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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。

4. 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。

5. 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。

6. 发明授权

US07758309B2 Vane wheel of turbine comprising a vane and at least one cooling channel 有权
标题翻译：涡轮的叶轮包括叶片和至少一个冷却通道
公开(公告)号：US07758309B2
公开(公告)日：2010-07-20
申请号：US11632013
申请日：2005-06-13
申请人： Hans-Thomas Bolms , Andreas Heselhaus , Roland Häbel , Torsten Koch , Ralf Müsgen
发明人： Hans-Thomas Bolms , Andreas Heselhaus , Roland Häbel , Torsten Koch , Ralf Müsgen
IPC分类号： F01D5/18
CPC分类号： F01D5/30 , F01D5/081 , F01D25/12 , F05D2230/12 , F05D2240/127 , F05D2240/81 , F05D2250/291 , F05D2260/2212 , F05D2260/22141
摘要： There is described a vane wheel of a turbine comprising at least one vane, the footing thereof being held on a wheel disk. At least one cooling channel is arranged between the wheel disk and the vane footing. The vane wheel having a plurality of turbulators is embodied on at least one of the walls of the cooling channel, the turbulators being configured in such a way that the turbulence and thus the heat transfer of a cooling fluid flowing through the cooling channel are increased.
摘要翻译：描述了一种涡轮机的叶轮，包括至少一个叶片，其叶片保持在轮盘上。至少一个冷却通道设置在轮盘和叶片基脚之间。具有多个紊流器的叶轮被实施在冷却通道的壁中的至少一个壁上，所述湍流器被构造成使得流过冷却通道的冷却流体的紊流以及热传递增加。

7. 发明授权

US07246993B2 Coolable segment for a turbomachine and combustion turbine 失效
标题翻译：用于涡轮机和燃气轮机的可冷却段
公开(公告)号：US07246993B2
公开(公告)日：2007-07-24
申请号：US10756671
申请日：2004-01-13
申请人： Hans-Thomas Bolms , Andreas Heselhaus , Bernhard Hoffschmidt
发明人： Hans-Thomas Bolms , Andreas Heselhaus , Bernhard Hoffschmidt
IPC分类号： F01D25/12 , F01D11/08
CPC分类号： F23R3/005 , F01D25/12 , F01D25/14 , F02K1/822 , F05D2260/20 , F23R3/007 , F23R3/06 , F23R2900/03041 , Y02T50/67 , Y02T50/671 , Y02T50/676
摘要： A coolable segment for a turbomachine such as a combustion turbine, which turbomachine is operated with a hot fluid. The segment comprises a cooling wall extending in an axial direction and in a circumferential direction orthogonal to the axial direction; a hot fluid surface to be exposed to the hot fluid. Between the wall and the surface a cooling structure is arranged which is permeable to cooling fluid and provides cooling surfaces for cooling by heat transmission through radiation. The cooling structure comprises either a netting, in particular a wire netting or a porous material.
摘要翻译：用于诸如燃气轮机的涡轮机的可冷却段，该涡轮机用热流体操作。所述片段包括在轴向方向和与所述轴向正交的圆周方向上延伸的冷却壁; 暴露于热流体的热流体表面。在壁和表面之间设置有冷却结构，其可冷却流体是可渗透的，并且通过辐射通过热传递提供用于冷却的冷却表面。冷却结构包括网，特别是网网或多孔材料。

8. 发明授权

US07234918B2 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：US07234918B2
公开(公告)日：2007-06-26
申请号：US11014271
申请日：2004-12-16
申请人： Dieter Brillert , Wayne Giddens , Harald Hoell , Robert W. Sunshine , Juergen Hermeler , Hans-Thomas Bolms
发明人： Dieter Brillert , Wayne Giddens , Harald Hoell , Robert W. Sunshine , Juergen Hermeler , Hans-Thomas Bolms
IPC分类号： F01D11/08
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。

9. 发明申请

US20060002796A1 Turbine blade 有权
标题翻译：涡轮叶片
公开(公告)号：US20060002796A1
公开(公告)日：2006-01-05
申请号：US11174275
申请日：2005-07-01
申请人： Hans-Thomas Bolms , Ralf Musgen
发明人： Hans-Thomas Bolms , Ralf Musgen
IPC分类号： B63H1/14
CPC分类号： F01D5/186 , F05D2250/314 , F05D2250/34 , F05D2260/202
摘要： A turbine blade (2), with a root section (4), with a tip section (6) and with a blade leaf (12) which is provided with a number of coolant ducts (22) through which a coolant (K) is capable of flowing, outlet ducts (34) which issue in outlet ports (24) branching off, in the leading edge region (28) of the blade leaf (12), from a coolant duct (22) running essentially in the longitudinal direction (L) of the turbine blade (2) and spaced apart from the leading edge (14), the outlet ports (24) being arranged along at least two rows oriented essentially parallel to the leading edge (14), and the outlet ducts (34) being oriented, in the region of their respective outlet port (24), obliquely with respect to the longitudinal direction (L) of the turbine blade (2), in such a way that the coolant (K) flowing out in a root-side subsection (38) of each row possesses, in the region of the outlet ports (24), a velocity component pointing toward the tip section (6) of the turbine blade (2), and the coolant (K) flowing out in a tip-side subsection (42), continguous thereto, of each row has a velocity component pointing toward the root section (4), is designed for a particularly reliable and uniform cooling of the leading edge region (28), at the same time with the requirement for coolant (K) being kept particularly low. For this purpose, according to the invention, the transitional points (40) at which the orientation of the outlet ducts (34) changes are arranged so as to be offset relative to one another in the longitudinal direction (L) in each case for two adjacent rows.
摘要翻译：一种具有根部（4）的涡轮叶片（2），具有尖端部分（6）和叶片叶片（12），叶片叶片（12）设置有多个冷却剂管道（22），冷却剂（K）能够流动的出口管道（34）从在叶片叶片（12）的前缘区域（28）中分支出来的出口端口（24）从基本上在纵向方向上运行的冷却剂管道（22）涡轮叶片（2）的间隔开并与前缘（14）间隔开，出口端口（24）沿至少两排排列成基本上平行于前缘（14）排列，出口管道（34））在其各自的出口（24）的区域中相对于涡轮机叶片（2）的纵向方向（L）倾斜，使得冷却剂（K）以根部的方式流出，每排的侧部分（38）在出口端口（24）的区域中具有指向尖端部分的速度分量（涡轮叶片（2）的流体分量（6）和与每一行相邻的尖端侧分段（42）中流出的冷却剂（K）具有指向根部（4）的速度分量，被设计用于对前缘区域（28）的特别可靠和均匀的冷却，同时对冷却剂（K）的要求保持特别低。为此，根据本发明，出口管道34的取向发生变化的过渡点40被布置成在纵向方向（L）上相对于彼此在每种情况下彼此偏移两个相邻行。

10. 发明授权

US10180081B2 Process for cooling the turbine stage and gas turbine having a cooled turbine stage 有权
公开(公告)号：US10180081B2
公开(公告)日：2019-01-15
申请号：US14009905
申请日：2012-03-08
申请人： Hans-Thomas Bolms , Boris Dobrzynski
发明人： Hans-Thomas Bolms , Boris Dobrzynski
IPC分类号： F01D25/12 , F01D5/18 , F02C7/18
摘要： A gas turbine having a turbine stage is presented. The gas turbine has a guide vane that can be operated cooled by a cooling medium, and a cooling medium feed device for feeding the cooling medium into the interior of the guide van, which, in the region of its rear edge, has on the pressure side at least one cooling medium outlet opening, through which the cooling medium can flow out of the interior of the guide vane into the main flow. The cooling medium feed device has a mass flow control device for controlling the mass flow through the at least one cooling medium outlet opening, with which the mass flow through the at least one cooling medium outlet opening can be increased during operation of the gas turbine under part-load compared to operation of the gas turbine under full load.

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