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1. 发明申请

US20050076622A1 Device for separating dust and filth in flowing media 有权
标题翻译：用于分离流动介质中灰尘和污物的装置
公开(公告)号：US20050076622A1
公开(公告)日：2005-04-14
申请号：US10495227
申请日：2002-11-08
申请人： Gordon Anderson , Reinhard Fried , Shailendra Naik , Stefan Schlechtriem , Thomas Zierer
发明人： Gordon Anderson , Reinhard Fried , Shailendra Naik , Stefan Schlechtriem , Thomas Zierer
IPC分类号： B01D45/16 , B01D50/00
CPC分类号： B01D45/16 , B01D50/002
摘要： The invention describes a device for separating dust and dirt out of flowing media. A curved flow path (1) is imposed on the flow (21), and heavy foreign bodies are separated out of the main flow by centrifugal force. The partial stream required to carry away the foreign bodies is aftertreated in a filter (11) and returned in purified form. Unlike with conventional filters, which have to process the entire flow of media, pressure losses during the separation of dust are minimized, and on the other hand no medium is lost for removing the dust load.
摘要翻译：本发明描述了一种用于从流动介质中分离灰尘和污垢的装置。在流动（21）上施加弯曲的流动路径（1），并且通过离心力将重的异物分离出主流体。携带异物所需的部分流在过滤器（11）中进行后处理，并以纯化的形式返回。与必须处理整个介质流的常规过滤器不同，在分离灰尘期间的压力损失最小化，另一方面不会丢失用于去除灰尘负载的介质。

2. 发明授权

US07311741B2 Device for separating dust and dirt out of flowing media 有权
标题翻译：用于从流动介质中分离灰尘和污物的装置
公开(公告)号：US07311741B2
公开(公告)日：2007-12-25
申请号：US10495227
申请日：2002-11-08
申请人： Gordon Anderson , Reinhard Fried , Shailendra Naik , Stefan Schlechtriem , Thomas Zierer
发明人： Gordon Anderson , Reinhard Fried , Shailendra Naik , Stefan Schlechtriem , Thomas Zierer
IPC分类号： B01D45/12
CPC分类号： B01D45/16 , B01D50/002
摘要： The invention describes a device for separating dust and dirt out of flowing media. A curved flow path (1) is imposed on the flow (21), and heavy foreign bodies are separated out of the main flow by centrifugal force. The partial stream required to carry away the foreign bodies is aftertreated in a filter (11) and returned in purified form. Unlike with conventional filters, which have to process the entire flow of media, pressure losses during the separation of dust are minimized, and on the other hand no medium is lost for removing the dust load.
摘要翻译：本发明描述了一种用于从流动介质中分离灰尘和污垢的装置。在流动（21）上施加弯曲的流动路径（1），并且通过离心力将重的异物分离出主流体。携带异物所需的部分流在过滤器（11）中进行后处理，并以纯化的形式返回。与必须处理整个介质流的常规过滤器不同，在分离灰尘期间的压力损失最小化，另一方面不会丢失用于去除灰尘负载的介质。

3. 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。

4. 发明授权

US06435256B1 Method for producing a cooled, lost-wax cast part 有权
标题翻译：冷却失蜡铸件的制造方法
公开(公告)号：US06435256B1
公开(公告)日：2002-08-20
申请号：US09921587
申请日：2001-08-06
申请人： Gordon Anderson , Peter Marx , Shailendra Naik
发明人： Gordon Anderson , Peter Marx , Shailendra Naik
IPC分类号： B22C924
CPC分类号： B22C9/04 , B22C7/02 , Y10T29/49336 , Y10T29/49989
摘要： The invention relates to a method for producing a cooled cast part for a thermal turbo machine by using a known casting process. Between a wax model of the cast part and a ceramic core, a wax seal is applied by hand above a step, only on an additional shoulder. The material that is created during the casting process at this point by the shoulder and the wax seal can be ground off without causing rough areas on the step to form. This simplifies the welding or soldering of a cooling plate to the step.
摘要翻译：本发明涉及一种通过使用已知的铸造工艺生产用于热式涡轮增压机的冷却铸造件的方法。在浇铸部件的蜡模型和陶瓷芯之间，手工将蜡密封件施加在台阶上，仅在额外的肩上。通过肩部和蜡密封件在此刻的铸造过程中产生的材料可以被磨掉而不会形成台阶上的粗糙区域。这简化了冷却板对台阶的焊接或焊接。

5. 发明授权

US09051838B2 Turbine blade 有权
标题翻译：涡轮叶片
公开(公告)号：US09051838B2
公开(公告)日：2015-06-09
申请号：US13330919
申请日：2011-12-20
申请人： Brian Kenneth Wardle , Christoph Didion , Herbert Brandl , Shailendra Naik
发明人： Brian Kenneth Wardle , Christoph Didion , Herbert Brandl , Shailendra Naik
IPC分类号： F01D5/08 , F01D5/18
CPC分类号： F01D5/081 , F01D5/087 , F01D5/188 , Y10T29/49341
摘要： A turbine blade of an axial turbine includes internal cooling fluid passages with radially outwardly extending passages connected to holes in the blade root. The holes are generally core printouts providing stability to the core during the casting process, but are not needed and need to be closed to guarantee the functioning of the cooling system. This is achieved by at least one covering plate. The plate is held by at least two slots located at the root of the turbine blade. Thus, the supply holes for cooling fluid located at the root section are closed by a simple mechanical device, e.g., a plate that does not require any subsequent brazing/welding operations. In addition, the plate is removable to facilitate inspection/cleaning, or further processing of the blade at service intervals.
摘要翻译：轴向涡轮机的涡轮机叶片包括内部冷却流体通道，其具有连接到叶片根部中的孔的径向向外延伸的通道。这些孔通常是在铸造过程中提供对芯的稳定性的核心打印输出，但是不需要并且需要关闭以保证冷却系统的功能。这通过至少一个覆盖板来实现。该板由位于涡轮叶片根部处的至少两个槽保持。因此，位于根部处的用于冷却流体的供应孔由简单的机械装置例如不需要随后的钎焊/焊接操作的板封闭。此外，该板是可拆卸的，以方便检查/清洁，或在维修间隔进一步处理叶片。

6. 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。

7. 发明申请

US20120163995A1 TURBINE BLADE 有权
标题翻译：涡轮叶片
公开(公告)号：US20120163995A1
公开(公告)日：2012-06-28
申请号：US13330919
申请日：2011-12-20
申请人： Brian Kenneth Wardle , Christoph Didion , Herbert Brandl , Shailendra Naik
发明人： Brian Kenneth Wardle , Christoph Didion , Herbert Brandl , Shailendra Naik
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/081 , F01D5/087 , F01D5/188 , Y10T29/49341
摘要： A turbine blade of an axial turbine includes internal cooling fluid passages with radially outwardly extending passages connected to holes in the blade root. The holes are generally core printouts providing stability to the core during the casting process, but are not needed and need to be closed to guarantee the functioning of the cooling system. This is achieved by at least one covering plate. The plate is held by at least two slots located at the root of the turbine blade. Thus, the supply holes for cooling fluid located at the root section are closed by a simple mechanical device, e.g., a plate that does not require any subsequent brazing/welding operations. In addition, the plate is removable to facilitate inspection/cleaning, or further processing of the blade at service intervals.
摘要翻译：轴向涡轮机的涡轮机叶片包括内部冷却流体通道，其具有连接到叶片根部中的孔的径向向外延伸的通道。这些孔通常是在铸造过程中提供对芯的稳定性的核心打印输出，但是不需要并且需要关闭以保证冷却系统的功能。这通过至少一个覆盖板来实现。该板由位于涡轮叶片根部处的至少两个槽保持。因此，位于根部处的用于冷却流体的供应孔通过简单的机械装置例如不需要随后的钎焊/焊接操作的板来封闭。此外，该板是可拆卸的，以方便检查/清洁，或在维修间隔进一步处理叶片。

8. 发明申请

US20080095622A1 Gas Turbine Airfoil With Leading Edge Cooling 有权
标题翻译：具有前沿冷却功能的燃气轮机翼型
公开(公告)号：US20080095622A1
公开(公告)日：2008-04-24
申请号：US11838960
申请日：2007-08-15
申请人： Shailendra Naik , Gregory Vogel
发明人： Shailendra Naik , Gregory Vogel
IPC分类号： F01D5/08
CPC分类号： F01D5/186 , F05D2240/121 , F05D2240/303 , F05D2250/314 , Y10T29/49341
摘要： A gas turbine airfoil (1) includes a pressure sidewall (15) and a suction sidewall (16), extending from a root to a tip and from a leading edge region to a trailing edge and having at least one cooling passage between the pressure sidewall (15) and the suction sidewall (16) for cooling air to pass through and cool the airfoil from within. One or several of the cooling passages (3) extend along the leading edge of the airfoil (1) and several film cooling holes (1,2) extend from the internal cooling passages (3) along the leading edge region to the outer surface of the leading edge region. The film cooling holes (1,2) each have a shape that is diffused in a radial outward direction of the leading edge of the airfoil (1) at least over a part of the length of the film cooling hole (1,2). Improved cooling in the leading edge region can be achieved because the cooling holes (1, 2) have a principal axis (17), and the shape is asymmetrically diffused in that it is diffused in the radial outward direction from the principal axis (17) along a forward inclination axis (20), and it is additionally diffused in a second lateral direction from the principal axis (17) along a lateral inclination axis (21).
摘要翻译：燃气涡轮机翼型件（1）包括压力侧壁（15）和吸力侧壁（16），其从根部延伸到尖端并且从前缘区域延伸到后缘，并且在压力侧壁之间具有至少一个冷却通道（15）和吸入侧壁（16），用于冷却空气以从内部通过并冷却翼型件。一个或几个冷却通道（3）沿着翼型件（1）的前缘延伸，并且多个膜冷却孔（1,2）从内部冷却通道（3）沿着前缘区域延伸到前沿区域。薄膜冷却孔（1,2）各自具有在薄膜冷却孔（1,2）的长度的至少一部分上在翼型件（1）的前缘的径向向外方向上扩散的形状。由于冷却孔（1,2）具有主轴（17），并且形状不对称扩散，因此从主轴线（17）沿径向向外的方向扩散，可以实现前缘区域的改进的冷却，沿着前倾斜轴线（20），并且沿着横向倾斜轴线（21）从主轴线（17）另外沿第二横向方向扩散。

9. 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。

10. 发明申请

US20120070308A1 COOLED BLADE FOR A GAS TURBINE 审中-公开
标题翻译：用于气体涡轮的冷却叶片
公开(公告)号：US20120070308A1
公开(公告)日：2012-03-22
申请号：US13234592
申请日：2011-09-16
申请人： Shailendra Naik , Gaurav Pathak
发明人： Shailendra Naik , Gaurav Pathak
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05D2240/307 , F05D2250/231 , F05D2250/232 , F05D2260/20 , F05D2260/202
摘要： A cooled blade for a gas turbine includes an airfoil section which extends in the radial direction of the turbine or in the longitudinal direction of the blade between a platform and a blade tip which is provided with a cap. The airfoil section is bounded transversely with respect to the longitudinal direction by a leading edge and a trailing edge and has a pressure face and a suction face. Cooling channels extend in a radial direction between the platform and the blade tip in an interior of the airfoil section. The cooling channels can be acted upon by a cooling air flow from the platform. The blade tip is cooled by first cooling holes for convection cooling provided on the pressure face of the blade, and second cooling holes for film cooling provided on the suction side of the blade, through the cap of the blade, in the blade tip from the cooling channels, and distributed over the blade width.
摘要翻译：用于燃气轮机的冷却叶片包括翼型部分，其在涡轮机的径向方向上或在叶片的纵向方向上在平台和设置有盖的叶片尖端之间延伸。翼型部分通过前缘和后缘相对于纵向方向横向限定，并具有压力面和吸力面。冷却通道在翼型部分的内部中在平台和叶片尖端之间的径向方向上延伸。冷却通道可以通过来自平台的冷却空气流动。叶片尖端由设置在叶片的压力面上的用于对流冷却的第一冷却孔冷却，并且在叶片的吸入侧通过叶片的盖在叶片尖端从第二冷却孔冷却通道，并分布在刀片宽度上。

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