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1. 发明申请

US20110286849A1 BLADE FOR A GAS TURBINE 有权
标题翻译：燃气轮机叶片
公开(公告)号：US20110286849A1
公开(公告)日：2011-11-24
申请号：US13091605
申请日：2011-04-21
申请人： Igor TSYPKAYKIN , Ruben Valiente , Brian Kenneth Wardle , Beat Von Arx , Andre Saxer
发明人： Igor TSYPKAYKIN , Ruben Valiente , Brian Kenneth Wardle , Beat Von Arx , Andre Saxer
IPC分类号： F01D5/14
CPC分类号： F01D5/225 , F05B2240/33
摘要： A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width.
摘要翻译：公开了一种用于燃气涡轮机的叶片，其包括翼型件，该翼型件沿着纵向轴线从叶片根部延伸到叶片尖端，并且在叶片尖端处具有护罩段。护罩部分与第一和第二边缘邻接抵靠相邻刀片的护罩部分以形成环形护罩。第一和第二边缘分别在护罩段的上侧设置有相应的侧轨。每个侧轨分为不同高度和/或宽度的部分。

2. 发明授权

US08632309B2 Blade for a gas turbine 有权
标题翻译：燃气轮机叶片
公开(公告)号：US08632309B2
公开(公告)日：2014-01-21
申请号：US13091605
申请日：2011-04-21
申请人： Igor Tsypkaykin , Ruben Valiente , Brian Kenneth Wardle , Beat Von Arx , Andre Saxer
发明人： Igor Tsypkaykin , Ruben Valiente , Brian Kenneth Wardle , Beat Von Arx , Andre Saxer
IPC分类号： F01D5/14
CPC分类号： F01D5/225 , F05B2240/33
摘要： A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width.
摘要翻译：公开了一种用于燃气涡轮机的叶片，其包括翼型件，该翼型件沿着纵向轴线从叶片根部延伸到叶片尖端，并且在叶片尖端处具有护罩段。护罩部分与第一和第二边缘邻接抵靠相邻刀片的护罩部分以形成环形护罩。第一和第二边缘分别在护罩段的上侧设置有相应的侧轨。每个侧轨分为不同高度和/或宽度的部分。

3. 发明申请

US20100124493A1 MULTI-VANE SEGMENT DESIGN AND CASTING METHOD 有权
标题翻译：多层分段设计和铸造方法
公开(公告)号：US20100124493A1
公开(公告)日：2010-05-20
申请号：US12617310
申请日：2009-11-12
申请人： Brian Kenneth WARDLE , Thomas Peter SOMMER , Beat Von ARX , Andre Saxer
发明人： Brian Kenneth WARDLE , Thomas Peter SOMMER , Beat Von ARX , Andre Saxer
IPC分类号： F01D9/02 , B22D23/00 , B22D25/00
CPC分类号： F01D9/041 , B22C9/043 , F05D2230/21 , F05D2230/211 , F05D2240/40 , Y02T50/671 , Y02T50/673
摘要： Provided is an industrial gas turbine multi vane segment, which can be cast in one piece using a wax pattern method. The multi vane segment includes a platform; at least three airfoils, extending radially from the platform, having a combined airfoil volume, a chord length and an airfoil thickness; and a shroud with a shroud volume, disposed on an end of said airfoils radially distant from the platform. The ratio of the shroud volume to the combined airfoil volume defines a first ratio, while the multi vane segment has a first ratio greater or equal to 1.4:1. This ratio enables preferential solidification, during casting, of the airfoils before the shroud.
摘要翻译：提供了一种工业燃气轮机多叶片段，其可以使用蜡模式法一体铸造。多叶片段包括一个平台; 从平台径向延伸的至少三个翼型件，具有组合的翼型体积，弦长和翼型件厚度; 以及具有护罩体积的护罩，其设置在径向远离平台的所述翼型件的端部上。护罩体积与组合的翼型体积的比值定义第一比例，而多叶片段具有大于或等于1.4:1的第一比例。该比率使得在浇铸之前优先凝固翼片前的翼型件。

4. 发明申请

US20110189002A1 TURBINE GUIDE VANE 审中-公开
标题翻译：涡轮导向槽
公开(公告)号：US20110189002A1
公开(公告)日：2011-08-04
申请号：US13012317
申请日：2011-01-24
申请人： Georgeta-Ileana Panaite , Igor Tsypkaykin , Beat Von Arx , Andre Saxer
发明人： Georgeta-Ileana Panaite , Igor Tsypkaykin , Beat Von Arx , Andre Saxer
IPC分类号： F01D9/04
CPC分类号： F01D9/042 , F01D25/246 , F05D2230/64 , F05D2240/80
摘要： A turbine guide vane (10) has a platform (12) from which at least a guide vane blade (13) extends. The platform (12) has a front rail (18) and a rear rail (20) arranged to be housed in guide vane carrier seats (19, 21). The front and rear rails (18, 20) have projecting pads (23, 24) arranged to rest against the guide vane carrier seats (19, 21). The front and rear rails (18, 20) have at least two pads (23) extending from one side of the front and rear rails (18, 20) and at least two further pads (24) extending from an opposite side of the front and rear rails (18, 20). The pads (23, 24) extend from opposite circumferential portions (26) of the front and rear rails (18, 20). The pads (23, 24) extending from the same circumferential portion (26) of the front and rear rails (18, 20) are at least partly staggered with respect to one another.
摘要翻译：涡轮引导叶片（10）具有平台（12），至少一个导叶叶片（13）从该平台延伸。平台（12）具有布置成容纳在导向叶片承载座（19,21）中的前轨（18）和后轨（20）。前导轨和后导轨（18,20）具有布置成抵靠引导叶片承载座（19,21）的突出垫（23,24）。前导轨和后导轨（18,20）具有从前后导轨（18,20）的一侧延伸的至少两个焊盘（23）和从前部的相对侧延伸的至少两个另外的焊盘（24）和后导轨（18,20）。垫（23,24）从前后导轨（18,20）的相对周向部分（26）延伸。从前后导轨（18,20）的同一圆周部分（26）延伸的焊盘（23,24）相对于彼此至少部分地交错。

5. 发明授权

US08371808B2 Multi-vane segment design and casting method 有权
标题翻译：多叶片段设计和铸造方法
公开(公告)号：US08371808B2
公开(公告)日：2013-02-12
申请号：US12617310
申请日：2009-11-12
申请人： Brian Kenneth Wardle , Thomas Peter Sommer , Beat Von Arx , Andre Saxer
发明人： Brian Kenneth Wardle , Thomas Peter Sommer , Beat Von Arx , Andre Saxer
IPC分类号： F01D9/02
CPC分类号： F01D9/041 , B22C9/043 , F05D2230/21 , F05D2230/211 , F05D2240/40 , Y02T50/671 , Y02T50/673
摘要： Provided is an industrial gas turbine multi vane segment, which can be cast in one piece using a wax pattern method. The multi vane segment includes a platform; at least three airfoils, extending radially from the platform, having a combined airfoil volume, a chord length and an airfoil thickness; and a shroud with a shroud volume, disposed on an end of said airfoils radially distant from the platform. The ratio of the shroud volume to the combined airfoil volume defines a first ratio, while the multi vane segment has a first ratio greater or equal to 1.4:1. This ratio enables preferential solidification, during casting, of the airfoils before the shroud.
摘要翻译：提供了一种工业燃气轮机多叶片段，其可以使用蜡模式法一体铸造。多叶片段包括一个平台; 从平台径向延伸的至少三个翼型件，具有组合的翼型体积，弦长和翼型件厚度; 以及具有护罩体积的护罩，其设置在径向远离平台的所述翼型件的端部上。护罩体积与组合的翼型体积的比值定义第一比例，而多叶片段具有大于或等于1.4:1的第一比例。该比率使得在浇铸之前优先凝固翼片前的翼型件。

6. 发明授权

US09341069B2 Gas turbine 有权
标题翻译：燃气轮机
公开(公告)号：US09341069B2
公开(公告)日：2016-05-17
申请号：US13239549
申请日：2011-09-22
申请人： Ruben Valiente , Shailendra Naik , Andre Saxer
发明人： Ruben Valiente , Shailendra Naik , Andre Saxer
IPC分类号： F01D5/08 , F01D5/30
CPC分类号： F01D5/3007 , F01D5/081 , F01D5/087
摘要： A gas turbine includes a rotor having a rotor groove and a rotor bore extending through the rotor, the rotor bore having a diffuser-shaped rotor bore exit. A blade is attached to the rotor and includes a blade tip having at least one dust hole. An airfoil has a leading edge and a trailing edge extending along a longitudinal axis of the blade between a lower end of the airfoil and the blade tip. A blade root is disposed at the lower end of the airfoil and is configured to be removably disposed in the rotor groove. The blade root includes a blade inlet having a cross sectional area that exceeds a cross sectional area of the rotor bore in at least one direction. A hollow blade core is disposed in the airfoil and extends along the longitudinal axis of the blade between the blade root and the blade tip.
摘要翻译：燃气轮机包括具有转子槽的转子和延伸穿过转子的转子孔，转子孔具有扩散器形的转子孔出口。叶片附接到转子并且包括具有至少一个灰尘孔的叶片尖端。翼型件具有前缘和后缘，其沿着翼片的纵向轴线在翼型的下端和叶片尖端之间延伸。叶片根部设置在翼型件的下端，并且构造成可拆卸地设置在转子槽中。叶片根部包括具有在至少一个方向上超过转子孔的横截面积的横截面积的叶片入口。空心叶片芯设置在翼型件中并且沿着叶片的纵向轴线在叶片根部和叶片尖端之间延伸。

7. 发明申请

US20120087782A1 GAS TURBINE 有权
标题翻译：燃气轮机
公开(公告)号：US20120087782A1
公开(公告)日：2012-04-12
申请号：US13239549
申请日：2011-09-22
申请人： Ruben Valiente , Shailendra Naik , Andre Saxer
发明人： Ruben Valiente , Shailendra Naik , Andre Saxer
IPC分类号： F01D5/08
CPC分类号： F01D5/3007 , F01D5/081 , F01D5/087
摘要： A gas turbine includes a rotor having a rotor groove and a rotor bore extending through the rotor, the rotor bore having a diffuser-shaped rotor bore exit. A blade is attached to the rotor and includes a blade tip having at least one dust hole. An airfoil has a leading edge and a trailing edge extending along a longitudinal axis of the blade between a lower end of the airfoil and the blade tip. A blade root is disposed at the lower end of the airfoil and is configured to be removably disposed in the rotor groove. The blade root includes a blade inlet having a cross sectional area that exceeds a cross sectional area of the rotor bore in at least one direction. A hollow blade core is disposed in the airfoil and extends along the longitudinal axis of the blade between the blade root and the blade tip.
摘要翻译：燃气轮机包括具有转子槽的转子和延伸穿过转子的转子孔，转子孔具有扩散器形状的转子孔出口。叶片附接到转子并包括具有至少一个灰尘孔的叶片尖端。翼型件具有前缘和后缘，其沿着翼片的纵向轴线在翼型的下端和叶片尖端之间延伸。叶片根部设置在翼型件的下端，并且构造成可拆卸地设置在转子槽中。叶片根部包括具有在至少一个方向上超过转子孔的横截面积的横截面积的叶片入口。空心叶片芯设置在翼型件中并且沿着叶片的纵向轴线在叶片根部和叶片尖端之间延伸。

8. 发明申请

US20110293428A1 METHOD FOR OPTIMIZING THE CONTACT SURFACES OF SHROUD SEGMENTS, WHICH ABUT AGAINST ONE ANOTHER, OF ADJACENT BLADES OF A GAS TURBINE 审中-公开
标题翻译：用于优化除了一个另外另外一个气体涡轮机相邻叶片的接头表面的方法
公开(公告)号：US20110293428A1
公开(公告)日：2011-12-01
申请号：US13117166
申请日：2011-05-27
申请人： Igor Tsypkaykin , Andre Saxer
发明人： Igor Tsypkaykin , Andre Saxer
IPC分类号： F01D5/22 , G06F17/50
CPC分类号： F01D5/225 , F05D2250/183
摘要： A method for optimizing the contact surfaces of abutting shroud segments of adjacent blades of a rotor blade row of a gas turbine includes providing a 3-D model of an individual blade. A geometry of the individual blade is calculated using the 3-D model while considering centrifugal forces, temperature stresses and pressure loads experienced in a loaded state of the blade during operation. The contact surfaces of the abutting shroud segments of adjacent blades are optimized in the loaded state of the blade. The optimization includes the surfaces of functionally serving interlocking surfaces and functionally serving wedge surfaces disposed on each side of the interlocking surfaces. A geometry of the interlocking surfaces and of the wedge surfaces in an unloaded state corresponding to the optimized contact surfaces in the loaded state of the blade is calculated.
摘要翻译：用于优化燃气轮机的转子叶片排的相邻叶片的邻接的护罩段的接触表面的方法包括提供单个叶片的3-D模型。使用三维模型计算单个叶片的几何形状，同时考虑在操作期间在叶片的加载状态下遇到的离心力，温度应力和压力负载。相邻叶片的邻接护罩段的接触表面在叶片的加载状态下被优化。优化包括设置在互锁表面的每一侧上的功能性联锁表面和功能性服务楔形表面的表面。计算在与负载状态下的优化的接触表面相对应的处于未加载状态的互锁表面和楔形表面的几何形状。

9. 发明授权

US09441489B2 Sealing structure on a shroud of a turbine blade 有权
标题翻译：涡轮叶片护罩上的密封结构
公开(公告)号：US09441489B2
公开(公告)日：2016-09-13
申请号：US13076653
申请日：2011-03-31
申请人： Andre Saxer , Igor Tsypkaykine , Ulrich Rathmann
发明人： Andre Saxer , Igor Tsypkaykine , Ulrich Rathmann
IPC分类号： F01D11/08 , F01D5/22 , F01D5/20 , F01D5/26 , F01D11/12
CPC分类号： F01D5/225 , F01D5/20 , F01D5/26 , F01D11/125 , F05D2250/70
摘要： A device on a shroud which is provided on a turbine rotor blade tip has a cutting structure designed like a line of ribs, locally projecting over the shroud radially to the rotational axis around which the turbine rotor blade is rotatably arranged. The sealing structure has a longitudinal extent (S) oriented in the direction of rotation (U) of the turbine rotor blade, tapers with increasing radial distance from the shroud, and terminates with a flat end face (St) which radially faces away from the turbine rotor blade, and can be divided into five interrelated surfaces.
摘要翻译：设置在涡轮转子叶片尖端上的护罩上的装置具有设计成类似肋条的切割结构，其在辐射体上径向地突出于旋转轴线，涡轮转子叶片围绕该旋转轴线可旋转地布置。密封结构具有沿涡轮转子叶片的旋转方向（U）定向的纵向范围（S），随着与护罩的径向距离的增加而逐渐变细，并以一个平坦的端面（St）终止，该端面径向地远离涡轮转子叶片，并可分为五个相互关联的表面。

10. 发明申请

US20110243714A1 SEALING STRUCTURE ON A SHROUD OF A TURBINE BLADE 有权
标题翻译：在涡轮叶片上密封结构
公开(公告)号：US20110243714A1
公开(公告)日：2011-10-06
申请号：US13076653
申请日：2011-03-31
申请人： Andre Saxer , Igor Tsypkaykine , Ulrich Rathmann
发明人： Andre Saxer , Igor Tsypkaykine , Ulrich Rathmann
IPC分类号： F01D11/08 , F01D5/26 , F01D5/14
CPC分类号： F01D5/225 , F01D5/20 , F01D5/26 , F01D11/125 , F05D2250/70
摘要： A device on a shroud which is provided on a turbine rotor blade tip has a cutting structure designed like a line of ribs, locally projecting over the shroud radially to the rotational axis around which the turbine rotor blade is rotatably arranged. The sealing structure has a longitudinal extent (S) oriented in the direction of rotation (U) of the turbine rotor blade, tapers with increasing radial distance from the shroud, and terminates with a flat end face (St) which radially faces away from the turbine rotor blade, and can be divided into five interrelated surfaces.
摘要翻译：设置在涡轮转子叶片尖端上的护罩上的装置具有设计成类似肋条的切割结构，其在辐射体上径向地突出于旋转轴线，涡轮转子叶片围绕该旋转轴线可旋转地布置。密封结构具有沿涡轮转子叶片的旋转方向（U）定向的纵向范围（S），随着与护罩的径向距离的增加而逐渐变细，并以一个平坦的端面（St）终止，该端面径向地远离涡轮转子叶片，并可分为五个相互关联的表面。

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