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：US20130170944A1

公开(公告)日：2013-07-04

申请号：US13343301

申请日：2012-01-04

申请人： Mahesh Pasupuleti ,  Shadab Ali ,  Mohankumar Banakar ,  Viswanathan Venkatachalapathy

发明人： Mahesh Pasupuleti ,  Shadab Ali ,  Mohankumar Banakar ,  Viswanathan Venkatachalapathy

IPC分类号： F04D29/08

CPC分类号： F01D11/006 ,  F05D2240/55 ,  F05D2260/32 ,  F05D2300/507

摘要： According to one aspect of the invention, a turbine assembly includes a first bucket with a first slashface and a second bucket including a recess formed in a second slashface of the second bucket, wherein the second slashface is adjacent to the first slashface when the first bucket is positioned adjacent to the second bucket. The turbine assembly also includes a pin configured to be placed in the recess, wherein the pin is magnetically urged toward the first slashface to reduce fluid flow between the first and second buckets.

摘要翻译： 根据本发明的一个方面，涡轮组件包括具有第一斜面的第一铲斗和包括形成在第二铲斗的第二斜面中的凹部的第二铲斗，其中当第一铲斗 定位成与第二桶相邻。 涡轮组件还包括构造成放置在凹部中的销，其中销被朝向第一斜面磁力推动以减少第一和第二桶之间的流体流动。