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1. 发明授权

US06575698B2 Sealing of a thermal turbomachine 失效
标题翻译：密封热涡轮机
公开(公告)号：US06575698B2
公开(公告)日：2003-06-10
申请号：US09897477
申请日：2001-07-03
申请人： Alexander Beeck , Ulrich Rathmann , Hans E. Wettstein
发明人： Alexander Beeck , Ulrich Rathmann , Hans E. Wettstein
IPC分类号： F01D1108
CPC分类号： F01D11/127 , F05D2250/283
摘要： A honeycomb structure is arranged on a stator of a gas turbine and is arranged opposite the moving blades of the gas turbine. The honeycomb structure is composed of metal sheets in such a way that webs having double the sheet thickness are obtained and connections of single thickness are obtained between the webs. The angle &agr; between the circumferential direction of the stator and the webs of double thickness is 5° to 175°. This serves to avoid undesirable efforts such as, for example, overheating during friction at the honeycomb structure of the moving blades of the gas turbine.
摘要翻译：蜂窝结构设置在燃气轮机的定子上并与燃气轮机的动叶片相对设置。蜂窝结构由金属板构成，从而获得双层厚度的纤维网，并且在幅材之间获得单一厚度的连接。定子的圆周方向与双层厚度的腹板之间的角度α为5°至175°。这用于避免不期望的努力，例如在燃气轮机的动叶片的蜂窝结构处的摩擦期间过热。

2. 发明授权

US06739594B2 Sealing arrangement between components of a rotating assembly as well as a method for producing a sealing joint 有权
标题翻译：旋转组件的部件之间的密封布置以及密封接头的制造方法
公开(公告)号：US06739594B2
公开(公告)日：2004-05-25
申请号：US09988313
申请日：2001-11-19
申请人： Alexander Beeck , Ulrich Rathmann
发明人： Alexander Beeck , Ulrich Rathmann
IPC分类号： F16J1500
CPC分类号： F16J15/164 , F01D5/08 , F01D9/06 , F01D11/005 , F05D2260/2322 , F05D2300/505 , F16J15/0887 , F16J15/104
摘要： A sealing arrangement between two radially adjoining components of an assembly that rotates during operation, in particular between the rotor and the rotating blade of a gas turbine component includes a sealing element in a depression of an inner one of the two components at the boundary surface to the outer one of the two components. The sealing element is designed in such a way that it does not or does only slightly project beyond the depression during assembly and that, during rotation of the assembly, the centrifugal force acting on it produces a sealing joint between the components. The present sealing arrangement permits an easy installation of rotating blades to the rotor of a gas turbine.
摘要翻译：在操作期间，特别是在转子和燃气轮机部件的旋转叶片之间旋转的组件的两个径向相邻的部件之间的密封装置包括密封元件，该密封元件位于边界表面的两个部件中的内部部分的凹部中，外部的两个组件之一。密封元件被设计成使得其在组装期间不会或仅仅稍微突出超过凹陷，并且在组件旋转期间，作用在其上的离心力在部件之间产生密封接头。本密封装置允许将旋转叶片容易地安装到燃气轮机的转子上。

3. 发明授权

US06499944B1 Turbo machine 有权
标题翻译：涡轮机
公开(公告)号：US06499944B1
公开(公告)日：2002-12-31
申请号：US09657304
申请日：2000-09-07
申请人： Alexander Beeck , Peter Ernst , Shailendra Naik , Ulrich Rathmann
发明人： Alexander Beeck , Peter Ernst , Shailendra Naik , Ulrich Rathmann
IPC分类号： F01D520
CPC分类号： F01D11/127 , F05D2250/28 , F05D2260/20
摘要： A heat shield of a turbo machine is provided with a microstructure. In a preferred embodiment, the microstructure element comprises a plateau, which is arranged on a rib in such a way that the structure has a “T”-shaped cross section. The ribs are preferably embodied as plates set on edge on the heat shield and are aligned with their surface perpendicular to the circumferential direction (U) of the turbo machine. This results in low bending dimensional rigidity in the circumferential direction. In this way, it is possible to accommodate scraping of a component involved in relative motion in the circumferential direction without plastic deformation. Moreover this arrangement gives the maximum possible resistance to a leakage flow. When used at high temperatures, it is furthermore advantageous to provide ways to enable a coolant to be supplied to the microstructure.
摘要翻译：涡轮机的隔热罩具有微结构。在优选实施例中，微结构元件包括平台，其以这样的方式布置在肋上，使得该结构具有“T”形横截面。肋优选地实施为设置在隔热板上的边缘上的板并且与其垂直于涡轮机的圆周方向（U）的表面对齐。这导致圆周方向的弯曲尺寸刚度低。以这种方式，可以容纳在圆周方向上涉及相对运动的部件的刮擦而没有塑性变形。此外，这种布置给出了泄漏流量的最大可能的阻力。当在高温下使用时，还有利的是提供使冷却剂能够供应到微结构的方式。

4. 发明授权

US06916021B2 Sealing arrangement 有权
标题翻译：密封安排
公开(公告)号：US06916021B2
公开(公告)日：2005-07-12
申请号：US10383735
申请日：2003-03-10
申请人： Alexander Beeck , Bruno Benedetti , Andreas Kieninger , Ulrich Rathmann
发明人： Alexander Beeck , Bruno Benedetti , Andreas Kieninger , Ulrich Rathmann
IPC分类号： F01D5/20 , F01D5/22 , F01D11/08 , F16J15/44
CPC分类号： F16J15/445 , F01D5/225 , F01D11/08 , F16J15/444
摘要： The present invention relates to a sealing arrangement which is formed between a rotating assembly (4, 6) and a static assembly (3, 14, 15). In this sealing arrangement, the rotating assembly (4, 6, 16) has at least one cutting element (1) which engages in a counterpart surface on the static component. The present sealing arrangement is distinguished by the fact that the cutting element (1) is designed as a chipping device with a geometrically determined cutting edge with respect to the counterpart surface (2) or forms a chipping device of this type when the rotating assembly is rotating. The proposed sealing arrangement reduces the wear to the cutting element even in the event of adverse rotation or temperature conditions.
摘要翻译：本发明涉及一种形成在旋转组件（4,6）和静态组件（3,14,15）之间的密封装置。在该密封装置中，旋转组件（4,6,16）具有至少一个切割元件（1），该切割元件（1）与静态部件上的配对表面接合。本密封装置的特征在于，切割元件（1）被设计为具有相对于配对表面（2）几何确定的切割边缘的切屑装置，或者当旋转组件为旋转。所提出的密封装置即使在不利的旋转或温度条件的情况下也减少了对切割元件的磨损。

5. 发明授权

US06534975B2 NONDESTRUCTIVE METHOD FOR DETERMINING THE THICKNESS OF A METALLIC PROTECTIVE LAYER ON A METALLIC BASE MATERIAL VIA A DIFFERENT TYPE OF LAYER BETWEEN THE METALLIC PROTECTIVE LAYER AND THE METALLIC BASE MATERIAL 有权
标题翻译：用于通过金属保护层和金属基材之间的不同类型的金属基材料确定金属保护层的厚度的非结合方法
公开(公告)号：US06534975B2
公开(公告)日：2003-03-18
申请号：US09754188
申请日：2001-01-05
申请人： Alexander Beeck , Andreas Boegli , John Fernihough , Klaus Schneider
发明人： Alexander Beeck , Andreas Boegli , John Fernihough , Klaus Schneider
IPC分类号： G01B706
CPC分类号： G01B21/085 , C23C4/12 , F01D5/288 , G01B1/00 , G01B7/105 , G01B17/025
摘要： A nondestructive method for determining the thickness of a metallic protective layer determined by detection of a different type of intervening layer which is situated between the metallic protective layer and the metallic base material, by ultrasound, eddy-current or (pulsed) thermography. The intervening layer may comprise a nonmetallic layer of oxides or carbides, a metallic layer of pure nickel or a layer with depleted Al and Ti content in that region of the base material which is close to the surface. This method can be used for turbine blades in order to determine the layer thickness, for example during the test phase of coating, and to avoid the known destruction of the turbine blade, which is labor- and cost-intensive.
摘要翻译：通过超声，涡流或（脉冲）热成像法检测位于金属保护层和金属基材之间的不同类型的中间层确定金属保护层的厚度的非破坏性方法。中间层可以包括氧化物或碳化物的非金属层，纯镍的金属层或在靠近表面的基材的区域中具有贫化的Al和Ti含量的层。为了确定层厚度，例如在涂层的测试阶段，这种方法可以用于涡轮叶片，并且避免已经破坏涡轮叶片，这是劳力和成本密集型的。

6. 发明授权

US06412541B2 Process for producing a thermally loaded casting 有权
标题翻译：制造热负荷铸件的方法
公开(公告)号：US06412541B2
公开(公告)日：2002-07-02
申请号：US09836297
申请日：2001-04-18
申请人： Hans-Joachim Roesler , Alexander Beeck , Peter Ernst , Reinhard Fried
发明人： Hans-Joachim Roesler , Alexander Beeck , Peter Ernst , Reinhard Fried
IPC分类号： B22C902
CPC分类号： B22C7/023 , B22C7/02 , B22C9/04 , B22C9/043 , F01D5/18 , F01D5/183 , F01D5/186 , F01D5/187 , F05D2230/211 , F05D2300/606 , F05D2300/611 , F05D2300/612
摘要： A thermally highly loaded casting is produced. The casting mold is produced from a slurry using a wax model and a polymer foam which is fixed to the wax model or has been introduced into a cavity. In this way, during the casting process the liquid superalloy also penetrates into the open-cell structure of the casting mold, so that an integral cooling structure is formed during the solidification of the casting. A single-crystal or directionally solidified casting is advantageously produced. It is also conceivable to vary the cell size of the polymer foam, to produce a cooling structure and a base material separately, and to coat the cooling structure with a ceramic protective layer (thermal barrier coating).
摘要翻译：产生热负荷高的铸件。铸造模具由使用蜡模型和聚合物泡沫体的浆料制成，所述蜡模型和聚合物泡沫固定在蜡模型上或已被引入腔中。以这种方式，在铸造过程中，液体超合金也渗透到铸模的开孔结构中，从而在铸件凝固期间形成一体的冷却结构。有利地生产单晶或定向凝固铸件。还可以想到改变聚合物泡沫的泡孔尺寸，分别制造冷却结构和基材，并用陶瓷保护层（热障涂层）涂覆冷却结构。

7. 发明授权

US6012723A Brush gasket 失效
标题翻译：刷垫圈
公开(公告)号：US6012723A
公开(公告)日：2000-01-11
申请号：US919321
申请日：1997-08-28
申请人： Alexander Beeck
发明人： Alexander Beeck
IPC分类号： F16J15/3288 , H02K5/124 , F16J15/44
CPC分类号： H02K5/124 , F16J15/3288 , Y10S277/917
摘要： A brush gasket for two co-operating components located opposite one another. The brush gasket has a carrier body for the brushes arranged on one of the two components to be sealed off relative to one another, for example, a stator and a rotor. The carrier body has a supporting wall for the brushes on the low-pressure side, in order to protect them against pressure-related deformation. On the second of the components, opposite the carrier body, there is an abrasion ring made of a material which is softer than the material of the brushes. The abrasion ring together with the brushes thus forms a gasket group.
摘要翻译：一个用于两个相互配合的配合部件的刷子垫圈。电刷垫圈具有用于电刷的载体，用于相对于彼此密封的两个部件之一，例如定子和转子。载体主体具有用于低压侧的刷子的支撑壁，以便保护它们免受压力相关的变形。在载体主体相对的第二部件上，存在由比电刷材料柔软的材料制成的磨损环。磨损环与刷子一起形成垫圈组。

8. 发明授权

US08770924B2 Gas turbine engine with angled and radial supports 有权
标题翻译：具有角度和径向支撑的燃气涡轮发动机
公开(公告)号：US08770924B2
公开(公告)日：2014-07-08
申请号：US13177701
申请日：2011-07-07
申请人： Alexander Beeck , Malberto Gonzalez , Jerome H. Katy , David J. Wiebe
发明人： Alexander Beeck , Malberto Gonzalez , Jerome H. Katy , David J. Wiebe
IPC分类号： F01D25/16
CPC分类号： F01D25/28 , F01D25/30 , F05D2250/314
摘要： A support structure in a gas turbine engine including an inner annular wall and an outer annular wall defining an annular flow path, a casing housing the structure defining the flow path, and a bearing compartment housing a rotor shaft bearing located radially inwardly from the inner annular wall. The support structure includes a plurality of circumferentially spaced radial support members extending radially inwardly from an outer mount connection at the casing to an inner mount connection at the bearing compartment housing. The radial support members provide structural support for radial bearing loads on the rotor shaft bearing. A plurality of circumferentially spaced axial support members extend radially and axially inwardly from an outer mount connection at the casing to an inner mount connection located on an annular structure extending radially between connection locations at the bearing compartment housing and the inner annular wall.
摘要翻译：一种燃气涡轮发动机中的支撑结构，包括内环形壁和限定环形流路的外环形壁，容纳限定流路的结构的壳体和容纳从内环径向向内定位的转子轴轴承的轴承室壁。支撑结构包括多个周向间隔开的径向支撑构件，其从壳体处的外部安装连接件径向向内延伸到轴承隔室壳体处的内部安装连接。径向支撑构件为转子轴承上的径向轴承负载提供结构支撑。多个周向间隔开的轴向支撑构件从壳体处的外部安装连接件径向和轴向向内延伸到位于在轴承隔室壳体和内部环形壁处的连接位置之间径向延伸的环形结构上的内部安装连接件。

9. 发明授权

US06446710B2 Arrangement for cooling a flow-passage wall surrrounding a flow passage, having at least one rib element 失效
标题翻译：用于冷却具有至少一个肋元件的流动通道周围的流动通道壁的布置
公开(公告)号：US06446710B2
公开(公告)日：2002-09-10
申请号：US09726424
申请日：2000-12-01
申请人： Alexander Beeck , Bernhard Bonhoff , Sacha Parneix , Bernhard Weigand
发明人： Alexander Beeck , Bernhard Bonhoff , Sacha Parneix , Bernhard Weigand
IPC分类号： F28F1312
CPC分类号： F01D5/187 , F05D2260/22141 , F23R2900/03045 , F28F1/40 , F28F3/02 , F28F13/12 , Y10T137/2093
摘要： An arrangement for cooling a flow-passage wall surrounding a flow passage is described, having at least one rib element which induces flow vortices in a flow medium passing through the flow passage, is attached to that side of the flow-passage wall which faces the flow passage, and the shape and size of which are selected in accordance with a certain heat transfer coefficient and a certain pressure loss caused in the flow medium due to the latter flowing over the rib element. The invention is characterized in that the rib element, while largely retaining its original shape and/or size, has contours enlarging its surface facing the flow passage.
摘要翻译：描述了用于冷却围绕流动通道的流动通道壁的布置，其具有至少一个在通过流动通道的流动介质中引起流动涡流的肋元件，其连接到流动通道壁的面向流动通道，其形状和尺寸根据一定的传热系数和由于流体介质流过肋元件而在流动介质中引起的一定的压力损失来选择。本发明的特征在于，虽然在很大程度上保持其原始形状和/或尺寸，但是其轮廓扩大了其面向流动通道的表面。

10. 发明授权

US06416282B1 Rotor for a gas turbine 失效
标题翻译：转子为燃气轮机
公开(公告)号：US06416282B1
公开(公告)日：2002-07-09
申请号：US09686963
申请日：2000-10-12
申请人： Alexander Beeck , Herbert Brandl , Hartmut Haehnle , Beat von Arx
发明人： Alexander Beeck , Herbert Brandl , Hartmut Haehnle , Beat von Arx
IPC分类号： F01D518
CPC分类号： F01D5/087 , F01D5/3015
摘要： A rotor for a gas turbine comprises a multiplicity of rotor blades of which each comprises a blade airfoil, a blade root and a platform arranged between blade airfoil and blade root and each of which, together with the blade root, is pushed into an axial location slot, which is arranged on the outer periphery of a rotor disk, and is releasably retained there in such a way that hollow spaces are formed between the platform and the peripheral surface of the rotor disk, and each of which is supplied, for cooling purposes, with cooling air through at least one cooling air supply passage extending in the rotor disk and emerging into the location slot, which cooling air is fed through the blade root to within the blade airfoil.
摘要翻译：用于燃气轮机的转子包括多个转子叶片，每个转子叶片包括叶片翼型件，叶片根部和布置在叶片翼型件和叶片根部之间的平台，并且每个转子叶片与叶片根部一起被推入轴向位置槽，其布置在转子盘的外周上，并且可释放地保持在其中，使得在平台和转子盘的周边表面之间形成中空空间，并且为了冷却目的而提供每个槽其中冷却空气通过至少一个在转子盘中延伸的冷却空气供应通道并且出现到定位槽中，该冷却空气通过叶片根部被供给到叶片翼型内。

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