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1. 发明申请

US20100008773A1 Turbine blade and gas turbine equipped with a turbine blade 失效
标题翻译：配有涡轮叶片的涡轮叶片和燃气轮机
公开(公告)号：US20100008773A1
公开(公告)日：2010-01-14
申请号：US12563369
申请日：2009-09-21
申请人： Stefan Baldauf , Hans-Thomas Bolms , Michael Händler , Christian Lerner
发明人： Stefan Baldauf , Hans-Thomas Bolms , Michael Händler , Christian Lerner
IPC分类号： F01D9/02
CPC分类号： F01D5/22 , F01D11/008 , F05D2240/80
摘要： The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.
摘要翻译：本发明涉及一种涡轮叶片，其包括沿叶片轴线延伸的叶片和位于叶片根部的平台区域，该平台区域具有横向延伸到叶片轴线的平台。本发明的目的是以最简单的方式配置燃气轮机的流动通道的定界。因此，平台由靠在叶片上的弹性金属板构成。所述部分通向燃气轮机，其包括沿燃气轮机的轴线延伸的流动管道，所述导管具有用于工作介质的环形横截面和位于第一叶片台的下游的第二叶片台，沿着轴。

2. 发明授权

US07607889B2 Turbine blade and gas turbine equipped with a turbine blade 失效
标题翻译：配有涡轮叶片的涡轮叶片和燃气轮机
公开(公告)号：US07607889B2
公开(公告)日：2009-10-27
申请号：US10586462
申请日：2005-01-12
申请人： Stefan Baldauf , Hans-Thomas Bolms , Michael Händler , Christian Lerner
发明人： Stefan Baldauf , Hans-Thomas Bolms , Michael Händler , Christian Lerner
IPC分类号： F01D5/18 , F01D5/22
CPC分类号： F01D5/22 , F01D11/008 , F05D2240/80
摘要： The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, which is located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.
摘要翻译：本发明涉及一种涡轮叶片，其包括沿叶片轴线延伸的叶片和位于叶片根部的平台区域，该平台区域具有横向于叶片轴线延伸的平台。本发明的目的是以最简单的方式配置燃气轮机的流动通道的定界。因此，平台由靠在叶片上的弹性金属板构成。所述部分通向燃气轮机，其包括沿燃气轮机的轴线延伸的流动管道，所述导管具有用于工作介质的环形横截面和位于第一叶片台的下游的第二叶片台，沿着轴。

3. 发明授权

US08251665B2 Turbine blade and gas turbine equipped with a turbine blade 失效
标题翻译：配有涡轮叶片的涡轮叶片和燃气轮机
公开(公告)号：US08251665B2
公开(公告)日：2012-08-28
申请号：US10585955
申请日：2005-01-12
申请人： Stefan Baldauf , Hans-Thomas Bolms , Michael Händler , Christian Lerner
发明人： Stefan Baldauf , Hans-Thomas Bolms , Michael Händler , Christian Lerner
IPC分类号： F01D5/18
CPC分类号： F01D11/008 , F01D5/22 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A turbine blade is presented including a vane that runs along a blade axis and a platform region, which is located at the root of the vane and has a platform that extends transversally to the blade axis. An improved cooling of a platform region and the transition region is provided from a turbine blade to a platform of a turbine blade. The platform includes a first platform wall that does not support the vane and a second platform wall that supports the vane. At the root of the vane and over the course of the transition region from the turbine blade to the platform, the first platform wall is aerodynamically curved and the course of the second platform wall has a receding shoulder in relation to the first platform wall, as a continuation of the vane.
摘要翻译：提供了一种涡轮机叶片，其包括沿叶片轴线延伸的叶片和位于叶片根部的平台区域，并且具有横向延伸到叶片轴线的平台。从涡轮叶片到涡轮叶片的平台提供了平台区域和过渡区域的改进的冷却。平台包括不支撑叶片的第一平台壁和支撑叶片的第二平台壁。在叶片的根部并且在从涡轮叶片到平台的过渡区域的过程中，第一平台壁在空气动力学上弯曲，并且第二平台壁的过程相对于第一平台壁具有后退的肩部，如叶片的延续。

4. 发明授权

US07963746B2 Turbine blade and gas turbine equipped with a turbine blade 失效
标题翻译：配有涡轮叶片的涡轮叶片和燃气轮机
公开(公告)号：US07963746B2
公开(公告)日：2011-06-21
申请号：US12563369
申请日：2009-09-21
申请人： Stefan Baldauf , Hans-Thomas Bolms , Michael Händler , Christian Lerner
发明人： Stefan Baldauf , Hans-Thomas Bolms , Michael Händler , Christian Lerner
IPC分类号： F01D5/18 , F01D5/22
CPC分类号： F01D5/22 , F01D11/008 , F05D2240/80
摘要： The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.
摘要翻译：本发明涉及一种涡轮叶片，其包括沿叶片轴线延伸的叶片和位于叶片根部的平台区域，该平台区域具有横向延伸到叶片轴线的平台。本发明的目的是以最简单的方式配置燃气轮机的流动通道的定界。因此，平台由靠在叶片上的弹性金属板构成。所述部分通向燃气轮机，其包括沿燃气轮机的轴线延伸的流动管道，所述导管具有用于工作介质的环形横截面和位于第一叶片台的下游的第二叶片台，沿着轴。

5. 发明申请

US20090016881A1 TURBINE BLADE AND GAS TURBINE EQUIPPED WITH A TURBINE BLADE 失效
标题翻译：涡轮叶片和燃气涡轮机配有涡轮叶片
公开(公告)号：US20090016881A1
公开(公告)日：2009-01-15
申请号：US10585955
申请日：2005-01-12
申请人： Stefan Baldauf , Hans-Thomas Bolms , Michael Handler , Christian Lerner
发明人： Stefan Baldauf , Hans-Thomas Bolms , Michael Handler , Christian Lerner
IPC分类号： F01D5/18
CPC分类号： F01D11/008 , F01D5/22 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, which is located at the root of the vane and has a platform that extends transversally to the blade axis. The aim of the invention is to guarantee the improved cooling of a platform region and the transition region from a turbine blade to a platform of a turbine blade, thus ensuring the cooling of the delimitation of a flow channel in a gas turbine. To achieve this, the platform comprises a first platform wall that does not support the vane and a second platform wall that supports said vane. According to the inventive concept, at the root of the vane and over the course of the transition region from the turbine blade to the platform, said first platform wall is aerodynamically curved and the course of the second platform wall has a receding shoulder in relation to the first platform wall, as a continuation of the vane.
摘要翻译：本发明涉及一种涡轮叶片，其包括沿叶片轴线延伸的叶片和位于叶片根部的平台区域，并且具有横向延伸到叶片轴线的平台。本发明的目的是确保平台区域和从涡轮叶片到涡轮叶片的平台的过渡区域的改进的冷却，从而确保冷却燃气涡轮机中的流动通道的定界。为了实现这一点，平台包括不支撑叶片的第一平台壁和支撑叶片的第二平台壁。根据本发明的概念，在叶片的根部处，并且在从涡轮机叶片到平台的过渡区域的过程中，所述第一平台壁是空气动力学弯曲的，并且第二平台壁的过程相对于第一个平台墙，作为叶片的延续。

6. 发明申请

US20080232956A1 Turbine Blade and Gas Turbine Equipped with a Turbine Blade 失效
标题翻译：涡轮叶片和燃气轮机配有涡轮叶片
公开(公告)号：US20080232956A1
公开(公告)日：2008-09-25
申请号：US10586462
申请日：2005-01-12
申请人： Stefan Baldauf , Hans-Thomas Bolms , Michael Handler , Christian Lerner
发明人： Stefan Baldauf , Hans-Thomas Bolms , Michael Handler , Christian Lerner
IPC分类号： F01D11/00
CPC分类号： F01D5/22 , F01D11/008 , F05D2240/80
摘要： The invention relates to a turbine blade (63, 65) comprising a vane (67, 69) that runs along a blade axis (73, 75) and a platform region (61), which is located at the root of the vane (67, 69) and has a platform (71) that extends transversally to the blade axis (73, 75). The aim of the invention is to configure a delimitation (87) of a flow channel (5) of a gas turbine (1) in the simplest possible manner. To achieve this, the platform (71) is configured by an elastic sheet metal part (77, 79) that rests on the vane (67, 69). Said part leads to a gas turbine (1) comprising a flow conduit (5) that runs along an axis (3) of the gas turbine (1), said conduit having an annular cross-section for a working medium (M) and a second (9, 13) vane stage (7, 9, 11, 13) that is situated downstream of a first (7, 11) vane stage, which runs along the axis (3). According to the invention, a vane stage comprises a number of turbine blades (63, 65) that are arranged in a ring and extend radially into the flow channel (5) in accordance with the inventive concept.
摘要翻译：本发明涉及一种涡轮叶片（63,65），其包括沿叶片轴线（73,75）延伸的叶片（67,69）和位于叶片（67）的根部处的平台区域（61），69）并且具有横向延伸到叶片轴线（73,75）的平台（71）。本发明的目的是以最简单的方式配置燃气轮机（1）的流动通道（5）的定界（87）。为了实现这一点，平台（71）由搁置在叶片（67,69）上的弹性金属片（77,79）构成。所述部分通向包括沿着燃气轮机（1）的轴线（3）延伸的流动管道（5）的燃气涡轮机（1），所述导管具有用于工作介质（M）的环形横截面和位于沿轴线（3）延伸的第一（7,11）叶片级的下游的第二（9,13）叶片级（7,9,11,13）。根据本发明，叶片台包括多个涡轮机叶片（63,65），其根据本发明构思被布置成环并径向延伸到流动通道（5）中。

7. 发明申请

US20110176930A1 Turbine vane for a gas turbine and casting core for the production of such 审中-公开
标题翻译：用于燃气轮机的涡轮叶片和用于生产的铸铁芯
公开(公告)号：US20110176930A1
公开(公告)日：2011-07-21
申请号：US13002986
申请日：2009-05-19
申请人： Fathi Ahmad , Hans-Thomas Bolms , Christian Lerner
发明人： Fathi Ahmad , Hans-Thomas Bolms , Christian Lerner
IPC分类号： F01D5/18 , B28B7/28
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2250/712 , F05D2260/2212 , F05D2260/22141
摘要： A turbine vane or blade including an interior structure is provided. In addition, turbulence elements connected directly upstream of openings disposed at the rear edge of the blade of the turbine vane or blade are also provided. These are disposed in a sequence, each having a flow side against which a coolant flows and which is at least partially arched in a concave manner. Preferably, the turbulence elements are configured in a crescent-shaped manner. This makes it possible to enlarge the openings without resulting in an increased consumption of coolant. A casting core is also provided. The openings required in the casting core for the production of the webs of a turbine vane or blade may now be placed at further distances than before.
摘要翻译：提供了包括内部结构的涡轮叶片或叶片。此外，还提供了连接在设置在涡轮机叶片或叶片的叶片的后边缘处的开口的上游的湍流元件。这些按顺序设置，每个具有流动侧，冷却剂流过该流动侧，并且至少部分地以凹形方式拱起。优选地，湍流元件被构造成月牙形。这使得可以扩大开口而不会导致冷却剂的消耗增加。还提供铸芯。用于生产涡轮叶片或叶片的腹板的铸造芯中所需的开口现在可以放置在比以前更远的距离处。

8. 发明申请

US20090220349A1 Method for Producing a Gas Turbine Component Which is to be Coated, With Exposed Holes, Device for Carrying Out the Method, and Coatable Turbine Blade with Film Cooling Holes 有权
标题翻译：用于制造待涂覆的燃气轮机部件的方法，具有暴露的孔，用于执行该方法的装置和具有膜冷却孔的涂覆涡轮机叶片
公开(公告)号：US20090220349A1
公开(公告)日：2009-09-03
申请号：US11992526
申请日：2006-09-14
申请人： Hans-Thomas Bolms , Stefan Irmisch , Jan Münzer
发明人： Hans-Thomas Bolms , Stefan Irmisch , Jan Münzer
IPC分类号： F01D5/18 , B05D3/12 , B24B49/00
CPC分类号： F01D5/005 , B23P2700/06 , F05D2230/80 , F05D2260/80
摘要： There is described a method with which, on the basis of a three-dimensional recording of a component to be reworked, its surface configuration can be determined and stored temporarily so that, after it has been coated, it can be produced in its original surface form, or in its surface form then required, in certain regions, i.e. locally in the area of film-cooling openings. An especially precise and quick three-dimensional recording can be achieved by the use of the triangulation method. In this case, a reference pattern depicted on the component by a projector is recorded by two camera arranged at an angle. From the images from the cameras, the coordinates describing the surface three-dimensionally can then be determined by a control system using the triangulation method.
摘要翻译：描述了一种方法，其基于待加工的部件的三维记录，其表面构造可以被暂时确定和存储，使得在其被涂覆之后，可以在其原始表面形式或其表面形式，然后需要在某些区域，即局部在膜冷却开口的区域中。通过使用三角测量方法可以实现特别精确和快速的三维记录。在这种情况下，通过投影仪在组件上描绘的参考图案由以一定角度布置的两个相机记录。从摄像机的图像中，可以通过使用三角测量法的控制系统来确定三维地描述表面的坐标。

9. 发明申请

US20060133927A1 Gap control system for turbine engines 有权
标题翻译：涡轮发动机间隙控制系统
公开(公告)号：US20060133927A1
公开(公告)日：2006-06-22
申请号：US11014271
申请日：2004-12-16
申请人： Dieter Brillert , Wayne Giddens , Harald Hoell , Robert Sunshine , Juergen Hermeler , Hans-Thomas Bolms
发明人： Dieter Brillert , Wayne Giddens , Harald Hoell , Robert Sunshine , Juergen Hermeler , Hans-Thomas Bolms
IPC分类号： F04D29/08
CPC分类号： F01D11/001 , F01D11/025
摘要： Embodiments of the invention relate to a system and method for controlling the size of gaps in a turbine engine. In many instances, it is desirable to minimize the size of the gaps between neighboring rotating and stationary components in a turbine engine, such as between a disc cover plate and a proximate pre-swirler. According to embodiments of the invention, each component can be provided with a sealing surface. The sealing surfaces can be angled relative to the axis of rotation. The sealing surfaces are spaced from each other so as to form a gap therebetween. The sealing surfaces may or may not be substantially parallel. As a result of such configuration, the size of the gap can be controlled by axial and radial movement of the components. For example, the gap between the cover plate and the pre-swirler can be adjusted by axially movement of the rotor.
摘要翻译：本发明的实施例涉及一种用于控制涡轮发动机中的间隙尺寸的系统和方法。在许多情况下，期望使涡轮发动机中的相邻旋转和静止部件之间的间隙的尺寸最小化，例如在盘盖板和邻近预旋流器之间。根据本发明的实施例，每个部件可以设置有密封表面。密封表面可以相对于旋转轴线成角度。密封表面彼此间隔开，以便在它们之间形成间隙。密封表面可以或可以不基本上平行。作为这种构造的结果，可以通过部件的轴向和径向运动来控制间隙的尺寸。例如，盖板和预旋流器之间的间隙可以通过转子的轴向运动来调节。

10. 发明申请

US20140097157A1 COMBINED METHOD FOR DRILLING A LAYER SYSTEM, IN WHICH MECHANICAL WORKING AND EDM WORKING ARE PERFORMED 审中-公开
标题翻译：用于钻孔机组系统的组合方法，机械工作和电火花加工
公开(公告)号：US20140097157A1
公开(公告)日：2014-04-10
申请号：US14036487
申请日：2013-09-25
申请人： Hans-Thomas Bolms
发明人： Hans-Thomas Bolms
IPC分类号： B23H5/04 , B23B27/00
CPC分类号： B23H5/04 , B23B27/00 , B23H9/10 , Y10T408/03 , Y10T408/353
摘要： A method including mechanical removal and electrical discharge machining (EDM) working allowing symmetrical or asymmetrical holes to be produced with exact contours in a layer system including a metallic substrate and a non-metallic outermost layer is provided. In a first step, an outer region of the hole is worked by mechanical removal. In a final method step, when the underlying substrate or a metallic adhesion promoting layer has been reached an electrical discharge machining tool is used.
摘要翻译：提供了一种包括机械去除和放电加工（EDM）工作的方法，其允许在包括金属基底和非金属最外层的层系统中产生具有精确轮廓的对称或不对称孔。在第一步骤中，孔的外部区域通过机械去除来加工。在最后的方法步骤中，当已经到达底层基底或金属粘合促进层时，使用放电加工工具。

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