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21. 发明授权

US09597751B2 Method for producing a hole with side-delimiting flanks in a component 有权
公开(公告)号：US09597751B2
公开(公告)日：2017-03-21
申请号：US12381835
申请日：2009-03-17
申请人： Hans-Thomas Bolms , Jan Münzer , Thomas Podgorski , Lutz Wolkers
发明人： Hans-Thomas Bolms , Jan Münzer , Thomas Podgorski , Lutz Wolkers
IPC分类号： B23K26/38 , B23K26/384 , B23K26/382 , B23K101/00
CPC分类号： B23K26/384 , B23K26/382 , B23K26/389 , B23K2101/001
摘要： A method for producing a hole with side-delimiting flanks in a component using a laser beam is provided. A laser beam is directed onto the component. A side flank of the hole is traced with the laser beam. A partial volume of the hole is formed by vaporizing the component material. This is repeated until the whole volume is formed. The laser beam may be oriented so that it includes an angle of more than 8° with the traced side flank.

22. 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。

23. 发明申请

US20090283508A1 Method for producting a hole 有权
标题翻译：产生孔的方法
公开(公告)号：US20090283508A1
公开(公告)日：2009-11-19
申请号：US12381835
申请日：2009-03-17
申请人： Hans-Thomas Bolms , Jan Munzer , Thomas Podgorski , Lutz Wolkers
发明人： Hans-Thomas Bolms , Jan Munzer , Thomas Podgorski , Lutz Wolkers
IPC分类号： B23K26/38
CPC分类号： B23K26/384 , B23K26/382 , B23K26/389 , B23K2101/001
摘要： A method for producing a hole with side-delimiting flanks in a component using a laser beam is provided. A laser beam is directed onto the component. A side flank of the hole is traced with the laser beam. A partial volume of the hole is formed by vaporizing the component material. This is repeated until the whole volume is formed. The laser beam may be oriented so that it includes an angle of more than 8° with the traced side flank.
摘要翻译：提供了一种使用激光束在组件中制造具有侧边界侧面的孔的方法。激光束被引导到组件上。孔的侧面用激光束追踪。孔的部分体积通过蒸发组分材料而形成。直到形成整个体积为止。激光束可以被定向成使得其与跟踪的侧面包括大于8°的角度。

24. 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。

25. 发明授权

US07402335B2 Layer structure and method for producing such a layer structure 失效
标题翻译：用于制造这种层结构的层结构和方法
公开(公告)号：US07402335B2
公开(公告)日：2008-07-22
申请号：US10563948
申请日：2004-06-17
申请人： Hans-Thomas Bolms , Andreas Heselhaus
发明人： Hans-Thomas Bolms , Andreas Heselhaus
IPC分类号： B32B5/14
CPC分类号： C23C28/3215 , C23C28/042 , C23C28/322 , C23C28/345 , C23C28/3455 , C23C30/00 , F01D5/183 , F01D5/288 , Y10T428/249954 , Y10T428/249955 , Y10T428/249956 , Y10T428/249961 , Y10T428/249967 , Y10T428/24997 , Y10T428/24999
摘要： The invention relates to a temperature resistant layered structure comprising a substrate and a porous layer arranged on the substrate having a pore defined by a wall, and a ceramic coating on an interior surface of the wall. The invention also relates to a layered turbine component arrangement comprising a substrate having a cooling passage adapted to allow a cooling gas medium to pass through the substrate and a porous layer arranged on the substrate, the porous layer having cooling passages formed by gas-permeable inter-connections between pores in the porous layer.
摘要翻译：本发明涉及一种耐温分层结构，其包括基板和布置在基板上的多孔层，其具有由壁限定的孔，以及在该壁的内表面上的陶瓷涂层。本发明还涉及一种层状涡轮机部件装置，其包括具有适于允许冷却气体介质通过基板的冷却通道的基板和布置在基板上的多孔层，多孔层具有由透气相互隔开的冷却通道 - 多孔层中的孔之间的连接。

26. 发明授权

US06612806B1 Turbo-engine with an array of wall elements that can be cooled and method for cooling an array of wall elements 失效
标题翻译：涡轮发动机具有可以冷却的壁元件阵列，并且用于冷却壁元件阵列的方法
公开(公告)号：US06612806B1
公开(公告)日：2003-09-02
申请号：US09937594
申请日：2001-09-28
申请人： Hans-Thomas Bolms , Peter Tiemann
发明人： Hans-Thomas Bolms , Peter Tiemann
IPC分类号： F01D500
CPC分类号： F02C7/18 , F01D25/12 , F05D2260/201
摘要： A turbomachine includes a coolable arrangement, having a first wail element and having a second wall element. Coolant is used to cool the arrangement in a turbomachine. After the impingement cooling of the first wall element, the coolant is further used for cooling the second wall element.
摘要翻译：涡轮机包括一个可冷却的装置，具有一个第一堰元件并具有第二个壁元件。冷却液用于冷却涡轮机中的排列。在第一壁元件的冲击冷却之后，冷却剂被进一步用于冷却第二壁元件。

27. 发明授权

US06533547B2 Turbine blade 有权
标题翻译：涡轮叶片
公开(公告)号：US06533547B2
公开(公告)日：2003-03-18
申请号：US09796309
申请日：2001-02-28
申请人： Dirk Anding , Burkhard Bischoff-Beiermann , Hans-Thomas Bolms , Michael Scheurlen , Thomas Schulenberg , Peter Tiemann
发明人： Dirk Anding , Burkhard Bischoff-Beiermann , Hans-Thomas Bolms , Michael Scheurlen , Thomas Schulenberg , Peter Tiemann
IPC分类号： F04D2958
CPC分类号： F01D5/188
摘要： The turbine blade has an internal space through which a coolant fluid is guided and in which stiffening ribs are formed to reinforce and support the external walls. Coolant screens that reduce the cooling of the stiffening ribs, are arranged in front of the stiffening ribs in order to reduce thermal stresses. The turbine blade is preferably a gas turbine blade.
摘要翻译：涡轮叶片具有内部空间，冷却剂流体通过该内部空间被引导，并且其中形成有加强肋以加强和支撑外壁。减少加强筋的冷却的冷却液筛被布置在加强筋的前面，以减少热应力。涡轮叶片优选为燃气轮机叶片。

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