公开(公告)号：US20130336801A1

公开(公告)日：2013-12-19

申请号：US13524026

申请日：2012-06-15

申请人： Sheo Narain Giri ,  Harish Bommanakatte ,  Mohankumar Banakar ,  John David Ward, JR. ,  Jonathan Matthew Lomas

发明人： Sheo Narain Giri ,  Harish Bommanakatte ,  Mohankumar Banakar ,  John David Ward, JR. ,  Jonathan Matthew Lomas

IPC分类号： F01D5/14

CPC分类号： F01D5/143 ,  F01D5/147 ,  F05D2240/80

摘要： A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.

摘要翻译： 涡轮机的旋转翼型部件，其中部件具有在部件的翼展方向上对齐的翼型，柄以及横向于翼展方向定向的平台。 平台具有邻近翼型的外径向表面，以及限定在其外径向表面中的至少一个凹陷区域。 凹陷区域从包含在凹陷区域的上游和下游的外部径向表面的部分的平台平面相对于翼展方向延伸。 凹陷区域与平台的端壁邻接并从其向翼型延伸。 凹陷区域限定了边界由平台平面包围的表面形状，并且具有从端壁向翼型延伸的轮廓形状。 凹陷区域的尺寸和形状可以增加平台的刚度。

公开(公告)号：US09033669B2

公开(公告)日：2015-05-19

申请号：US13524026

申请日：2012-06-15

申请人： Sheo Narain Giri ,  Harish Bommanakatte ,  Mohankumar Banakar ,  John David Ward, Jr. ,  Jonathan Matthew Lomas

发明人： Sheo Narain Giri ,  Harish Bommanakatte ,  Mohankumar Banakar ,  John David Ward, Jr. ,  Jonathan Matthew Lomas

IPC分类号： F01D5/14

CPC分类号： F01D5/143 ,  F01D5/147 ,  F05D2240/80

摘要： A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.

摘要翻译： 涡轮机的旋转翼型部件，其中部件具有在部件的翼展方向上对齐的翼型，柄以及横向于翼展方向定向的平台。 平台具有邻近翼型的外径向表面，以及限定在其外径向表面中的至少一个凹陷区域。 凹陷区域从包含在凹陷区域的上游和下游的外部径向表面的部分的平台平面相对于翼展方向延伸。 凹陷区域与平台的端壁邻接并从其向翼型延伸。 凹陷区域限定了边界由平台平面包围的表面形状，并且具有从端壁向翼型延伸的轮廓形状。 凹陷区域的尺寸和形状可以增加平台的刚度。

公开(公告)号：US20130343868A1

公开(公告)日：2013-12-26

申请号：US13532470

申请日：2012-06-25

申请人： Sanjeev Kumar Jha ,  Sheo Narain Giri ,  Bhaskar Pemmi ,  Harish Bommanakatte ,  Rajesh Achudhan

发明人： Sanjeev Kumar Jha ,  Sheo Narain Giri ,  Bhaskar Pemmi ,  Harish Bommanakatte ,  Rajesh Achudhan

IPC分类号： F01D9/04 ,  F01D17/12 ,  F01D25/12

CPC分类号： F01D5/087 ,  F02C7/057 ,  F04D29/023 ,  F04D29/321 ,  F04D29/584 ,  F05D2300/17 ,  F05D2300/505

摘要： Embodiments of the present application include a gas turbine system. The system may include a rotor wheel and one or more impeller vanes radially disposed on the rotor wheel. The system may also include one or more fluid passages defined by adjacent impeller vanes. The one or more fluid passages may be radially disposed across the rotor wheel. Moreover, the system may include one or more shape memory alloy valves disposed within each of the fluid passages. The one or more shape memory alloy valves may be configured to change shape to control a flow of fluid through the fluid passages.

摘要翻译： 本申请的实施例包括燃气轮机系统。 该系统可以包括转子轮和径向设置在转子轮上的一个或多个叶轮叶片。 系统还可以包括由相邻叶轮叶片限定的一个或多个流体通道。 一个或多个流体通道可以跨过转子轮径向地设置。 此外，系统可以包括设置在每个流体通道内的一个或多个形状记忆合金阀。 一个或多个形状记忆合金阀可以被配置为改变形状以控制通过流体通道的流体流动。

公开(公告)号：US09188010B2

公开(公告)日：2015-11-17

申请号：US13532470

申请日：2012-06-25

申请人： Sanjeev Kumar Jha ,  Sheo Narain Giri ,  Bhaskar Pemmi ,  Harish Bommanakatte ,  Rajesh Achudhan

发明人： Sanjeev Kumar Jha ,  Sheo Narain Giri ,  Bhaskar Pemmi ,  Harish Bommanakatte ,  Rajesh Achudhan

IPC分类号： F01D5/08 ,  F04D29/02 ,  F04D29/58 ,  F04D29/32 ,  F02C7/057

CPC分类号： F01D5/087 ,  F02C7/057 ,  F04D29/023 ,  F04D29/321 ,  F04D29/584 ,  F05D2300/17 ,  F05D2300/505

摘要： Embodiments of the present application include a gas turbine system. The system may include a rotor wheel and one or more impeller vanes radially disposed on the rotor wheel. The system may also include one or more fluid passages defined by adjacent impeller vanes. The one or more fluid passages may be radially disposed across the rotor wheel. Moreover, the system may include one or more shape memory alloy valves disposed within each of the fluid passages. The one or more shape memory alloy valves may be configured to change shape to control a flow of fluid through the fluid passages.

摘要翻译： 本申请的实施例包括燃气轮机系统。 该系统可以包括转子轮和径向设置在转子轮上的一个或多个叶轮叶片。 系统还可以包括由相邻叶轮叶片限定的一个或多个流体通道。 一个或多个流体通道可以跨过转子轮径向地设置。 此外，系统可以包括设置在每个流体通道内的一个或多个形状记忆合金阀。 一个或多个形状记忆合金阀可以被配置为改变形状以控制通过流体通道的流体流动。

公开(公告)号：US09051845B2

公开(公告)日：2015-06-09

申请号：US13344421

申请日：2012-01-05

申请人： Harish Bommanakatte ,  Sheo Narain Giri ,  David Randolph Spracher ,  Zachary James Taylor ,  Ryan Zane Ziegler

发明人： Harish Bommanakatte ,  Sheo Narain Giri ,  David Randolph Spracher ,  Zachary James Taylor ,  Ryan Zane Ziegler

IPC分类号： F01D5/32 ,  F01D5/30

CPC分类号： F01D5/3007 ,  F01D5/22 ,  F01D5/30 ,  F01D5/3053 ,  F01D5/32 ,  Y10T29/49321

摘要： A turbomachine system includes a turbomachine that includes a rotor that includes a rotational axis, a first rotating segment having a first mating axial mount coupled to a first axial mount of the rotor in a first installed position and a first pin configured to insert into a first inserted position in both a first slot in the rotor and a first mating slot in the first rotating segment. The first pin in the first inserted position is configured to block axial movement of the first mating axial mount relative to the first axial mount. The turbomachine also includes a second rotating segment having a second mating axial mount coupled to a second axial mount of the rotor in a second installed position. The second rotating segment in the second installed position is configured to block removal of the first pin.

摘要翻译： 涡轮机系统包括涡轮机，其包括包括旋转轴线的转子，第一旋转段，具有在第一安装位置中联接到转子的第一轴向安装件的第一配合轴向安装件，以及构造成插入到第一安装位置的第一销 在转子的第一槽和第一旋转段中的第一配合槽中的插入位置。 第一插入位置中的第一销被构造成阻止第一配合轴向安装件相对于第一轴向安装件的轴向运动。 涡轮机还包括第二旋转段，其具有在第二安装位置中联接到转子的第二轴向安装件的第二配合轴向安装件。 在第二安装位置的第二旋转部分构造成阻止第一销的移除。

公开(公告)号：US20130177429A1

公开(公告)日：2013-07-11

申请号：US13344421

申请日：2012-01-05

申请人： Harish Bommanakatte ,  Sheo Narain Giri ,  David Randolph Spracher ,  Zachary James Taylor ,  Ryan Zane Ziegler

发明人： Harish Bommanakatte ,  Sheo Narain Giri ,  David Randolph Spracher ,  Zachary James Taylor ,  Ryan Zane Ziegler

IPC分类号： F01D5/32 ,  B23P15/04

CPC分类号： F01D5/3007 ,  F01D5/22 ,  F01D5/30 ,  F01D5/3053 ,  F01D5/32 ,  Y10T29/49321

摘要： A turbomachine system includes a turbomachine that includes a rotor that includes a rotational axis, a first rotating segment having a first mating axial mount coupled to a first axial mount of the rotor in a first installed position and a first pin configured to insert into a first inserted position in both a first slot in the rotor and a first mating slot in the first rotating segment. The first pin in the first inserted position is configured to block axial movement of the first mating axial mount relative to the first axial mount. The turbomachine also includes a second rotating segment having a second mating axial mount coupled to a second axial mount of the rotor in a second installed position. The second rotating segment in the second installed position is configured to block removal of the first pin.

摘要翻译： 涡轮机系统包括涡轮机，其包括包括旋转轴线的转子，第一旋转段，具有在第一安装位置中联接到转子的第一轴向安装件的第一配合轴向安装件，以及构造成插入到第一安装位置的第一销 在转子的第一槽和第一旋转段中的第一配合槽中的插入位置。 第一插入位置中的第一销被构造成阻止第一配合轴向安装件相对于第一轴向安装件的轴向运动。 涡轮机还包括第二旋转段，其具有在第二安装位置中联接到转子的第二轴向安装件的第二配合轴向安装件。 在第二安装位置的第二旋转部分构造成阻止第一销的移除。

公开(公告)号：US20130186103A1

公开(公告)日：2013-07-25

申请号：US13354625

申请日：2012-01-20

申请人： Sanjeev Kumar Jha ,  Harish Bommonakatte ,  Sheo Narain Giri

发明人： Sanjeev Kumar Jha ,  Harish Bommonakatte ,  Sheo Narain Giri

IPC分类号： F02C7/28 ,  F16J15/44

CPC分类号： F01D11/001 ,  F01D11/02 ,  F05B2250/61 ,  F05D2250/232

摘要： A near flow path seal for a turbomachine includes a support member having a first end portion that extends to a second end portion through an intermediate portion, and an arm member extending from the first end portion of the support member. The arm member includes a first end that extends to a second end, a first surface extending between the first and second ends, and a second, opposing surface extending between the first and second ends. The second surface includes a plurality of surface features that extend from about the first end toward the second end.

摘要翻译： 用于涡轮机的近流路密封件包括支撑构件，该支撑构件具有通过中间部分延伸到第二端部的第一端部和从支撑构件的第一端部延伸的臂构件。 臂构件包括延伸到第二端的第一端，在第一和第二端之间延伸的第一表面和在第一和第二端之间延伸的第二相对表面。 第二表面包括从大约第一端向第二端延伸的多个表面特征。

公开(公告)号：US20120177478A1

公开(公告)日：2012-07-12

申请号：US12985498

申请日：2011-01-06

申请人： Sheo Narain Giri ,  Siddaraja Mallikarjuna Devangada ,  Brad Wilson VanTassel ,  Debdulal Das

发明人： Sheo Narain Giri ,  Siddaraja Mallikarjuna Devangada ,  Brad Wilson VanTassel ,  Debdulal Das

IPC分类号： F01D25/12

CPC分类号： F01D25/12 ,  F01D5/187 ,  F01D9/041 ,  F05D2230/232 ,  F05D2230/642 ,  F05D2250/611 ,  F05D2260/201 ,  Y02T50/671 ,  Y02T50/676

摘要： An impingement plate adapted to reduce thermally-induced strains and stresses that may damage the plate or its attachment to a second component. The plate includes an interior region having cooling holes, a peripheral wall surrounding the interior region and projecting out of the plane of the interior region, a peripheral flange surrounding the peripheral wall and lying in a plane spaced apart from the plane of the interior region, and one or more through-thickness rib. One such rib may be disposed in the interior region, project away from and out of the plane of the interior region, and linearly extend across the interior region. Alternatively or in addition, one such rib may be disposed between the peripheral wall and flange and project out of the plane of the flange.

摘要翻译： 适于减少可能损坏板或其附接到第二部件的热诱导应变和应力的冲击板。 所述板包括具有冷却孔的内部区域，围绕所述内部区域并突出到所述内部区域的平面外围的周边壁;围绕所述周边壁并位于与所述内部区域的平面间隔开的平面中的周边凸缘， 和一个或多个贯穿厚度的肋。 一个这样的肋可以设置在内部区域中，远离和离开内部区域的平面，并且线性延伸穿过内部区域。 或者或另外，一个这样的肋可以设置在周壁和凸缘之间并突出到凸缘的平面之外。

公开(公告)号：US20140023517A1

公开(公告)日：2014-01-23

申请号：US13555417

申请日：2012-07-23

申请人： Shruti Kulkarni ,  Joseph Vincent Pawlowski ,  Sheo Narain Giri

发明人： Shruti Kulkarni ,  Joseph Vincent Pawlowski ,  Sheo Narain Giri

IPC分类号： F01D5/18

CPC分类号： F01D9/041 ,  F01D9/042 ,  F01D11/008 ,  F01D25/246 ,  F05D2240/80 ,  F05D2240/81

摘要： A nozzle for a turbine system is disclosed. The nozzle includes an airfoil, an inner sidewall, and an outer sidewall. The airfoil includes exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge. The airfoil further defines a tip and a root. The inner sidewall is connected to the airfoil at the tip. The outer sidewall is connected to the airfoil at the root. The inner sidewall and outer sidewall each includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face has a generally curvilinear profile.

摘要翻译： 公开了一种用于涡轮机系统的喷嘴。 喷嘴包括翼型件，内侧壁和外侧壁。 翼型件包括限定压力侧的外表面和在前缘和后缘之间延伸的吸力侧。 翼型件还限定了尖端和根部。 内侧壁在尖端连接到翼型。 外侧壁与根部的翼型连接。 内侧壁和外侧壁均包括限定压力侧斜面，吸力侧斜面，前缘面和后缘面的周缘。 内侧壁压侧侧斜面，内侧壁吸力侧斜面，外侧壁压侧侧斜面或外侧壁吸力侧斜面中的至少一方具有大致曲线的轮廓。

公开(公告)号：US08544852B2

公开(公告)日：2013-10-01

申请号：US13152585

申请日：2011-06-03

申请人： Sheo Narain Giri

发明人： Sheo Narain Giri

IPC分类号： F16J15/02

CPC分类号： F16J15/0887 ,  F01D11/003 ,  F05D2250/15 ,  F05D2260/38

摘要： A torsion seal is provided and includes a first section, a second section and a torsion section connected at opposite end portions thereof to the first and second sections and having a central portion extending between the opposite end portions to absorb differential thermal growth of vessels to which the first and second sections are coupled.

摘要翻译： 提供扭转密封件，并且包括第一部分，第二部分和扭转部分，该部分在其相对端部处连接到第一和第二部分，并且具有在相对端部之间延伸的中心部分，以吸收容器的不同热生长， 第一和第二部分联接。