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21. 发明申请

US20110085892A1 VORTEX CHAMBERS FOR CLEARANCE FLOW CONTROL 有权
标题翻译： VORTEX阀门用于间隙流量控制
公开(公告)号：US20110085892A1
公开(公告)日：2011-04-14
申请号：US12578770
申请日：2009-10-14
申请人： Joshy John , Sanjeev Kumar Jain , Sachin Kumar Rai
发明人： Joshy John , Sanjeev Kumar Jain , Sachin Kumar Rai
IPC分类号： F01D11/10
CPC分类号： F01D11/10 , F05D2240/127
摘要： An apparatus is provided and includes a first member with a flow diverting member extending from a surface thereof and a second member disposed proximate to the first member with a clearance gap area defined between a surface of the second member and a distal end of the flow diverting member such that a fluid path, along which fluid flows from an upstream section and through the clearance gap area, is formed between the surfaces of the first and second members. The second member is formed to define dual vortex chambers at the upstream section in which the fluid is directed to flow in vortex patterns prior to being permitted to flow through the clearance gap area.
摘要翻译：提供了一种装置，其包括具有从其表面延伸的流动分流构件的第一构件和靠近第一构件设置的第二构件，其间限定在第二构件的表面与分流器的远端之间的间隙区域使得在第一和第二构件的表面之间形成流体路径，流体路径从上游区段流过间隙区域。第二构件被形成为在上游部分处限定双涡流室，在该部分处流体被引导以在允许流过间隙区域之前以涡流图案流动。

22. 发明授权

US08870532B2 Exhaust hood diffuser 有权
标题翻译：排气罩扩散器
公开(公告)号：US08870532B2
公开(公告)日：2014-10-28
申请号：US12945917
申请日：2010-11-15
申请人： Sudhakar Neeli , Joshy John
发明人： Sudhakar Neeli , Joshy John
IPC分类号： F01D25/24 , F01D25/30
CPC分类号： F01D25/30 , F05D2220/31 , F05D2250/11
摘要： The present application provides a diffuser for an exhaust hood of a steam turbine. The diffuser may include a first end adjacent to a last bucket and a second end downstream of a steam guide and adjacent to a bearing cone. An exhaust flow path extends therethrough. The second end may include an axial extension enlarging the exhaust flow path.
摘要翻译：本申请提供了一种用于蒸汽轮机的排气罩的扩散器。扩散器可以包括与最后一个铲斗相邻的第一端和蒸汽引导件的下游的第二端并与轴承锥相邻。排气流路延伸穿过其中。第二端可以包括扩大排气流动路径的轴向延伸。

23. 发明授权

US08721289B2 Flow balancing slot 有权
标题翻译：流量平衡槽
公开(公告)号：US08721289B2
公开(公告)日：2014-05-13
申请号：US12609376
申请日：2009-10-30
申请人： Joshy John , Rajnikumar Nandalal Suthar , Rajaguru Nathan Krishnasamy
发明人： Joshy John , Rajnikumar Nandalal Suthar , Rajaguru Nathan Krishnasamy
IPC分类号： F01D11/06 , B64C27/20
CPC分类号： F01D5/225
摘要： A cover of an airfoil having opposing pressure and suction sides of a rotatable turbine stage to prevent fluid from crossover-flowing from a pressure side of a leading airfoil to a suction side of a trailing airfoil is provided. The cover includes pressure and suction side edge portions, one of which having a shape that is discontinuous relative to that of a complementary one of suction and pressure side edge portions of an aft cover of a corresponding one of a trailing and a leading airfoil, respectively.
摘要翻译：提供具有可旋转涡轮机台的相对的压力和吸力侧的翼型的盖子，以防止流体从引导翼型的压力侧跨越到后缘翼的吸力侧。盖子包括压力和吸力侧边缘部分，其中一个具有分别相对于拖尾和先导翼型中的相应一个的后盖的吸力和压力侧边缘部分互补的一个形状不连续的形状。

24. 发明授权

US08608424B2 Contoured honeycomb seal for a turbomachine 有权
标题翻译：用于涡轮机的轮廓式蜂窝密封
公开(公告)号：US08608424B2
公开(公告)日：2013-12-17
申请号：US12576345
申请日：2009-10-09
申请人： Sanjeev Kumar Jain , Joshy John , Sachin Kumar Rai , Rajnikumar Nandalal Suthar
发明人： Sanjeev Kumar Jain , Joshy John , Sachin Kumar Rai , Rajnikumar Nandalal Suthar
IPC分类号： F01D11/12
CPC分类号： F01D11/127 , F05D2250/32 , F05D2250/71
摘要： A turbomachine includes a housing having an inner surface, a compressor, a turbine and a rotary member including a plurality of blade members configured as part of one of the compressor and the turbine. Each of the plurality of blade members includes a base portion and a tip portion. The turbomachine also includes a honeycomb seal member mounted to the inner surface of the housing adjacent the rotary member. The honeycomb seal member includes a contoured surface having formed therein a deformation zone. The deformation zone includes an inlet zone and an outlet zone. The inlet zone is spaced a first distance from the tip portion of each of the plurality of blade members and the outlet zone is spaced a second distance from the tip portion of each of the plurality of blade members. The second distance being substantially equal to or less than the first distance.
摘要翻译：涡轮机包括具有内表面的壳体，压缩机，涡轮机和旋转构件，其包括构造为压缩机和涡轮机之一的一部分的多个叶片构件。多个叶片构件中的每一个包括基部和尖端部。涡轮机还包括蜂窝密封构件，其安装在邻近旋转构件的壳体的内表面上。蜂窝状密封构件包括在其中形成有变形区域的轮廓表面。变形区包括入口区和出口区。入口区域与多个叶片构件中的每一个的顶端部分隔开第一距离，并且出口区域与多个叶片构件中的每一个的顶端部分间隔开第二距离。第二距离基本上等于或小于第一距离。

25. 发明授权

US08333557B2 Vortex chambers for clearance flow control 有权
标题翻译：涡流室用于清除流量控制
公开(公告)号：US08333557B2
公开(公告)日：2012-12-18
申请号：US12578770
申请日：2009-10-14
申请人： Joshy John , Sanjeev Kumar Jain , Sachin Kumar Rai
发明人： Joshy John , Sanjeev Kumar Jain , Sachin Kumar Rai
IPC分类号： F01D11/10
CPC分类号： F01D11/10 , F05D2240/127
摘要： An apparatus is provided and includes a first member with a flow diverting member extending from a surface thereof and a second member disposed proximate to the first member with a clearance gap area defined between a surface of the second member and a distal end of the flow diverting member such that a fluid path, along which fluid flows from an upstream section and through the clearance gap area, is formed between the surfaces of the first and second members. The second member is formed to define dual vortex chambers at the upstream section in which the fluid is directed to flow in vortex patterns prior to being permitted to flow through the clearance gap area.
摘要翻译：提供了一种装置，其包括具有从其表面延伸的流动分流构件的第一构件和靠近第一构件设置的第二构件，其间限定在第二构件的表面与分流器的远端之间的间隙区域使得在第一和第二构件的表面之间形成流体路径，流体路径从上游区段流过间隙区域。第二构件被形成为在上游部分处限定双涡流室，在该部分处流体被引导以在允许流过间隙区域之前以涡流图案流动。

26. 发明授权

US08317467B2 Radial channel diffuser for steam turbine exhaust hood 失效
标题翻译：汽轮机排气罩径向通道扩散器
公开(公告)号：US08317467B2
公开(公告)日：2012-11-27
申请号：US12648721
申请日：2009-12-29
申请人： Prakash B. Dalsania , Joshy John
发明人： Prakash B. Dalsania , Joshy John
IPC分类号： F01D25/30
CPC分类号： F01D25/30
摘要： An exhaust hood for an axial steam turbine that includes a radial channel, downstream from the normal flow pattern. The radial channel guides the exhaust steam flow in upper half of the hood in the flow momentum direction. Due to this pattern of flow direction, vortex generation in upper exhaust hood is reduced and increased flow diffusion results. The geometric arrangement can eliminate the outer casing of the exhaust hood over the axial length of the turbine inner casing, allowing the turbine inner casing to be supported directly by a foundation for the steam turbine.
摘要翻译：一种用于轴向蒸汽轮机的排气罩，其包括在正常流动模式下游的径向通道。径向通道在流动动量方向引导罩的上半部分中的排气蒸汽流。由于流动方向的这种模式，上排气罩中的涡流产生减少，流量扩散增加。几何布置可以在涡轮机内壳的轴向长度上消除排气罩的外壳，允许涡轮机内壳由蒸汽轮机的基座直接支撑。

27. 发明申请

US20110248452A1 AXIALLY-ORIENTED CELLULAR SEAL STRUCTURE FOR TURBINE SHROUDS AND RELATED METHOD 有权
标题翻译：涡轮轴承的面向轴向的密封结构及相关方法
公开(公告)号：US20110248452A1
公开(公告)日：2011-10-13
申请号：US12757584
申请日：2010-04-09
申请人： Joshy JOHN , Sanjeev Kumar JAIN , Rajnikumar Nandalal SUTHAR
发明人： Joshy JOHN , Sanjeev Kumar JAIN , Rajnikumar Nandalal SUTHAR
IPC分类号： F16J15/447 , B23P11/00
CPC分类号： F01D11/127 , F05D2250/283 , Y10T29/49826
摘要： A seal system between a row of buckets supported on a machine rotor and a surrounding stationary casing or stator includes a tip shroud secured at radially outer tips of each of the buckets, the tip shroud formed with a radially-projecting rail. A cellular seal structure is supported in the stationary stator in radial opposition to the tip shroud and the rail. The seal structure has an annular array of individual cells formed to provide continuous, substantially horizontal flow passages devoid of any radial obstruction along substantially an entire axial length dimension of the cellular seal structure to prevent flow about the tip shroud from turning radially inwardly.
摘要翻译：支撑在机器转子和周围的固定壳体或定子之间的一排铲斗之间的密封系统包括固定在每个铲斗的径向外部尖端处的尖端罩，所述尖端护罩形成有径向突出的轨道。蜂窝密封结构在固定式定子中以尖端护罩和导轨的径向相反的方式支撑。密封结构具有单个单元的环形阵列，其形成为提供连续的，基本上水平的流动通道，其在多孔密封结构的基本上整个轴向长度尺寸处没有任何径向阻塞，以防止尖端护罩周围径向向内转动。

28. 发明申请

US20110085893A1 COUNTOURED HONEYCOMB SEAL FOR A TURBOMACHINE 有权
标题翻译：用于涡轮发动机的蜂鸣器
公开(公告)号：US20110085893A1
公开(公告)日：2011-04-14
申请号：US12576345
申请日：2009-10-09
申请人： Sanjeev Kumar Jain , Joshy John , Sachin Kumar Rai , Rajnikumar Nandalal Suthar
发明人： Sanjeev Kumar Jain , Joshy John , Sachin Kumar Rai , Rajnikumar Nandalal Suthar
IPC分类号： F01D11/12 , B23P11/00
CPC分类号： F01D11/127 , F05D2250/32 , F05D2250/71
摘要： A turbomachine includes a housing having an inner surface, a compressor, a turbine and a rotary member including a plurality of blade members configured as part of one of the compressor and the turbine. Each of the plurality of blade members includes a base portion and a tip portion. The turbomachine also includes a honeycomb seal member mounted to the inner surface of the housing adjacent the rotary member. The honeycomb seal member includes a contoured surface having formed therein a deformation zone. The deformation zone includes an inlet zone and an outlet zone. The inlet zone is spaced a first distance from the tip portion of each of the plurality of blade members and the outlet zone is spaced a second distance from the tip portion of each of the plurality of blade members. The second distance being substantially equal to or less than the first distance.
摘要翻译：涡轮机包括具有内表面的壳体，压缩机，涡轮机和旋转构件，其包括构造为压缩机和涡轮机之一的一部分的多个叶片构件。多个叶片构件中的每一个包括基部和尖端部。涡轮机还包括蜂窝密封构件，其安装在邻近旋转构件的壳体的内表面上。蜂窝状密封构件包括在其中形成有变形区域的轮廓表面。变形区包括入口区和出口区。入口区域与多个叶片构件中的每一个的顶端部分隔开第一距离，并且出口区域与多个叶片构件中的每一个的顶端部分间隔开第二距离。第二距离基本上等于或小于第一距离。

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