公开(公告)号：US06514041B1

公开(公告)日：2003-02-04

申请号：US09949636

申请日：2001-09-12

申请人： Alfred Paul Matheny ,  Alexander Beeck

发明人： Alfred Paul Matheny ,  Alexander Beeck

IPC分类号： F01D508

CPC分类号： F01D25/246 ,  F01D11/18

摘要： A thermal turbo machine is provided for the attachment of guide vanes on its stationary housing with guide vane carriers with a guide vane platform, from which braces extend towards a band that is suspended in a recess in the stationary housing. In particular, part of the axially adjoining heat shield segments form part of the guide vane platform, and the braces are arranged in a V shape. The braces and the guide vane platform furthermore include a first material, and the band of a second material, whereby the first material has a higher coefficient of expansion than the second material. The guide vane carrier according to the invention has the advantage that the radial blade clearance for the guide vanes and at the same time the radial blade clearance for the rotating blades is minimized for different operating conditions of the turbo machine.

摘要翻译： 提供了一种热涡轮机，用于将导向叶片安装在其固定壳体上，该导向叶片载体具有导向叶片平台，该支架从该导向叶片承载件延伸到悬挂在固定壳体中的凹槽中的带状物上。 特别地，轴向相邻的隔热片的一部分形成导叶平台的一部分，并且支架被布置成V形。 支架和导向叶片平台还包括第一材料和第二材料的带，由此第一材料具有比第二材料更高的膨胀系数。 根据本发明的导叶载体的优点在于，对于涡轮机的不同操作条件，用于导向叶片的径向叶片间隙和同时用于旋转叶片的径向叶片间隙最小化。

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。

公开(公告)号：US06481966B2

公开(公告)日：2002-11-19

申请号：US09739282

申请日：2000-12-19

申请人： Alexander Beeck ,  Jörgen Ferber ,  Christoph Nagler ,  Lothar Schneider ,  Klaus Semmler

发明人： Alexander Beeck ,  Jörgen Ferber ,  Christoph Nagler ,  Lothar Schneider ,  Klaus Semmler

IPC分类号： F01D518

CPC分类号： B22D11/0405 ,  F01D5/187 ,  F05D2240/122 ,  F05D2240/304

摘要： In a gas-turbine guide element (30) around which a hot air flow (23) flows and which, at least in a trailing edge region (21), in which the air flow (23) separates from the guide element (30), comprises at least two walls (10, 11) arranged essentially in parallel and connected to one another by ribs (16, 17, 20) in such a way as to form internal cooling passages (18, 19, 25, 26, 27), and which is cooled on the inside with cooling medium (28, 29) flowing through the cooling passages (18, 19, 25, 26, 27), the cooling medium discharging from the guide element (30) at the trailing edge (21) essentially parallel to and between the walls (10, 11), and in a method of producing it, easier reworking and less susceptibility to foreign particles are achieved owing to the fact that at least some of the ribs are arranged as choke ribs (24) so as to terminate essentially flush with the trailing edge (21).

摘要翻译： 在热空气流（23）流过的燃气涡轮引导元件（30）中，并且至少在其中气流（23）与引导元件（30）分离的后缘区域（21）中， 至少两个壁（10,11），其基本上平行布置并且通过肋（16,17,20）彼此连接，以形成内部冷却通道（18,19,25,26,27） 并且在流过冷却通道（18,19,25,26,27）的冷却介质（28,29）在内部冷却，冷却介质从后缘（21）处的引导元件（30）排出 ）基本上平行于壁（10,11），并且在其制造方法中，由于至少一些肋布置为扼流肋（24），实现了更容易的再加工和对外来颗粒的较小的敏感性 ），以便基本上与后缘（21）齐平地终止。

公开(公告)号：US06333069B1

公开(公告)日：2001-12-25

申请号：US09465767

申请日：1999-12-17

申请人： Alexander Beeck

发明人： Alexander Beeck

IPC分类号： B32B3500

CPC分类号： F01D5/186 ,  B23P2700/06 ,  C23C4/01 ,  F01D5/288

摘要： A method is disclosed for preventing harm caused by constrictions in the cooling holes of gas-cooled parts, in particular of gas turbines and/or burners. These constrictions form because the walls of the gas-cooled parts through which the cooling holes extend and which are covered on their outside with a protective, first coating are provided during the course of an overhaul with a second, repeat coating, and coating material is deposited in the cooling holes. Constant flow ratios in the cooling holes are achieved in a simple manner in that prior to the overhaul, the cooling holes are constricted with first means to an extent that corresponds to the later constrictions created during the course of the second coating. The first means are removed after the overhaul. The first means takes the form of an insert with holes that constrict the flow through the cooling holes.

摘要翻译： 公开了一种用于防止由气体冷却部件，特别是燃气轮机和/或燃烧器的冷却孔中的收缩引起的危害的方法。 这些收缩形成是因为冷却孔延伸的气体冷却部分的壁在其外部被保护的第一涂层覆盖，在大修过程中提供了第二重复涂层，涂层材料是 沉积在冷却孔中。 以简单的方式实现冷却孔中的恒定流量比，因为在大修之前，冷却孔以第一装置收缩到对应于在第二次涂覆过程中产生的稍后的收缩的程度。 第一种手段在大修后被删除。 第一种方式采用具有孔的插入物的形式，该孔具有压缩通过冷却孔的流动。

公开(公告)号：US06265022B1

公开(公告)日：2001-07-24

申请号：US09617107

申请日：2000-07-14

申请人： John Fernihough ,  Alexander Beeck ,  Andreas Bögli

发明人： John Fernihough ,  Alexander Beeck ,  Andreas Bögli

IPC分类号： B05D132

CPC分类号： F01D5/28 ,  B23K26/384 ,  B23K26/389 ,  B23K26/40 ,  B23K2101/001 ,  B23K2101/35 ,  B23K2103/42 ,  B23K2103/50 ,  B23K2103/52 ,  B23P2700/06 ,  C23C4/01 ,  Y10T29/49318 ,  Y10T29/49341 ,  Y10T29/49343

摘要： Process of plugging cooling holes (4) of a gas turbine component (1) with an external surface (7), having a cavity (2) and a plurality of cooling holes (4) before coating the gas turbine component (4), characterised in that mask material (6) is applied to the external surface (7) of the component (1) while a fluid is forced through the cooling holes (4), the mask material (6) is thickened while the fluid is forced through the cooling holes (4), the cooling holes (4) are plugged with plug material (6b), the mask material (6a) is removed from the external surface (7) of the component (1), the component (1) and the plugged cooling holes (4) are coated and the plug material (6b) is removed from the cooling holes (4).

摘要翻译： 在涂覆燃气轮机部件（4）之前，将具有空腔（2）和多个冷却孔（4）的具有外表面（7）的燃气轮机部件（1）的冷却孔（4）堵塞的过程，其特征在于 其中当流体被迫通过冷却孔（4）时，掩模材料（6）被施加到部件（1）的外表面（7）上，掩模材料（6）被加厚，同时流体被迫通过 冷却孔（4），冷却孔（4）用塞子材料（6b）堵塞，掩模材料（6a）从部件（1）的外表面（7），部件（1）和 插入堵塞的冷却孔（4），从冷却孔（4）中取出塞子材料（6b）。

公开(公告)号：US06241469B1

公开(公告)日：2001-06-05

申请号：US09419789

申请日：1999-10-18

申请人： Alexander Beeck ,  Mohamed Nazmy

发明人： Alexander Beeck ,  Mohamed Nazmy

IPC分类号： F01D514

CPC分类号： F01D5/183 ,  B22F7/004 ,  C22C49/14 ,  F01D5/186

摘要： Described is a turbine blade with a metal blade body and a protective coating constructed of a porous intermetallic felt, and in the blade body of the turbine blade cooling air channels are constructed that end at the intermetallic felt in order to supply it with cooling air. The intermetallic felt is based on an iron or nickel aluminide alloy with mixing ratios of Fe:Al or Ni:Al of approximately 50:50, and that the protective coating has cooling channels that are facing the blade body and end in the area of the cooling channels. The design of the turbine blades permits their cooling with a smaller amount of cooling air, and, due to improved aerodynamics and a lower cooling air supply, the degree of effectiveness of the turbine is significantly increased.

摘要翻译： 描述了具有金属叶片本体和由多孔金属间毡构成的保护涂层的涡轮机叶片，并且在涡轮机叶片的叶片体中，冷却空气通道被构造成在金属间毛毡处终止以便向其供应冷却空气。 金属间毡是基于Fe / Al或Ni：Al的混合比为约50:50的铁或镍铝化物合金，并且保护涂层具有面向刀体的冷却通道并且在 冷却通道。 涡轮叶片的设计允许其用较少量的冷却空气进行冷却，并且由于改善的空气动力学和较低的冷却空气供应，涡轮机的有效程度显着增加。

公开(公告)号：US20130011242A1

公开(公告)日：2013-01-10

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。

公开(公告)号：US20100074731A1

公开(公告)日：2010-03-25

申请号：US12611241

申请日：2009-11-03

申请人： David J. Wiebe ,  Brian J. Wessell ,  Todd Ebert ,  Alexander Beeck ,  George Liang ,  Walter H. Marussich

发明人： David J. Wiebe ,  Brian J. Wessell ,  Todd Ebert ,  Alexander Beeck ,  George Liang ,  Walter H. Marussich

IPC分类号： F02C7/28

CPC分类号： F01D11/001 ,  F01D11/005

摘要： A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.

摘要翻译： 燃气轮机包括可旋转叶片的前排和后排，在可旋转叶片的前排和后排之间的一排固定叶片，环形中间盘和密封件收纳装置。 可旋转刀片的前排和后排被联接到盘/转子组件的相应的第一和第二部分。 环形中间盘联接到盘/转子组件，以在燃气轮机的运行期间与盘/转子组件一起旋转。 环形中间盘包括联接到盘/转子组件的第一部分的前侧和联接到盘/转子组件的第二部分的后侧。 密封壳体装置联接到环形中间盘，以在燃气轮机的操作期间与环形中间盘和盘/转子组件一起旋转。

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。

公开(公告)号：US06705383B2

公开(公告)日：2004-03-16

申请号：US10002136

申请日：2001-12-05

申请人： Alexander Beeck ,  John Fernihough

发明人： Alexander Beeck ,  John Fernihough

IPC分类号： B22D2300

CPC分类号： B23P15/04 ,  B33Y80/00 ,  F01D5/147 ,  F01D5/18 ,  F05D2230/13 ,  F05D2230/21 ,  F05D2230/23 ,  F05D2230/90 ,  Y10T29/49339 ,  Y10T29/49796

摘要： A process for the rapid production of hollow components of flow machines, in particular turbine blades, for manufacturing development. In the process, the turbine blade to be produced is divided into two or more portions such that none of the portions has a cavity. The two or more portions are individually cast by means of a Rapid Prototype process, and are then joined together to form the hollow component. The process makes possible the simple and cost-effective production of turbine blades for manufacturing development, in particular for the development of the cooling systems.

摘要翻译： 用于快速生产用于制造开发的流动机器，特别是涡轮叶片的中空部件的方法。 在此过程中，待生产的涡轮机叶片被分成两部分或更多部分，使得没有一个部分具有空腔。 两个或更多个部分通过快速原型工艺单独浇铸，然后连接在一起以形成中空部件。 该过程使制造开发中的涡轮叶片的简单和成本有效的生产成为可能，特别是用于冷却系统的开发。