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31. 发明授权

US06422811B1 Cooling arrangement for blades of a gas turbine 有权
标题翻译：燃气轮机叶片的冷却装置
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。

32. 发明授权

US06340284B1 Turbine blade with actively cooled shroud-band element 有权
标题翻译：涡轮叶片带有主动冷却的护罩带元件
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。

33. 发明授权

US06333069B1 Method for preventing harm from constrictions formed during coating with a protective coat in the cooling holes of gas-cooled parts 失效
标题翻译：用于防止在气体冷却部件的冷却孔中用保护涂层涂覆期间形成的收缩的危害的方法
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。

34. 发明授权

US06265022B1 Process of plugging cooling holes of a gas turbine component 失效
标题翻译：堵塞燃气轮机部件的冷却孔的过程
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）。

35. 发明授权

US06241469B1 Turbine blade 有权
标题翻译：涡轮叶片
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。

36. 发明申请

US20130011242A1 GAS TURBINE ENGINE WITH ANGLED AND RADIAL SUPPORTS 有权
标题翻译：气体涡轮发动机带有光束和径向支撑
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。

37. 发明申请

US20100074731A1 Gas Turbine Sealing Apparatus 有权
标题翻译：燃气轮机封口机
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。

38. 发明授权

US06705383B2 Process for the rapid production of hollow components of flow machines for manufacturing development 有权
标题翻译：快速生产用于制造开发的流动机的中空部件的方法
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。

39. 发明授权

US06641360B2 Device and method for cooling a platform of a turbine blade 有权
公开(公告)号：US06641360B2
公开(公告)日：2003-11-04
申请号：US10003419
申请日：2001-12-06
申请人： Alexander Beeck , Stefan Florjancic
发明人： Alexander Beeck , Stefan Florjancic
IPC分类号： F01D518
CPC分类号： F01D5/187 , F01D5/186 , F01D5/225 , F05D2240/81
摘要： Described is a device and a method for cooling a platform of a turbine blade comprising a blade root, a vane with a leading and trailing edge, as well as a blade tip with a platform, through which platform extends radially, at least in part, at least one cooling channel that is connected with at least one outlet channel exiting via an outlet opening at the platform. The invention is characterized in that the outlet channel has, adjacent to the outlet opening, a longitudinal channel direction that extends, in projection, longitudinally to the turbine blade in an essentially co-parallel manner with respect to the flow direction of a local flow field of a mass flux relatively passing by the turbine blade, said flow field directly flowing over the exit opening.

40. 发明授权

US06589011B2 Device for cooling a shroud of a gas turbine blade 有权
标题翻译：用于冷却燃气轮机叶片的护罩的装置
公开(公告)号：US06589011B2
公开(公告)日：2003-07-08
申请号：US09996693
申请日：2001-11-30
申请人： Alexander Beeck , Reinhard Fried , Markus Oehl
发明人： Alexander Beeck , Reinhard Fried , Markus Oehl
IPC分类号： F04D3100
CPC分类号： F01D5/081 , F01D5/187 , F01D5/22 , F01D5/225 , F01D25/12 , F05D2240/81 , F05D2250/191
摘要： Described is a cooling device for a shroud of a gas turbine blade, having a cooling channel system provided in the shroud, which is provided radially to the gas turbine blade with cooling channels that are open on one side, and which is closed off with a cover plate. The invention is characterized in that, between the cover plate and the cooling channels that are open on one side, an impact cooling plate is provided in such a way that the impact cooling plate rests on the cooling channels that are open on one side, is pressed against them by force, and encloses a space with the cover plate.
摘要翻译：描述了一种用于燃气轮机叶片的护罩的冷却装置，其具有设置在护罩中的冷却通道系统，该冷却通道系统设置在燃气轮机叶片的径向上，其具有在一侧敞开的冷却通道，并且其被封闭盖盘。本发明的特征在于，在盖板和一侧开口的冷却通道之间，设置冲击冷却板，使得冲击冷却板支撑在一侧开口的冷却通道上，是用力压住它们，并用盖板封住一个空间。

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