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1. 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。

2. 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。

3. 发明授权

US08444372B2 Passive cooling system for a turbomachine 有权
标题翻译：涡轮机的被动冷却系统
公开(公告)号：US08444372B2
公开(公告)日：2013-05-21
申请号：US13022039
申请日：2011-02-07
申请人： Rajnikumar Nandalal Suthar , Sanjeev Kumar Jain , Joshy John
发明人： Rajnikumar Nandalal Suthar , Sanjeev Kumar Jain , Joshy John
IPC分类号： F04D21/00
CPC分类号： F01D11/10 , F01D25/12
摘要： A turbomachine includes a housing having an outer surface and an inner surface that defines an interior portion. The housing includes a fluid plenum. A rotating member is arranged within the housing. The rotating member includes at least one bucket having a base portion and a tip portion. A stationary member is mounted to the inner surface of the housing adjacent the tip portion of the at least one bucket. At least one fluid passage passes through at least a portion of the stationary member. The at least one fluid passage includes a fluid inlet fluidly coupled to the fluid plenum and a fluid outlet exposed to the interior portion. The fluid outlet being configured and disposed to direct a flow of fluid toward the tip portion of the at least one bucket.
摘要翻译：涡轮机包括具有外表面和限定内部部分的内表面的壳体。壳体包括流体增压室。旋转构件设置在壳体内。旋转构件包括具有基部和尖端部分的至少一个铲斗。固定构件安装到邻近所述至少一个铲斗的末端部分的所述壳体的内表面。至少一个流体通道穿过固定构件的至少一部分。至少一个流体通道包括流体连接到流体室的流体入口和暴露于内部的流体出口。流体出口被构造和设置成将流体流引向至少一个桶的顶端部分。

4. 发明申请

US20120201650A1 PASSIVE COOLING SYSTEM FOR A TURBOMACHINE 有权
标题翻译：用于涡轮机的被动冷却系统
公开(公告)号：US20120201650A1
公开(公告)日：2012-08-09
申请号：US13022039
申请日：2011-02-07
申请人： Rajnikumar Nandalal Suthar , Sanjeev Kumar Jain , Joshy John
发明人： Rajnikumar Nandalal Suthar , Sanjeev Kumar Jain , Joshy John
IPC分类号： F01D9/02
CPC分类号： F01D11/10 , F01D25/12
摘要： A turbomachine includes a housing having an outer surface and an inner surface that defines an interior portion. The housing includes a fluid plenum. A rotating member is arranged within the housing. The rotating member includes at least one bucket having a base portion and a tip portion. A stationary member is mounted to the inner surface of the housing adjacent the tip portion of the at least one bucket. At least one fluid passage passes through at least a portion of the stationary member. The at least one fluid passage includes a fluid inlet fluidly coupled to the fluid plenum and a fluid outlet exposed to the interior portion. The fluid outlet being configured and disposed to direct a flow of fluid toward the tip portion of the at least one bucket.
摘要翻译：涡轮机包括具有外表面和限定内部部分的内表面的壳体。壳体包括流体增压室。旋转构件设置在壳体内。旋转构件包括具有基部和尖端部分的至少一个铲斗。固定构件安装到邻近所述至少一个铲斗的末端部分的所述壳体的内表面。至少一个流体通道穿过固定构件的至少一部分。至少一个流体通道包括流体连接到流体室的流体入口和暴露于内部的流体出口。流体出口被构造和设置成将流体流引向至少一个桶的顶端部分。

5. 发明授权

US08444371B2 Axially-oriented cellular seal structure for turbine shrouds and related method 有权
标题翻译：涡轮机护罩的轴向定向多孔密封结构及相关方法
公开(公告)号：US08444371B2
公开(公告)日：2013-05-21
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： F01D5/08
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。

6. 发明申请

US20120195742A1 TURBINE BUCKET FOR USE IN GAS TURBINE ENGINES AND METHODS FOR FABRICATING THE SAME 审中-公开
标题翻译：用于气体涡轮发动机的涡轮马桶及其制造方法
公开(公告)号：US20120195742A1
公开(公告)日：2012-08-02
申请号：US13015747
申请日：2011-01-28
申请人： Sanjeev Kumar Jain , Rajnikumar Nandalal Suthar , Matthew Durham Collier
发明人： Sanjeev Kumar Jain , Rajnikumar Nandalal Suthar , Matthew Durham Collier
IPC分类号： F01D11/08 , B22C9/10 , B22D25/02
CPC分类号： F01D5/225 , F01D11/122 , F05D2250/34 , F05D2250/38
摘要： A turbine bucket for use with a turbine engine. The turbine bucket includes a dovetail that is coupled to a rotor assembly that is positioned within a turbine casing. A platform extends from the dovetail. An airfoil extends from the platform. The airfoil includes a root end and a tip end. The tip end extends outwardly from the root end towards the turbine casing. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. A first shroud rail extending a first radial distance from the shroud plate towards the turbine casing. A second shroud rail extends a second radial distance from the shroud plate towards the turbine casing that is different than the first radial distance.
摘要翻译：用于涡轮发动机的涡轮机桶。涡轮机桶包括燕尾榫，其连接到位于涡轮机外壳内的转子组件。一个平台从燕尾榫延伸出来。机翼从平台延伸。翼型件包括根端和尖端。尖端从根端朝向涡轮机壳体向外延伸。尖端罩从尖端延伸。尖端护罩包括护罩板。第一护罩导轨，其从罩板向涡轮机壳体延伸第一径向距离。第二护栏导轨从罩板朝着与第一径向距离不同的涡轮机壳体延伸第二径向距离。

7. 发明申请

US20110103966A1 FLOW BALANCING SLOT 有权
标题翻译：流平衡槽
公开(公告)号：US20110103966A1
公开(公告)日：2011-05-05
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： B64C11/16
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。

8. 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。

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