公开(公告)号：US06634859B2

公开(公告)日：2003-10-21

申请号：US10006725

申请日：2001-12-10

申请人： Bernhard Weigand ,  James P. Downs

发明人： Bernhard Weigand ,  James P. Downs

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F05D2260/201

摘要： An apparatus and a process are provided for impingement cooling of a component exposed to heat in a flow machine. The component includes a wall section on at least one side of which at least one impingement air flow impinges, the air flow passing through a flow channel within a surface element arranged spaced apart from the wall section and striking against the wall section to be cooled. The flow channel has an inlet aperture and an outlet aperture, with the outlet aperture directly facing toward the wall section to be cooled, and the inlet aperture has a throughflow cross section which is smaller than the throughflow cross section of the outlet aperture.

摘要翻译： 提供了一种用于在流动机器中暴露于热量的部件的冲击冷却的装置和工艺。 所述部件包括至少一个侧壁上的至少一个冲击气流撞击的壁部分，所述空气流通过与所述壁部分隔开布置的表面元件内的流动通道，并撞击待冷却的壁部分。 流动通道具有入口孔和出口孔，出口孔直接面向待冷却的壁部分，并且入口孔具有小于出口孔的通过横截面的通流横截面。

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。

公开(公告)号：US5934874A

公开(公告)日：1999-08-10

申请号：US916789

申请日：1997-08-25

申请人： Kenneth Hall ,  Bernhard Weigand

发明人： Kenneth Hall ,  Bernhard Weigand

IPC分类号： F01D5/18 ,  F02C7/18

CPC分类号： F01D5/187 ,  F05D2260/201

摘要： A coolable blade (10) essentially comprises a blade root (11) and a blade body (1), which is composed of a pressure-side wall (6) and a suction-side wall (5). They are connected to one another essentially via a trailing-edge region (4) and a leading-edge region (3) in such a way that at least one hollow space (2) used as a cooling-fluid passage is formed. An essentially radially running, diverging cooling passage (7) is arranged in the trailing-edge region (4).

摘要翻译： 可冷却叶片（10）基本上包括由压力侧壁（6）和吸力侧壁（5）组成的叶片根部（11）和叶片体（1）。 它们基本上通过后缘区域（4）和前缘区域（3）彼此连接，使得形成用作冷却流体通道的至少一个中空空间（2）。 在后缘区域（4）中布置有基本上径向延伸的发散冷却通道（7）。

公开(公告)号：US06923247B1

公开(公告)日：2005-08-02

申请号：US09431178

申请日：1999-11-01

申请人： Jörgen Ferber ,  Bernhard Weigand

发明人： Jörgen Ferber ,  Bernhard Weigand

IPC分类号： B23K26/38 ,  F01D5/18 ,  F01D5/08 ,  B64C11/24

CPC分类号： F01D5/186 ,  B23K26/389 ,  F05D2250/232 ,  Y10T29/49341

摘要： A thermally highly loaded machine component (10), which is protected from overheating by film cooling, is provided with conical cooling passages (30) of circular cross section. The cooling passages are designed so as to be divergent from the cold-gas side (13) toward the hot-gas side. The conical cooling passages, as compared with cylindrical passages with regard to the mass flow of cooling medium (35) fed through the cooling passages, are substantially less dependent on the pressure ratio between the cold-gas side (13) and hot-gas side (14) of the component. The straight conical cooling passages of round cross section throughout may be produced in a very simple manner by laser drilling, with a convergent cutting beam being used for the machining.

摘要翻译： 具有圆形横截面的圆锥形冷却通道（30），通过薄膜冷却而防止过热的热负荷高的机器部件（10）。 冷却通道被设计成从冷气侧（13）向热气侧发散。 与通过冷却通道供给的冷却介质（35）的质量流量的圆柱形通道相比，锥形冷却通道基本上较冷冷气侧（13）和热气体侧之间的压力比 （14）。 整个圆形横截面的直锥形冷却通道可以通过激光钻孔以非常简单的方式产生，并且会聚切割梁用于机加工。