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1. 发明授权

US08353663B2 Shroud seal segments arrangement in a gas turbine 有权
标题翻译：护罩密封段布置在燃气轮机中
公开(公告)号：US08353663B2
公开(公告)日：2013-01-15
申请号：US13011203
申请日：2011-01-21
申请人： Tanguy Arzel , Thomas Heinz-Schwarzmaier , Martin Schnieder
发明人： Tanguy Arzel , Thomas Heinz-Schwarzmaier , Martin Schnieder
IPC分类号： F04D29/38
CPC分类号： F01D11/24 , F01D5/08 , F01D11/08 , F01D25/12 , F05D2240/11 , F05D2260/201 , F05D2260/202 , F05D2260/205
摘要： A gas turbine is provided that includes a rotor which is rotatable around an axis and equipped with rotor blades, and which is concentrically enclosed at a distance by a casing, which is equipped with stator blades, forming an annular hot gas passage. Rings with stator blades and rotor blades are arranged in a manner alternating in the axial direction. Between adjacent stator blades, heat shield segments are arranged, which delimit the hot gas passage on the outside in a region of the rotor blades and are cooled by impingement cooling where a cooling medium from an outer annular cavity flows into the heat shield segment.
摘要翻译：提供了一种燃气轮机，其包括能够绕轴线旋转并且配备有转子叶片的转子，并且由配置有定子叶片的壳体一定距离同心地封闭，该壳体形成环形的热气体通道。具有定子叶片和转子叶片的环以轴向交替排列。在相邻的定子叶片之间，布置有隔热板段，其在转子叶片的区域中限定外部的热气体通道，并且通过来自外部环形空腔的冷却介质流入隔热板段的冲击冷却来冷却。

2. 发明申请

US20120063891A1 COOLED COMPONENT FOR A GAS TURBINE 审中-公开
标题翻译：用于气体涡轮的冷却组件
公开(公告)号：US20120063891A1
公开(公告)日：2012-03-15
申请号：US13247429
申请日：2011-09-28
申请人： Jörg Krückels , Tanguy Arzel , Jose Anguisola Mcfeat , Martin Schnieder
发明人： Jörg Krückels , Tanguy Arzel , Jose Anguisola Mcfeat , Martin Schnieder
IPC分类号： F04D29/58
CPC分类号： F01D5/186 , F01D5/187 , F01D5/225 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/205
摘要： A cooled component for a gas turbine is disclosed, which by an outer side of a wall delimits hot gas passage of the gas turbine and on an inner side has a device for impingement cooling. The impingement cooling device can include a multiplicity of impingement cooling chambers which are arranged next to each other, operate in parallel, are covered by impingement cooling plates which are equipped with impingement cooling holes, and are impinged upon by cooling air during operation.
摘要翻译：公开了一种用于燃气轮机的冷却部件，其通过壁的外侧限定燃气轮机的热气体通道，并且在内侧具有用于冲击冷却的装置。冲击冷却装置可以包括彼此相邻布置的多个冲击冷却室，并联操作，被装有冲击冷却孔的冲击冷却板覆盖，并且在操作期间被冷却空气撞击。

3. 发明申请

US20090285676A1 CONTINUOUS-FLOW MACHINE, TURBINE, OR COMPRESSOR 有权
标题翻译：连续流量机，涡轮机或压缩机
公开(公告)号：US20090285676A1
公开(公告)日：2009-11-19
申请号：US12429249
申请日：2009-04-24
申请人： Volker Eppler , Tanguy Arzel , Martin Schnieder
发明人： Volker Eppler , Tanguy Arzel , Martin Schnieder
IPC分类号： F01D11/00
CPC分类号： F01D11/04 , F01D25/12 , F02C7/18 , F02C7/28
摘要： A continuous-flow machine (1), in particular a turbine or a compressor, includes at least one stator blade section (2) which has a plurality of stator blades (3) which project into a gas path (10) of a working gas, and at least one adjacent section (6), which has a plurality of adjacent elements (7), which bound the working gas path (10) at the side. A gap (11), through which a cooling gas can be introduced into the working gas path (10), is formed between the stator blades (3) of the stator blade section (2) and the adjacent elements (7) of the adjacent section (6). In order to improve the efficiency of the continuous-flow machine (1), lateral seals (14) are formed in the gap (11) and prevent or at least impede pressure equalization and/or a gas flow in the gap (11) in the lateral direction (5).
摘要翻译：连续流动机器（1），特别是涡轮机或压缩机，包括至少一个定子叶片部分（2），该定子叶片部分（2）具有多个定子叶片（3），该定子叶片突出到工作气体，以及至少一个相邻部分（6），其具有多个邻近的元件（7），所述多个相邻元件（7）在该侧面上限制了工作气体通道（10）。在定子叶片部分（2）的定子叶片（3）和邻近的定子叶片部分（2）的相邻元件（7）之间形成有可以将冷却气体引入工作气体通道（10）的间隙（11）第（6）节。为了提高连续流动机（1）的效率，在间隙（11）中形成侧向密封件（14），并且防止或至少妨碍间隙（11）中的压力平衡和/或气体流动横向（5）。

4. 发明授权

US08057164B2 Continuous-flow machine, turbine, or compressor 有权
标题翻译：连续流量机，涡轮机或压缩机
公开(公告)号：US08057164B2
公开(公告)日：2011-11-15
申请号：US12429249
申请日：2009-04-24
申请人： Volker Eppler , Tanguy Arzel , Martin Schnieder
发明人： Volker Eppler , Tanguy Arzel , Martin Schnieder
IPC分类号： F01D5/14 , F03D11/00 , F04D29/38
CPC分类号： F01D11/04 , F01D25/12 , F02C7/18 , F02C7/28
摘要： A continuous-flow machine (1), in particular a turbine or a compressor, includes at least one stator blade section (2) which has a plurality of stator blades (3) which project into a gas path (10) of a working gas, and at least one adjacent section (6), which has a plurality of adjacent elements (7), which bound the working gas path (10) at the side. A gap (11), through which a cooling gas can be introduced into the working gas path (10), is formed between the stator blades (3) of the stator blade section (2) and the adjacent elements (7) of the adjacent section (6). In order to improve the efficiency of the continuous-flow machine (1), lateral seals (14) are formed in the gap (11) and prevent or at least impede pressure equalization and/or a gas flow in the gap (11) in the lateral direction (5).
摘要翻译：连续流动机器（1），特别是涡轮机或压缩机，包括至少一个定子叶片部分（2），该定子叶片部分（2）具有多个定子叶片（3），该定子叶片突出到工作气体，以及至少一个相邻部分（6），其具有多个邻近的元件（7），所述多个相邻元件（7）在该侧面上限制了工作气体通道（10）。在定子叶片部分（2）的定子叶片（3）和邻近的定子叶片部分（2）的相邻元件（7）之间形成有可以将冷却气体引入工作气体通道（10）的间隙（11）第（6）节。为了提高连续流动机（1）的效率，在间隙（11）中形成侧向密封件（14），并且防止或至少妨碍间隙（11）中的压力平衡和/或气体流动横向（5）。

5. 发明授权

US08718989B2 Method to determine the internal structure of a heat conducting body 有权
标题翻译：确定导热体内部结构的方法
公开(公告)号：US08718989B2
公开(公告)日：2014-05-06
申请号：US11429954
申请日：2006-05-09
申请人： Andrew Clifton , Martin Schnieder , Chiara Zambetti
发明人： Andrew Clifton , Martin Schnieder , Chiara Zambetti
IPC分类号： G06F17/50
CPC分类号： G01K1/02 , G01K3/14 , G01K17/00 , G01N25/72
摘要： In a non-destructive method for determining the internal structure of a heat conducting body, such as a cooling structure of a turbine blade, a flow medium is passed through the internal structure and the resultant thermal image on an external surface of the body is registered using a pixelised thermal image detector. Heat transfer coefficients and wall thicknesses of the internal structure are determined by means of a 1-,2-, or 3-dimensional inverse method that includes the numerical modelling of the surface temperatures using initial values for heat transfer coefficients and wall thicknesses and an optimization of the values using an iteration method. In a special variant of the method, the spatial geometry of the internal structure of the body is determined by means of the same inverse method and a geometry model that is optimised by iteration. No prior knowledge of the internal geometry is required.
摘要翻译：在用于确定诸如涡轮叶片的冷却结构的导热体的内部结构的非破坏性方法中，使流动介质通过内部结构，并且在身体的外表面上记录所得的热图像使用像素化热图像检测器。内部结构的传热系数和壁厚通过1，2或3维逆方法确定，其中包括使用传热系数和壁厚的初始值的表面温度的数值模拟和优化的值使用迭代方法。在该方法的特殊变型中，通过相同的逆方法和通过迭代优化的几何模型来确定身体的内部结构的空间几何。不需要内部几何的先验知识。

6. 发明授权

US08801366B2 Stator blade for a gas turbine and gas turbine having same 有权
标题翻译：具有相同燃气轮机和燃气轮机的定子叶片
公开(公告)号：US08801366B2
公开(公告)日：2014-08-12
申请号：US12892423
申请日：2010-09-28
申请人： Roland Dueckershoff , Shailendra Naik , Martin Schnieder
发明人： Roland Dueckershoff , Shailendra Naik , Martin Schnieder
IPC分类号： F01D9/02 , F01D9/04 , F01D5/18
CPC分类号： F01D5/187 , F01D9/041 , F05D2220/3215 , F05D2250/185 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A stator blade for a gas turbine with sequential combustion, has a blade airfoil which extends in the radial direction between a blade tip and a shroud, with cooling passages extending inside the blade airfoil, through which a cooling medium can flow for cooling the blade and can then discharge from the stator blade into the hot gas flow flowing through the turbine. The blade airfoil has a sharply curved shape in space in the radial direction, and three cooling passages, which extend in the radial direction, arranged inside the blade airfoil in series in the hot gas flow direction and are interconnected by deflection regions, which are arranged at ends of the blade airfoil, so that the cooling medium flows through the cooling passages one after the other, with change of direction. The cooling passages follow the curvature of the blade airfoil in space in the radial direction.
摘要翻译：一种用于具有顺序燃烧的燃气轮机的定子叶片具有在叶片尖端和护罩之间沿径向方向延伸的叶片翼型件，其中在叶片翼型内部延伸有冷却通道，冷却介质可通过该叶片气流流动以冷却叶片，然后可以从定子叶片排出流入流经涡轮的热气流。叶片翼型件在径向空间中具有急剧弯曲的形状，并且在径向方向上延伸的三个冷却通道在热气流方向上串联布置在叶片翼型内部并且通过偏转区域相互连接，偏转区域被布置在叶片翼型的端部处，使得冷却介质随着方向的改变一个接一个地流过冷却通道。冷却通道在径向方向上沿着空间中的叶片翼型的曲率。

7. 发明授权

US09062555B2 Gas turbine blade and method for producing a blade 有权
标题翻译：燃气轮机叶片及其制造方法
公开(公告)号：US09062555B2
公开(公告)日：2015-06-23
申请号：US13528013
申请日：2012-06-20
申请人： Martin Schnieder , Jörg Krückels
发明人： Martin Schnieder , Jörg Krückels
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/202 , F05D2260/22141 , Y10T29/49341
摘要： A blade (10) for a gas turbine has a blade airfoil (11), the blade wall (18) of which encloses an interior space (17). For cooling the blade wall (18), the blade wall (18) includes a cooling arrangement (19) which has a radial passage (20) extending in the longitudinal direction of the blade and from which a multiplicity of cooling passages (21, 22), extending in the blade wall (18), branch in the transverse direction, and from which a multiplicity of film-cooling holes (23) are led to the outside in the transverse direction. Particularly efficient cooling is made possible by the distribution of the film-cooling holes (23) along the radial passage (20) being selected independently of the distribution of the cooling passages (21, 22) along the radial passage (20).
摘要翻译：用于燃气涡轮机的叶片（10）具有叶片翼型件（11），其叶片壁（18）包围内部空间（17）。为了冷却叶片壁（18），叶片壁（18）包括冷却装置（19），该冷却装置具有在叶片的纵向方向上延伸的径向通道（20），多个冷却通道（21,22 ）在叶片壁（18）中延伸，在横向方向上分支，多个薄膜冷却孔（23）从该横向方向被引导到外部。通过沿着径向通道（20）分配不同于冷却通道（21,22）的分配的径向通道（20）分布薄膜冷却孔（23），可以实现特别有效的冷却。

8. 发明申请

US20130017064A1 GAS TURBINE AIRFOIL WITH SHAPED TRAILING EDGE COOLANT EJECTION HOLES 有权
标题翻译：气体涡轮机空气带有形状的跟踪边缘冷却液喷射孔
公开(公告)号：US20130017064A1
公开(公告)日：2013-01-17
申请号：US13622055
申请日：2012-09-18
申请人： Shailendra Naik , Martin Schnieder
发明人： Shailendra Naik , Martin Schnieder
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/304
摘要： A turbine blade or vane includes at least one internal radial channel for the circulation of cooling medium bordered on a pressure side by a pressure side wall and on a suction side by a suction side wall joined at a upstream side at a leading edge and at and downstream side at the trailing edge. At least one exit hole extends through at least one of the pressure side wall or the suction side wall for blowing out of cooling medium from the internal radial channel to a medium surrounding the blade or vane. At least one trailing edge exit hole along the trailing edge has a surfacial exit opening disposed at the pressure side of the trailing edge.
摘要翻译：涡轮机叶片或叶片包括至少一个内部径向通道，用于通过压力侧壁在压力侧上界定并在吸力侧通过在前缘和上方的上游侧连接的吸力侧壁循环冷却介质，在后缘的下游侧。至少一个出口孔延伸穿过压力侧壁或吸力侧壁中的至少一个，用于将冷却介质从内部径向通道吹出到围绕叶片或叶片的介质。沿着后缘的至少一个后缘出口孔具有设置在后缘的压力侧的表面出口。

9. 发明申请

US20130004332A1 GAS TURBINE BLADE AND METHOD FOR PRODUCING A BLADE 有权
标题翻译：气体涡轮叶片及其制造方法
公开(公告)号：US20130004332A1
公开(公告)日：2013-01-03
申请号：US13528013
申请日：2012-06-20
申请人： Martin Schnieder , Jörg Krückels
发明人： Martin Schnieder , Jörg Krückels
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/202 , F05D2260/22141 , Y10T29/49341
摘要： A blade (10) for a gas turbine has a blade airfoil (11), the blade wall (18) of which encloses an interior space (17). For cooling the blade wall (18), the blade wall (18) includes a cooling arrangement (19) which has a radial passage (20) extending in the longitudinal direction of the blade and from which a multiplicity of cooling passages (21, 22), extending in the blade wall (18), branch in the transverse direction, and from which a multiplicity of film-cooling holes (23) are led to the outside in the transverse direction. Particularly efficient cooling is made possible by the distribution of the film-cooling holes (23) along the radial passage (20) being selected independently of the distribution of the cooling passages (21, 22) along the radial passage (20).
摘要翻译：用于燃气涡轮机的叶片（10）具有叶片翼型件（11），其叶片壁（18）包围内部空间（17）。为了冷却叶片壁（18），叶片壁（18）包括冷却装置（19），该冷却装置具有在叶片的纵向方向上延伸的径向通道（20），多个冷却通道（21,22 ）在叶片壁（18）中延伸，在横向方向上分支，多个薄膜冷却孔（23）从该横向方向被引导到外部。通过沿着径向通道（20）分配不同于冷却通道（21,22）的分配的径向通道（20）分布薄膜冷却孔（23），可以实现特别有效的冷却。

10. 发明授权

US09097118B2 Transitional region for a combustion chamber of a gas turbine 有权
标题翻译：燃气轮机燃烧室的过渡区域
公开(公告)号：US09097118B2
公开(公告)日：2015-08-04
申请号：US13226020
申请日：2011-09-06
申请人： Martin Schnieder , Jörg Krückels , Uwe Rüdel , Christoph Appel , Urs Benz
发明人： Martin Schnieder , Jörg Krückels , Uwe Rüdel , Christoph Appel , Urs Benz
IPC分类号： F02C7/24 , F23R3/04 , F01D9/02 , F23R3/00
CPC分类号： F01D9/023 , F02C7/24 , F23R3/002 , F23R3/007 , F23R2900/00005 , F23R2900/03042 , Y02T50/67 , Y02T50/675
摘要： A gas turbine including a combustion chamber and a first row of guide vanes, arranged essentially directly downstream thereof, of a turbine. The outer and/or inner limitation of the combustion chamber defined by at least one outer and/or inner heat shield, mounted on at least one combustion chamber structure arranged radially outside and/or inside. The hot gases flow path in the region of the guide vane row being restricted radially on the outside and/or inside by an outer and/or inner vane platform, mounted at least indirectly on at least one turbine carrier. A minimal gap size directly upstream of the first row of guide vanes is achieved by mounting at least indirectly on the turbine carrier at least one mini heat shield, arranged upstream of the first row of guide vanes and essentially adjacent the vane platform and in the flow direction between the heat shield and the vane platform.
摘要翻译：一种燃气轮机，包括燃烧室和第一排导叶，基本上直接布置在涡轮的下游。由至少一个外部和/或内部热屏蔽限定的燃烧室的外部和/或内部限制，其安装在径向外侧和/或内部布置的至少一个燃烧室结构上。引导叶片排的区域中的热气体流动通道至少间接地安装在至少一个涡轮机载体上的外部和/或内部叶片平台的外侧和/或内部径向限制。通过至少间接地安装在涡轮机载体上至少一个微型隔热罩来实现第一排导叶直接上游的最小间隙尺寸，其布置在第一排导叶的上游并且基本上邻近叶片平台和流体隔热板和叶片平台之间的方向。

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