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1. 发明申请

US20060177310A1 Cooled blade or vane for a gas turbine 有权
标题翻译：用于燃气轮机的冷却叶片或叶片
公开(公告)号：US20060177310A1
公开(公告)日：2006-08-10
申请号：US11330268
申请日：2006-01-12
申请人： Shailendra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
发明人： Shailendra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D25/12 , F05D2250/185 , F05D2260/211
摘要： A cooled blade or vane for a gas turbine has a main blade or vane part which starts from a blade or vane root and a blade or vane shank and has a leading edge and a trailing edge, as well as, inside the main blade or vane part, a plurality of cooling ducts, which extend in the radial direction, are connected in series in terms of flow and of which a first cooling duct has a main stream of a cooling medium flowing through it along the leading edge. A second cooling duct has a main stream of a cooling medium flowing through it along the trailing edge, from the blade or vane root to the tip of the main blade or vane part. The outlet of the first cooling duct is in communication, via a first diverting region, a third cooling duct arranged between the first and second cooling ducts, and a second diverting region, with the inlet of the second cooling duct.
摘要翻译：用于燃气轮机的冷却的叶片或叶片具有从叶片或叶片根部以及叶片或叶片柄开始并具有前缘和后缘以及主叶片或叶片内的主叶片或叶片部分部分，沿径向方向延伸的多个冷却管道以流动方式串联连接，并且第一冷却管道具有沿着前缘流过其中的冷却介质的主流。第二冷却管道具有沿着后缘从叶片或叶片根部流到主叶片或叶片部分的尖端的冷却介质的主流。第一冷却管道的出口经由第一转向区域与布置在第一和第二冷却管道之间的第三冷却管道与第二冷却管道的入口与第二转向区域连通。

2. 发明授权

US07264445B2 Cooled blade or vane for a gas turbine 有权
标题翻译：用于燃气轮机的冷却叶片或叶片
公开(公告)号：US07264445B2
公开(公告)日：2007-09-04
申请号：US11330268
申请日：2006-01-12
申请人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
发明人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D25/12 , F05D2250/185 , F05D2260/211
摘要： A cooled blade or vane for a gas turbine has a main blade or vane part which starts from a blade or vane root and a blade or vane shank and has a leading edge and a trailing edge, as well as, inside the main blade or vane part, a plurality of cooling ducts, which extend in the radial direction, are connected in series in terms of flow and of which a first cooling duct has a main stream of a cooling medium flowing through it along the leading edge. A second cooling duct has a main stream of a cooling medium flowing through it along the trailing edge, from the blade or vane root to the tip of the main blade or vane part. The outlet of the first cooling duct is in communication, via a first diverting region, a third cooling duct arranged between the first and second cooling ducts, and a second diverting region, with the inlet of the second cooling duct.
摘要翻译：用于燃气轮机的冷却的叶片或叶片具有从叶片或叶片根部以及叶片或叶片柄开始并具有前缘和后缘以及主叶片或叶片内的主叶片或叶片部分部分，沿径向方向延伸的多个冷却管道以流动方式串联连接，并且第一冷却管道具有沿着前缘流过其中的冷却介质的主流。第二冷却管道具有沿着后缘从叶片或叶片根部流到主叶片或叶片部分的尖端的冷却介质的主流。第一冷却管道的出口经由第一转向区域与布置在第一和第二冷却管道之间的第三冷却管道与第二冷却管道的入口与第二转向区域连通。

3. 发明申请

US20060292006A1 Cooled blade for a gas turbine 有权
公开(公告)号：US20060292006A1
公开(公告)日：2006-12-28
申请号：US11483091
申请日：2006-07-10
申请人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
发明人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/081 , F05D2250/50 , F05D2260/205 , F05D2260/221
摘要： A cooled blade for a gas turbine has a blade airfoil, which emerges from a blade root and a blade shank and has a leading edge and a trailing edge and, within the blade airfoil, a plurality of sequential coolant ducts, in terms of flow, extending in a radial direction. A first coolant duct along the leading edge, and a second coolant duct along the trailing edge, have a main flow of a coolant flowing through them from the blade root to the tip of the blade airfoil. An inlet of the first coolant duct is in connection with a main coolant inlet, and an outlet of the first coolant duct is in connection with the inlet to the second coolant duct via a first deflection region. A third coolant duct is arranged between the first and the second coolant duct and a second deflection region. An additional flow of cooler coolant provided from outside is added from the third coolant duct into the heated main flow of the coolant flowing into the second coolant duct. An orifice can, for example, extend from the main coolant inlet to the second deflection region.

4. 发明授权

US07520724B2 Cooled blade for a gas turbine 有权
标题翻译：用于燃气轮机的冷却叶片
公开(公告)号：US07520724B2
公开(公告)日：2009-04-21
申请号：US11483091
申请日：2006-07-10
申请人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
发明人： Shailandra Naik , Sacha Parneix , Ulrich Rathmann , Helene Saxer-Felici , Stefan Schlechtriem , Beat Von Arx
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/081 , F05D2250/50 , F05D2260/205 , F05D2260/221
摘要： A cooled blade for a gas turbine has a blade airfoil, which emerges from a blade root and a blade shank and has a leading edge and a trailing edge and, within the blade airfoil, a plurality of sequential coolant ducts, in terms of flow, extending in a radial direction. A first coolant duct along the leading edge, and a second coolant duct along the trailing edge, have a main flow of a coolant flowing through them from the blade root to the tip of the blade airfoil. An inlet of the first coolant duct is in connection with a main coolant inlet, and an outlet of the first coolant duct is in connection with the inlet to the second coolant duct via a first deflection region. A third coolant duct is arranged between the first and the second coolant duct and a second deflection region. An additional flow of cooler coolant provided from outside is added from the third coolant duct into the heated main flow of the coolant flowing into the second coolant duct. An orifice can, for example, extend from the main coolant inlet to the second deflection region.
摘要翻译：用于燃气涡轮机的冷却叶片具有叶片翼型件，叶片翼型件从叶片根部和叶片柄部突出并且具有前缘和后缘，并且在叶片翼型件内，在流动方面，多个顺序的冷却剂管道，沿径向延伸。沿着前缘的第一冷却剂管道和沿着后缘的第二冷却剂管道具有从叶片根部到叶片翼型的尖端流过它们的冷却剂的主流。第一冷却剂管道的入口与主冷却剂入口连接，并且第一冷却剂管道的出口经由第一偏转区域与第二冷却剂管道的入口连接。第三冷却剂管道布置在第一和第二冷却剂管道和第二偏转区域之间。从外部提供的另外冷却剂冷却流从第三冷却剂管道加入流入第二冷却剂管道的冷却剂的加热主流。孔可以例如从主冷却剂入口延伸到第二偏转区域。

5. 发明授权

US07104751B2 Hot gas path assembly 有权
标题翻译：热气路组装
公开(公告)号：US07104751B2
公开(公告)日：2006-09-12
申请号：US10865749
申请日：2004-06-14
申请人： Shailendra Naik , Ulrich Rathmann
发明人： Shailendra Naik , Ulrich Rathmann
IPC分类号： F01D11/12 , F01D11/10
CPC分类号： F01D11/127 , F01D11/10 , F01D25/12 , F05D2260/201 , F05D2300/612
摘要： A hot gas path assembly, suitable for use in the hot gas path of a gas turbine, has as a hot gas duct wall an impact-cooled gas-impermeable element and a transpiration-cooled gas permeable element. The gas-permeable element is a run-on covering for the sealing tip, and the gas-impermeable element is a blade foot of a turbine blade. Coolant is led in series through an impact-cooling element to cool the gas-impermeable element, and through the gas-permeable element for transpiration cooling and, if appropriate, also cools the sealing tip. Coolant thus is utilized particularly efficiently. Subdividing walls are arranged for the lateral subdivision of the coolant path, particularly in the circumferential direction, into segments. Because of the subdivision, in the event of damage to the gas-permeable element in one segment, the other segments remain essentially uninfluenced. Redundant cooling orifices may ensure coolant flow even when flow resistance in a transpiration-cooled element rises.
摘要翻译：适用于燃气轮机的热气路径的热气路组件具有作为热气管道壁的冲击冷却气体不可渗透元件和蒸发冷却气体可渗透元件。透气元件是用于密封末端的随动覆盖物，气体不可渗透元件是涡轮叶片的叶片脚。冷却剂通过冲击冷却元件串联引导，以冷却气体不可渗透元件，并通过透气元件进行蒸发冷却，并且如果合适也冷却密封末端。因此，冷却剂被特别有效地利用。布置细分壁，用于将冷却剂路径的侧向细分，特别是在圆周方向上分成段。由于细分，在一个部分的气体可渗透元件损坏的情况下，其他部分基本上不受影响。冗余冷却孔可以确保冷却剂流动，即使蒸发冷却元件中的流动阻力上升。

6. 发明授权

US07077622B2 Emergency cooling system for a thermally loaded component 失效
标题翻译：用于热负荷组件的紧急冷却系统
公开(公告)号：US07077622B2
公开(公告)日：2006-07-18
申请号：US10694738
申请日：2003-10-29
申请人： Jan Ehrhard , Maxim Konter , Shailendra Naik , Ulrich Rathmann
发明人： Jan Ehrhard , Maxim Konter , Shailendra Naik , Ulrich Rathmann
IPC分类号： F01D21/12
CPC分类号： F01D25/12 , F01D5/18 , F01D5/186 , F05D2260/202 , F23R3/005
摘要： In an emergency cooling system (17) for a component (1) which is subject to thermal load in operation, in, e.g., a turbine, the component (1) has a wall (3) which, in operation, is acted on by heat on a first wall side (14) and is acted on by a flow of cooling fluid (11) on a second wall side (15). The wall (3) has at least one emergency cooling opening (12) which is closed off by a plug (16) and through which cooling fluid flows from the second wall side (15) to the first wall side (14) when the plug (16) is absent. The plug (16) is designed so as to melt at a predetermined temperature. The plug (16) is a body which is produced separately from the component (1), the plug (16) being inserted into the emergency cooling opening (12), in which it is connected to the component (1).
摘要翻译：在用于在运行中经受热负荷的部件（1）的紧急冷却系统（17）中，例如在涡轮机中，部件（1）具有壁（3），其在操作中由在第一壁侧（14）上的热量被第二壁侧（15）上的冷却流体（11）流动。所述壁（3）具有至少一个紧急冷却开口（12），所述紧急冷却开口（12）由所述塞子（16）封闭，并且当所述塞子（16）从所述第二壁侧（15）流动到所述第一壁侧（16）不存在。插头（16）设计成在预定温度下熔化。插头（16）是与部件（1）分开制造的主体，插头插入紧急冷却开口（12）中，连接到部件（1）。

7. 发明授权

US06499944B1 Turbo machine 有权
标题翻译：涡轮机
公开(公告)号：US06499944B1
公开(公告)日：2002-12-31
申请号：US09657304
申请日：2000-09-07
申请人： Alexander Beeck , Peter Ernst , Shailendra Naik , Ulrich Rathmann
发明人： Alexander Beeck , Peter Ernst , Shailendra Naik , Ulrich Rathmann
IPC分类号： F01D520
CPC分类号： F01D11/127 , F05D2250/28 , F05D2260/20
摘要： A heat shield of a turbo machine is provided with a microstructure. In a preferred embodiment, the microstructure element comprises a plateau, which is arranged on a rib in such a way that the structure has a “T”-shaped cross section. The ribs are preferably embodied as plates set on edge on the heat shield and are aligned with their surface perpendicular to the circumferential direction (U) of the turbo machine. This results in low bending dimensional rigidity in the circumferential direction. In this way, it is possible to accommodate scraping of a component involved in relative motion in the circumferential direction without plastic deformation. Moreover this arrangement gives the maximum possible resistance to a leakage flow. When used at high temperatures, it is furthermore advantageous to provide ways to enable a coolant to be supplied to the microstructure.
摘要翻译：涡轮机的隔热罩具有微结构。在优选实施例中，微结构元件包括平台，其以这样的方式布置在肋上，使得该结构具有“T”形横截面。肋优选地实施为设置在隔热板上的边缘上的板并且与其垂直于涡轮机的圆周方向（U）的表面对齐。这导致圆周方向的弯曲尺寸刚度低。以这种方式，可以容纳在圆周方向上涉及相对运动的部件的刮擦而没有塑性变形。此外，这种布置给出了泄漏流量的最大可能的阻力。当在高温下使用时，还有利的是提供使冷却剂能够供应到微结构的方式。

8. 发明授权

US06712581B2 Process for producing a groove-like recess, and a groove-like recess of this type 有权
标题翻译：用于制造这种凹槽的凹槽的方法和这种槽状凹槽
公开(公告)号：US06712581B2
公开(公告)日：2004-03-30
申请号：US10219323
申请日：2002-08-16
申请人： Stefan Florjancic , Ulrich Rathmann
发明人： Stefan Florjancic , Ulrich Rathmann
IPC分类号： F01D1100
CPC分类号： F01D11/005 , B23P13/00 , Y10T29/49995
摘要： A process for producing a groove-like recess which is part of a strip seal between two components which enclose a gap, uses a material-removing process technology to create the groove-like recess in the two components in such a manner that the groove-like recess in each of the two components, after orientation with respect to one another, lie substantially opposite one another in an end position in which they enclose the gap between them, and that a strip element can be introduced into the groove-like recesses in such a manner that the strip element at least partially projects into both groove-like recesses and, under the action of a force, forms a substantially gastight joint with the groove-like recesses in the two components. Furthermore, a groove-like recess of this type is part of a strip seal.
摘要翻译：用于制造作为封闭间隙的两个部件之间的带状密封件的一部分的凹槽状凹部的方法使用材料去除工艺技术以这样的方式在两个部件中形成凹槽状凹部，在两个部件中的每一个中，在彼此相对定向之后，在其中包围它们之间的间隙的端部位置处基本上彼此相对，并且可以将带状元件引入槽状凹部中这种方式使得带状元件至少部分地突出到两个凹槽状的凹部中，并且在力的作用下，与两个部件中的槽状凹部形成基本上气密的接头。此外，这种类型的槽状凹部是带状密封件的一部分。

9. 发明授权

US06575698B2 Sealing of a thermal turbomachine 失效
标题翻译：密封热涡轮机
公开(公告)号：US06575698B2
公开(公告)日：2003-06-10
申请号：US09897477
申请日：2001-07-03
申请人： Alexander Beeck , Ulrich Rathmann , Hans E. Wettstein
发明人： Alexander Beeck , Ulrich Rathmann , Hans E. Wettstein
IPC分类号： F01D1108
CPC分类号： F01D11/127 , F05D2250/283
摘要： A honeycomb structure is arranged on a stator of a gas turbine and is arranged opposite the moving blades of the gas turbine. The honeycomb structure is composed of metal sheets in such a way that webs having double the sheet thickness are obtained and connections of single thickness are obtained between the webs. The angle &agr; between the circumferential direction of the stator and the webs of double thickness is 5° to 175°. This serves to avoid undesirable efforts such as, for example, overheating during friction at the honeycomb structure of the moving blades of the gas turbine.
摘要翻译：蜂窝结构设置在燃气轮机的定子上并与燃气轮机的动叶片相对设置。蜂窝结构由金属板构成，从而获得双层厚度的纤维网，并且在幅材之间获得单一厚度的连接。定子的圆周方向与双层厚度的腹板之间的角度α为5°至175°。这用于避免不期望的努力，例如在燃气轮机的动叶片的蜂窝结构处的摩擦期间过热。

10. 发明授权

US08534675B2 Strip seal and method for designing a strip seal 有权
标题翻译：带状密封和设计带状密封的方法
公开(公告)号：US08534675B2
公开(公告)日：2013-09-17
申请号：US12694765
申请日：2010-01-27
申请人： Thomas Heinz-Schwarzmaier , Ulrich Steiger , Ulrich Rathmann
发明人： Thomas Heinz-Schwarzmaier , Ulrich Steiger , Ulrich Rathmann
IPC分类号： F16J3/00
CPC分类号： F01D11/005 , F01D25/04 , F05D2240/11 , F05D2240/57 , F05D2260/96 , F05D2300/501
摘要： A strip seal and method of configuration thereof for sealing two adjacent non-rotating gas turbine hot gas components exposed to pressure pulsations. The strip seal has at least two clamping projections distributed along discrete points of the strip seal length that extend out from a pressure face of the strip seal. The location of the projections are defined by two ratios. The first ratio, of less than 25, is the strip seal length extending free of clamping projections from any one of the ends of the strip seal to a clamping projection to the ratio of strip seal thickness. The second ratio, of less than 200, is the ratio of the strip seal length extending free of clamping projections between any two projections to the thickness of the strip seal. This seal arrangement ameliorates detrimental effects of induced resonance.
摘要翻译：一种带状密封件及其构造方法，用于密封暴露于压力脉动的两个相邻的非旋转燃气轮机热气体组件。带状密封件具有沿带状密封件长度的离散点分布的至少两个夹紧突起，其从带状密封件的压力表面延伸出来。突起的位置由两个比例定义。小于25的第一比率是从带状密封件的任何一个端部延伸到没有夹紧突起的条形密封长度到夹紧突起到条形密封件厚度的比率。小于200的第二比率是在任何两个突起之间没有夹紧突起的条形密封长度与带状密封件的厚度之间的比率。该密封装置改善了诱导共振的有害影响。

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