公开(公告)号：US06439846B1

公开(公告)日：2002-08-27

申请号：US09446949

申请日：2000-04-10

申请人： Gordon Anderson ,  Jorgen Ferber ,  Rainer Hocker ,  Fathi Tarada ,  Bernhard Weigand

发明人： Gordon Anderson ,  Jorgen Ferber ,  Rainer Hocker ,  Fathi Tarada ,  Bernhard Weigand

IPC分类号： F04D2958

CPC分类号： F01D5/187 ,  F05D2260/201 ,  Y02T50/672 ,  Y02T50/676

摘要： The invention relates to an impact flow for wall sections including a plurality of impact openings which are arranged on a plane in a flat or curved support. The support is fitted it a distance from the wall section, and the impact surface of the wall section that is to be cooled is configured as a bulged relief. The bulge elements are arranged around the impact surface of the impact beam. The surfaces of the bulge elements facing the impact beam include two curves which blend into one another.

摘要翻译： 本发明涉及一种用于壁部分的冲击流程，其包括多个冲击开口，其布置在平坦或弯曲的支撑件的平面上。 将支撑件安装在距离壁部分一定距离处，并且要被冷却的壁部分的冲击表面被配置为凸出的浮雕。 凸起元件围绕冲击梁的冲击表面布置。 凸起元件面向冲击梁的表面包括彼此相互融合的两条曲线。

公开(公告)号：US06261053B1

公开(公告)日：2001-07-17

申请号：US09151809

申请日：1998-09-14

申请人： Gordon Anderson ,  Jörgen Ferber ,  Kenneth Hall ,  Michael Hock ,  Fathi Tarada ,  Bernhard Weigand

发明人： Gordon Anderson ,  Jörgen Ferber ,  Kenneth Hall ,  Michael Hock ,  Fathi Tarada ,  Bernhard Weigand

IPC分类号： F01D514

CPC分类号： F01D25/12 ,  F01D5/08 ,  F01D5/143 ,  F01D5/187 ,  F01D11/006 ,  F01D11/04 ,  F05D2250/14 ,  F05D2250/16 ,  F05D2250/192 ,  F05D2250/231 ,  F05D2250/292 ,  F05D2250/312 ,  F05D2250/314 ,  F05D2250/322 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676

摘要： A hot-gas stream (40) flows along the surface of a segment arrangement for shroud bands, in particular in a gas turbine. The segment arrangement comprises segments (20, 20′) arranged next to one another and in each case separated from one another by a gap (12). The hot-gas stream (40), in at least one section (70) of the gap (12), has a velocity component perpendicular to the direction of the gap from a first segment (20) to a second segment (20′). In this case, in said section (70), along that edge (26) of the first segment (20) which faces the gap (12), at least one film-cooling bore (52) connects a cooling-air chamber (50), allocated to the first segment, to the surface (22) subjected to the hot-gas stream (40), and/or, in said section (70), along that edge (26′) of the second segment (20′) which faces the gap (12), at least one edge-cooling bore (56) connects a cooling-air chamber (50′), allocated to the second segment, to the inside (28′) of the gap (12).

摘要翻译： 热气流（40）沿着用于护罩带的段装置的表面流动，特别是在燃气轮机中。 片段装置包括彼此相邻布置并且在每种情况下彼此间隔开间隙（12）的片段（20,20'）。 在间隙（12）的至少一个部分（70）中的热气流（40）具有垂直于从第一段（20）到第二段（20'）的间隙方向的速度分量， 。 在这种情况下，在所述部分（70）中，沿着第一段（20）的面向间隙（12）的边缘（26），至少一个膜冷却孔（52）将冷却空气室 ）分配给第一段的第二段（20'）的边缘（26'）分配给经受热气流（40）的表面（22）和/或在所述部分（70） ），至少一个边缘冷却孔（56）将分配给第二段的冷却空气室（50'）连接到间隙（12）的内部（28'）。

公开(公告)号：US6082961A

公开(公告)日：2000-07-04

申请号：US152516

申请日：1998-09-14

申请人： Gordon Anderson ,  Kenneth Hall ,  Michael Hock ,  Fathi Tarada ,  Bernhard Weigand

发明人： Gordon Anderson ,  Kenneth Hall ,  Michael Hock ,  Fathi Tarada ,  Bernhard Weigand

IPC分类号： F01D5/08 ,  F01D25/08

CPC分类号： F01D9/04 ,  F01D25/12 ,  F01D5/08 ,  F05D2240/81

摘要： Platform cooling having a guide-blade platform (30; 60) which is subjected to a hot-gas stream (20) and is separated by a gap (36; 66) from a combustion-chamber segment (40; 70) arranged upstream, one or more segment cooling bores (42; 72) being made in the combustion-chamber segment (40; 70), which segment cooling bores (42; 72) connect a cooling-air chamber (44; 74) to the gap (36; 66). The guide-blade platform (30; 60) has a surface (34; 64) on the downstream side in the region of the gap (36; 66), the axes of the one or more segment cooling bores (42; 72) running roughly tangentially to said surface (34; 64).

摘要翻译： 平台冷却具有导向叶片平台（30; 60），该导向叶片平台经受热气流（20）并且被间隔（36; 66）与布置在上游的燃烧室段（40; 70）分开， 一个或多个节段冷却孔（42; 72）在燃烧室段（40; 70）中制成，其将冷却孔（42; 72）分段连接冷却空气室（44; 74）与间隙（36; ; 66）。 引导刀片平台（30; 60）在间隙（36; 66）的区域中的下游侧具有表面（34; 64），一个或多个段冷却孔（42; 72）的轴线 大致切向地与所述表面（34; 64）相切。

公开(公告)号：US06644920B2

公开(公告)日：2003-11-11

申请号：US09991970

申请日：2001-11-26

申请人： Alexander Beeck ,  Bernhard Weigand

发明人： Alexander Beeck ,  Bernhard Weigand

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  B23H9/10 ,  B23H9/14 ,  B23H9/16 ,  F01D5/186 ,  F05D2230/12 ,  F05D2240/81 ,  F05D2250/15 ,  F05D2250/25 ,  F05D2250/71 ,  Y10T29/49341

摘要： A method of forming a curved cooling channel into a gas turbine component such as a turbine blade uses an electrode in the form of a helix. The electrode is driven to rotate around the central rotational axis of the helix and axially along the central rotational axis. A turbine blade for a gas turbine component is provided with at least one helical cooling channel.

摘要翻译： 在涡轮叶片等燃气轮机部件中形成弯曲的冷却通道的方法使用螺旋形式的电极。 电极被驱动以围绕螺旋的中心旋转轴线旋转并沿着中心旋转轴线轴向旋转。 用于燃气涡轮机部件的涡轮机叶片设置有至少一个螺旋形冷却通道。

公开(公告)号：US06422811B1

公开(公告)日：2002-07-23

申请号：US09593162

申请日：2000-06-14

申请人： Alexander Beeck ,  Bernhard Weigand

发明人： Alexander Beeck ,  Bernhard Weigand

IPC分类号： F04D2938

CPC分类号： F01D5/188 ,  F02C7/18 ,  F05D2260/2322

摘要： A cooling arrangement for blades of a gas turbine or the like, in each case the blades being built up from a suction-side wall and a pressure-side wall which are connected, to form a cavity, via a leading edge, a trailing edge, a blade tip and a blade root, and a flow path, through which a cooling medium, in particular steam, is capable of flowing, being integrated in the cavity, and in which the flow paths in each case of two or more adjacent blades are connected to one another in such a way that a continuous cooling duct sealed off relative to the hot-gas stream is formed. It thus becomes possible to increase cooling efficiency by better utilization of the cooling medium and at the same time to reduce the outlay in terms of construction.

摘要翻译： 一种用于燃气轮机等的叶片的冷却装置，在每种情况下，叶片由吸入侧壁和压力侧壁构成，所述吸入侧壁和压力侧壁经由前缘连接以形成空腔，后缘 ，叶片尖端和叶片根部，以及流动路径，冷却介质，特别是蒸汽能够流动通过该流动路径集成在空腔中，并且每个情况下的两个或更多个相邻叶片的流动路径 彼此连接，从而形成相对于热气流密封的连续冷却管道。 因此，可以通过更好地利用冷却介质来提高冷却效率，同时可以减少施工方面的费用。

公开(公告)号：US06340284B1

公开(公告)日：2002-01-22

申请号：US09471410

申请日：1999-12-23

申请人： Alexander Beeck ,  Ibrahim El-Nashar ,  Beat Von Arx ,  Bernhard Weigand

发明人： Alexander Beeck ,  Ibrahim El-Nashar ,  Beat Von Arx ,  Bernhard Weigand

IPC分类号： F01D518

CPC分类号： F01D5/225 ,  F01D5/187 ,  F05D2240/81

摘要： In an air-cooled turbine blade which, at the blade tip, has a shroud-band element extending transversely to the longitudinal axis of the blade, a plurality of cooling bores passing through the shroud-band element for the purpose of cooling, which cooling bores are connected on the inlet side to at least one cooling-air passage running through the turbine blade to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade, improved and assured cooling is achieved owing to the fact that the cooling bores run from inside to outside in the shroud-band element at least approximately parallel to the direction of movement of the blade and in each case open upstream of the outer margin of the shroud-band element into a surface recess open toward the exterior space. The top side of the shroud band is preferable provided with at least two ribs and, which run in parallel and, in interaction with the opposite casing wall, form a cavity, into which the cooling air discharging from the cooling bores flows.

摘要翻译： 在风冷涡轮机叶片中，在叶片尖端处具有横向于叶片的纵向轴线延伸的护罩带元件，多个冷却孔穿过护罩带元件用于冷却，该冷却 孔在入口侧连接到至少一个冷却空气通道，该冷却空气通道穿过涡轮机叶片到达叶片尖端，并且在出口侧打开到围绕涡轮机叶片的外部空间中，由于以下事实实现了改进和确保的冷却： 所述冷却孔在所述护罩带元件中从内到外延伸至少大致平行于所述叶片的运动方向，并且在每种情况下，在所述护罩带元件的外缘的上游开口朝向所述外部开口的表面凹部 空间。 护罩带的顶侧优选设置有至少两个肋，并且平行延伸并且与相对的壳体壁相互作用形成空腔，冷却孔从冷却孔排出的冷却空气流过。

公开(公告)号：US06305903B1

公开(公告)日：2001-10-23

申请号：US09379465

申请日：1999-08-24

申请人： Klaus Semmler ,  Bernhard Weigand

发明人： Klaus Semmler ,  Bernhard Weigand

IPC分类号： F01D508

CPC分类号： F01D5/187 ,  F05D2260/221

摘要： A cooled vane for a gas turbine or similar device including a vane blade constructed of a suction side wall and a pressure side wall that are connected via a leading edge and a trailing edge with each other, which has an essentially radially extending cavity through which a cooling medium is capable of flowing. The vane blade has multiple cooling channels that, starting from the cavity, extend through a vane section adjoining the trailing edge and formed by sections of the suction side wall and the pressure side wall, and end at the trailing edge. A first row of cooling channels is associated with the suction side (SS) of the vane blade, and a second row of cooling channels is associated with the pressure side (DS) of the vane blade. The cooled vane has improved cooling efficiency and can be produced entirely with a casting process while complying with basic geometric conditions.

摘要翻译： 一种用于燃气轮机或类似装置的冷却叶片，包括由吸入侧壁和压力侧壁构成的叶片叶片，该叶片叶片经由前缘和后缘彼此连接，所述侧壁具有基本上径向延伸的空腔， 冷却介质能够流动。 叶片叶片具有多个冷却通道，其从腔体开始延伸通过与后缘相邻的叶片部分并且由吸力侧壁和压力侧壁的部分形成并且在后缘处结束。 第一排冷却通道与叶片的吸入侧（SS）相关联，第二排冷却通道与叶片的压力侧（DS）相关联。 冷却的叶片具有提高的冷却效率，并且可以在符合基本几何条件的情况下通过铸造工艺完全制造。

公开(公告)号：US07137777B2

公开(公告)日：2006-11-21

申请号：US10882335

申请日：2004-07-02

申请人： Reinhard Fried ,  Bernhard Weigand

发明人： Reinhard Fried ,  Bernhard Weigand

IPC分类号： F01D5/12

CPC分类号： F01D5/082 ,  F01D11/001 ,  F05D2260/607

摘要： A device separates foreign particles from cooling air fed to turbine rotor blades. The cooling air is fed directly or indirectly via stationary nozzle units to an annular space between wall parts of a turbine stator and rotating wheel disk as a cooling-air stream in the circumferential direction. The annular space communicates with ducts, arranged in the disk, for feeding the cooling air into the blades. A diverter unit is provided inside the annular space or so as to delimit the annular space on one side, so cooling air emerging from the nozzle units, before entering the ducts, is diverted on one side and foreign particles are centrifugally thrown into a radially outer part of the annular space and separated therefrom with a barrier-air fraction. The diverter unit has a surface region on which the stream impinges so it can be diverted radially outward through an angle greater than 90°.

摘要翻译： 一种装置将外来颗粒与供给到涡轮转子叶片的冷却空气分离。 冷却空气通过固定喷嘴单元被直接地或间接地供给到涡轮机定子的壁部分与旋转轮盘之间的环形空间，作为在圆周方向上的冷却空气流。 环形空间与布置在盘中的管道连通，用于将冷却空气供给到叶片中。 在环形空间内设置转向单元，或者在一侧限定环形空间，从而在进入导管之前从喷嘴单元排出的冷却空气在一侧被转向，异物将离心地投入到径向外侧 环形空间的一部分并与阻挡空气部分分离。 分流器单元具有流体撞击的表面区域，使得其可以径向向外转过大于90°的角度。

公开(公告)号：US06464460B2

公开(公告)日：2002-10-15

申请号：US09725722

申请日：2000-11-30

申请人： Ibrahim El-Nashar ,  Beat Von Arx ,  Bernhard Weigand ,  Hartmut Haehnle ,  Rudolf Kellerer

发明人： Ibrahim El-Nashar ,  Beat Von Arx ,  Bernhard Weigand ,  Hartmut Haehnle ,  Rudolf Kellerer

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F01D5/225 ,  F05D2240/81 ,  F05D2250/141

摘要： In an air-cooled turbine blade (10) which has a shroud-band element (11) at the blade tip, the shroud-band element (11) extending transversely to the blade longitudinal axis, hollow spaces (16, 16′, 17, 17′) for cooling being provided in the interior of the shroud-band element (11), which hollow spaces (16, 16′, 17, 17′) are connected on the inlet side to at least one cooling-air passage (18) passing through the turbine blade (10) to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade (10), the hollow spaces (16, 16′, 17, 17′) and the shroud-band element (11) are matched to one another in shape and dimensions in order to reduce the weight of the shroud-band element (11).

摘要翻译： 在风叶涡轮叶片（10）中，在叶片尖端处具有护罩带元件（11），所述护罩带元件（11）横向于叶片纵向轴线延伸，中空空间（16,16'，17 ，17'）设置在所述护罩带元件（11）的内部，所述中空空间（16,16'，17,17'）在入口侧连接到至少一个冷却空气通道（ 18）通过涡轮机叶片（10）到叶片尖端并且在出口侧打开到围绕涡轮机叶片（10）的外部空间中，中空空间（16,16'，17,17'）和护罩 - 带元件（11）的形状和尺寸彼此匹配，以便减少护罩带元件（11）的重量。

公开(公告)号：US06312218B1

公开(公告)日：2001-11-06

申请号：US09414968

申请日：1999-10-12

申请人： Alexander Beeck ,  Mohamed Nazmy ,  Bernhard Weigand

发明人： Alexander Beeck ,  Mohamed Nazmy ,  Bernhard Weigand

IPC分类号： F01D1100

CPC分类号： F01D11/006 ,  F01D11/005

摘要： Described is a sealing arrangement for reducing leakage flows inside a rotary fluid-flow machine, preferably an axial turbomachine, having moving and guide blades, which are in each case arranged in at least one moving- or guide-blade row respectively and have blade roots, via which the individual moving and guide blades are connected to fastening contours. A sealing element having felt-like material is provided between at least two adjacent blade roots within a guide- or moving-blade row or between guide and/or moving blades and adjacent components of the fluid-flow machine.

摘要翻译： 描述了一种用于减少旋转流体流动机器（优选轴向涡轮机）内的泄漏流的密封装置，其具有移动和导向叶片，每个移动和导向叶片分别布置在至少一个移动或导向叶片排中并具有叶片根部 单独的移动和导向叶片通过其连接到紧固轮廓。 具有毛毡状材料的密封元件设置在导向或移动叶片排中的至少两个相邻叶片根之间或在流体流动机器的引导和/或移动叶片和相邻部件之间。