2010-07-20
申请号：US11632013
申请日：2005-06-13
申请人： Hans-Thomas Bolms , Andreas Heselhaus , Roland Häbel , Torsten Koch , Ralf Müsgen
发明人： Hans-Thomas Bolms , Andreas Heselhaus , Roland Häbel , Torsten Koch , Ralf Müsgen
IPC分类号： F01D5/18
CPC分类号： F01D5/30 , F01D5/081 , F01D25/12 , F05D2230/12 , F05D2240/127 , F05D2240/81 , F05D2250/291 , F05D2260/2212 , F05D2260/22141
摘要： There is described a vane wheel of a turbine comprising at least one vane, the footing thereof being held on a wheel disk. At least one cooling channel is arranged between the wheel disk and the vane footing. The vane wheel having a plurality of turbulators is embodied on at least one of the walls of the cooling channel, the turbulators being configured in such a way that the turbulence and thus the heat transfer of a cooling fluid flowing through the cooling channel are increased.
摘要翻译：描述了一种涡轮机的叶轮，包括至少一个叶片，其叶片保持在轮盘上。至少一个冷却通道设置在轮盘和叶片基脚之间。具有多个紊流器的叶轮被实施在冷却通道的壁中的至少一个壁上，所述湍流器被构造成使得流过冷却通道的冷却流体的紊流以及热传递增加。

2. 发明授权

US08267659B2 Turbine blade 失效
标题翻译：涡轮叶片
公开(公告)号：US08267659B2
公开(公告)日：2012-09-18
申请号：US12525156
申请日：2008-01-14
申请人： Fathi Ahmad , Scarlett Fajardo-Reina , Markus Gill , Stefan Werner Kiliani , Silvio-Ulrich Martin , Ralf Müsgen , Oliver Schneider
发明人： Fathi Ahmad , Scarlett Fajardo-Reina , Markus Gill , Stefan Werner Kiliani , Silvio-Ulrich Martin , Ralf Müsgen , Oliver Schneider
IPC分类号： F01D5/18
CPC分类号： F01D5/181 , F01D5/182 , F05D2230/237 , F05D2230/238 , F05D2240/241 , Y10T29/49341
摘要： A turbine blade is provided. The turbine blade includes a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure by at least one spacing element. For example the spacing element can be a solder globule in order to form a space through which a cooling medium can flow between the support structure and the shell. A method for the production of a turbine blade having a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure is also provided. The shell is soldered to the support structure in at least at one place of the support structure in order to connect the shell to and at a distance from the support structure.
摘要翻译：提供涡轮叶片。涡轮机叶片包括支撑结构和壳体，其围绕支撑结构并且通过至少一个间隔元件连接到并且与支撑结构一定距离。例如，间隔元件可以是焊球，以便形成冷却介质可以在支撑结构和壳体之间流动的空间。还提供了一种用于生产具有支撑结构和壳体的涡轮叶片的方法，所述支撑结构和壳体围绕所述支撑结构并且连接到所述支撑结构并且距离所述支撑结构一定距离。壳体至少在支撑结构的一个位置被焊接到支撑结构，以便将壳体与支撑结构连接并且与支撑结构相距一定距离。

3. 发明授权

US08021118B2 Turbine blade for a turbine with a cooling medium passage 有权
标题翻译：具有冷却介质通道的涡轮机的涡轮叶片
公开(公告)号：US08021118B2
公开(公告)日：2011-09-20
申请号：US11974895
申请日：2007-10-16
申请人： Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Eβer , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
发明人： Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Eβer , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
IPC分类号： F01D5/14
CPC分类号： F01D25/12 , F01D5/18 , F05D2230/10 , F05D2230/21 , F05D2230/232 , F05D2230/238 , F05D2240/81 , F05D2260/36
摘要： A turbine blade for a turbine of a thermal power plant, with a platform for partial delimiting of a flow passage in the turbine, wherein the platform has at least one cooling medium passage, which extends inside the platform, for guiding a cooling medium, is characterized according to the invention in that the at least one cooling medium passage emerges from the platform at at least two connecting openings, and the turbine blade has at least one supplementary component which can be fastened on the platform, with a communicating passage, which is designed for interconnecting the connecting openings in a fluid-guiding manner.
摘要翻译：一种用于火力发电厂的涡轮机的涡轮机叶片，具有用于部分限定涡轮机中的流动通道的平台，其中平台具有至少一个在平台内延伸以用于引导冷却介质的冷却介质通道，是根据本发明的特征在于，至少一个冷却介质通道在至少两个连接开口处从平台排出，并且涡轮叶片具有可以紧固在平台上的至少一个辅助部件，连通通道设计用于以流体引导方式互连连接开口。

4. 发明申请

US20110188999A1 Axial turbine for a gas turbine with limited play between blades and housing 审中-公开
标题翻译：用于燃气轮机的轴向涡轮机，叶片和壳体之间的间隙有限
公开(公告)号：US20110188999A1
公开(公告)日：2011-08-04
申请号：US13054162
申请日：2009-07-08
申请人： Stefan Braun , Christian Cornelius , Annika Emde , Andreas Heilos , Olaf Hein , Thomas Hofbauer , Christian Lerner , Silvio-Ulrich Martin , Thorsten Mattheis , Ralf Müsgen , Eckart Schumann , Rostislav Teteruk , Adam Zimmermann
发明人： Stefan Braun , Christian Cornelius , Annika Emde , Andreas Heilos , Olaf Hein , Thomas Hofbauer , Christian Lerner , Silvio-Ulrich Martin , Thorsten Mattheis , Ralf Müsgen , Eckart Schumann , Rostislav Teteruk , Adam Zimmermann
IPC分类号： F01D11/00
CPC分类号： F01D5/20 , F01D5/141 , F01D5/143
摘要： An axial turbine for a gas turbine including a rotor blade cascade is provided. The rotor blade cascade is formed from rotor blades each including, a front edge, a blade tip, and an annular space wall that surrounds the rotor blade cascade and includes an annular space inner side, enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annual space inner side. When the turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges include a radial projection and the annular space wall includes on the annular space inner side, a peripheral radial recess that interacts with the radial projections such that a minimum is established in the direction of the main through-flow of the turbine.
摘要翻译：提供了一种用于包括转子叶片级联的燃气轮机的轴向涡轮机。转子叶片级联由转子叶片形成，每个转子叶片包括前缘，叶片尖端和围绕转子叶片级联的环形空间壁，并且包括环形空间内侧，使得环形空间壁能够直接邻近叶片尖端在叶片尖端的覆盖物和年度空间内侧之间形成径向间隙。当涡轮机运行时，具有最高压力负载的叶片尖端的区域设置在前边缘的区域中，并且其前边缘区域中的转子叶片包括径向突起，并且环形空间壁包括在环形空间内侧，与径向突起相互作用的周向径向凹部，使得在涡轮机的主通流方向上建立最小值。

5. 发明申请

US20090324421A1 Turbine Blade 失效
标题翻译：涡轮叶片
公开(公告)号：US20090324421A1
公开(公告)日：2009-12-31
申请号：US12525156
申请日：2008-01-14
申请人： Fathi Ahmad , Scarlett Fajardo-Reina , Markus Gill , Stefan Werner Kiliani , Silvio-Ulrich Martin , Ralf Müsgen , Oliver Schneider
发明人： Fathi Ahmad , Scarlett Fajardo-Reina , Markus Gill , Stefan Werner Kiliani , Silvio-Ulrich Martin , Ralf Müsgen , Oliver Schneider
IPC分类号： F01D5/18 , B23P15/04
CPC分类号： F01D5/181 , F01D5/182 , F05D2230/237 , F05D2230/238 , F05D2240/241 , Y10T29/49341
摘要： A turbine blade is provided. The turbine blade includes a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure by at least one spacing element. For example the spacing element can be a solder globule in order to form a space through which a cooling medium can flow between the support structure and the shell. A method for the production of a turbine blade having a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure is also provided. The shell is soldered to the support structure in at least at one place of the support structure in order to connect the shell to and at a distance from the support structure.
摘要翻译：提供涡轮叶片。涡轮机叶片包括支撑结构和壳体，其围绕支撑结构并且通过至少一个间隔元件连接到并且与支撑结构一定距离。例如，间隔元件可以是焊球，以便形成冷却介质可以在支撑结构和壳体之间流动的空间。还提供了一种用于生产具有支撑结构和壳体的涡轮叶片的方法，所述支撑结构和壳体围绕所述支撑结构并且连接到所述支撑结构并且距离所述支撑结构一定距离。壳体至少在支撑结构的一个位置被焊接到支撑结构，以便将壳体与支撑结构连接并且与支撑结构相距一定距离。

6. 发明申请

US20090304503A1 STATOR BLADE SEGMENT OF A THERMAL TURBOMACHINE, ASSOCIATED PRODUCTION METHOD AND ALSO THERMAL TURBOMACHINE 失效
标题翻译：热涡轮机的定子叶片分段，相关的生产方法和热涡轮机
公开(公告)号：US20090304503A1
公开(公告)日：2009-12-10
申请号：US12225933
申请日：2007-02-21
申请人： Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Esser , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
发明人： Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Esser , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
IPC分类号： F01D9/04 , F01D9/02 , B23P11/00
CPC分类号： F01D9/042 , F01D25/246 , F05D2230/23 , F05D2230/238 , F05D2240/10 , F05D2240/80 , F05D2260/30 , Y10T29/49323
摘要： The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.
摘要翻译：本发明涉及一种热涡轮机的导向叶片段，特别是燃气涡轮机，其包括布置在平台上的多个异型叶片。用于将引导片段固定到相关联的引导叶片支撑件上的多个固定元件布置在平台的远离叶片的侧面上。本发明的目的是提供一种可以以简单和经济的方式制造的导向叶片段，避免了铸造问题区域，使得导向叶片段以特别可靠和可靠的方式附接到相关联的导向叶片支撑件。根据本发明，至少一个固定元件的至少一个部分是单独制造的部件，其刚性地连接到平台或固定元件的附加部分。

7. 发明授权

US08257032B2 Gas turbine with a guide vane 失效
标题翻译：燃气轮机带导叶
公开(公告)号：US08257032B2
公开(公告)日：2012-09-04
申请号：US12009314
申请日：2008-01-17
申请人： Alexander R. Beeck , Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Eβer , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
发明人： Alexander R. Beeck , Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Eβer , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
IPC分类号： F04D29/54
CPC分类号： F01D9/00 , F01D5/146 , F05D2240/301 , Y02T50/673
摘要： A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body.
摘要翻译：一种具有叶片基体的燃气轮机的导向叶片，其具有单件式设计，并且包括在叶片根部和盖板之间延伸的异型叶片叶片，以及与叶片和盖板一体形成的叶片根部与叶片一体地，以相对简单的方式旨在能够与单独的使用条件匹配，特别是在设备和物流方面的特别少的费用。为此，根据本发明，在叶片叶片的工作介质的流动方向上观察到连接在叶片叶片的上游的具有前进导向叶片的流动路线体与叶片基体接合。

8. 发明授权

US08128357B2 Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine 失效
标题翻译：热涡轮机的定子叶片段，相关的生产方法和热涡轮机
公开(公告)号：US08128357B2
公开(公告)日：2012-03-06
申请号：US12225933
申请日：2007-02-21
申请人： Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Eβer , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
发明人： Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Eβer , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
IPC分类号： F04D29/44
CPC分类号： F01D9/042 , F01D25/246 , F05D2230/23 , F05D2230/238 , F05D2240/10 , F05D2240/80 , F05D2260/30 , Y10T29/49323
摘要： The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.
摘要翻译：本发明涉及一种热涡轮机的导向叶片段，特别是燃气涡轮机，其包括布置在平台上的多个异型叶片。用于将引导片段固定到相关联的引导叶片支撑件上的多个固定元件布置在平台的远离叶片的侧面上。本发明的目的是提供一种可以以简单和经济的方式制造的导向叶片段，避免了铸造问题区域，使得导向叶片段以特别可靠和可靠的方式附接到相关联的导向叶片支撑件。根据本发明，至少一个固定元件的至少一个部分是单独制造的部件，其刚性地连接到平台或固定元件的附加部分。

9. 发明授权

US07832988B2 Turbine blade 有权
标题翻译：涡轮叶片
公开(公告)号：US07832988B2
公开(公告)日：2010-11-16
申请号：US11807387
申请日：2007-05-29
申请人： Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Eβer , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
发明人： Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Eβer , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/147 , F05D2230/232
摘要： A turbine blade with an aerodynamically profiled blade leaf which is produced from two assembled shell elements is provided. The shell elements forming the suction-side and the pressure-side blade leaf wall have been assembled by a high-temperature and high-pressure bonding process. In the region of the blade leaf tip, a cramp is provided which hooks the two blade walls together with one another with a form fit.
摘要翻译：提供了由两个组装的壳单元制成的具有空气动力学异型叶片叶片的涡轮叶片。形成吸入侧和压力侧叶片叶片的壳单元已经通过高温高压粘合工艺组装。在叶片叶尖的区域中，提供了将两个叶片壁彼此钩合在一起的抽筋。

10. 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。

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