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1. 发明申请

US20130091865A1 EXHAUST GAS DIFFUSER 审中-公开
标题翻译：排气歧管
公开(公告)号：US20130091865A1
公开(公告)日：2013-04-18
申请号：US13275040
申请日：2011-10-17
申请人： Deepesh Dinesh Nanda , Joshy John
发明人： Deepesh Dinesh Nanda , Joshy John
IPC分类号： F02C3/04 , F01D25/30
CPC分类号： F01D25/30 , F01D9/065
摘要： An exhaust gas diffuser is provided and includes a peripheral body, a center body, formed to define an interior and disposed within the peripheral body to define an annulus between the peripheral body and the center body through which a first fluid flows along a main flow direction, a plurality of first members, each of which is respectively coupled to the peripheral body and the center body, to support the center body within the peripheral body and a plurality of second members, each of which extends across the annulus from the peripheral body to the center body downstream from the plurality of the first members relative to the main flow direction, to transport a second fluid to the center body interior. The plurality of the second members is circumferentially clocked relative to the plurality of the first members.
摘要翻译：设置排气扩散器，其包括周边体，中心体，其形成为限定内部并且设置在周边本体内，以限定周边本体与中心体之间的环形空间，第一流体沿着主流动方向，多个第一构件，每个第一构件分别联接到周边主体和中心体，以将中心体支撑在周边主体内;以及多个第二构件，每个第二构件从周向体延伸穿过环形空间，中心体从多个第一构件相对于主流动方向下游，以将第二流体输送到中心体内部。多个第二构件相对于多个第一构件周向地定时。

2. 发明申请

US20130167551A1 TURBINE TO OPERATE AT PART-LOAD 有权
标题翻译：涡轮在部分负载下运行
公开(公告)号：US20130167551A1
公开(公告)日：2013-07-04
申请号：US13343269
申请日：2012-01-04
申请人： Moorthi Subramaniyan , Umesh Garg , Joshy John , Lakshmanan Valliappan
发明人： Moorthi Subramaniyan , Umesh Garg , Joshy John , Lakshmanan Valliappan
IPC分类号： F02C9/18
CPC分类号： F02C9/18 , F01D5/18 , F01D5/187 , F01D9/04 , F01D9/065 , F01D25/08 , F02C1/04 , F02C7/14
摘要： A turbine includes a compressor to intake a fluid and to compress the fluid, a combustion chamber to heat the fluid from the compressor, a turbine section to rotate a shaft with the heated fluid from the combustion chamber, and a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section.
摘要翻译：涡轮机包括用于吸入流体并压缩流体的压缩机，用于加热来自压缩机的流体的燃烧室，用于使来自燃烧室的加热流体旋转轴的涡轮部分，以及旁路回路以产生旁路通过从压缩机中除去一部分流体来加热旁路流，并将旁路流插入到涡轮部分。

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. 发明授权

US08434766B2 Turbine engine seals 有权
标题翻译：涡轮发动机密封
公开(公告)号：US08434766B2
公开(公告)日：2013-05-07
申请号：US12858701
申请日：2010-08-18
申请人： Xiaoqiang Zeng , Jonathon Edward Slepski , Tao Guo , Joshy John , Sudhakar Neeli
发明人： Xiaoqiang Zeng , Jonathon Edward Slepski , Tao Guo , Joshy John , Sudhakar Neeli
IPC分类号： F16J15/447
CPC分类号： F01D11/001 , F01D11/02 , F05D2250/232 , F16J15/441 , F16J15/4472
摘要： A seal is provided for preventing axial leakage through a radial gap between a stationary structure and a rotating structure. The radial gap is defined by an inner radial surface opposing an outer radial surface across the radial gap. The seal includes at least one land disposed on one of the inner radial surface and outer radial surface. At least one first tooth and at least one second tooth project from the other of the radial surfaces. The second tooth is shorter than the first tooth. At least one of the first tooth and second tooth, is configured to extend at an angle upstream. This angle is defined between a radial surface from which the first or second tooth projects and an upstream surface of the same tooth. The angle is less than or equal to about 80 degrees.
摘要翻译：提供密封件以防止通过固定结构和旋转结构之间的径向间隙的轴向泄漏。径向间隙由跨越径向间隙的与外径向表面相对的内径向表面限定。密封件包括设置在内径向表面和外径向表面中的一个上的至少一个区域。至少一个第一齿和至少一个第二齿从另一个径向表面突出。第二个齿比第一个牙齿短。第一齿和第二齿中的至少一个构造成在上游以一定角度延伸。该角度限定在第一或第二齿突出的径向表面与同一牙齿的上游表面之间。该角度小于或等于约80度。

5. 发明授权

US08740563B2 Sealing assembly for use in turbomachines and methods of assembling same 有权
标题翻译：用于涡轮机的密封组件及其组装方法
公开(公告)号：US08740563B2
公开(公告)日：2014-06-03
申请号：US12951128
申请日：2010-11-22
申请人： Sudhakar Neeli , Joshy John
发明人： Sudhakar Neeli , Joshy John
IPC分类号： F04D29/10
CPC分类号： F01D11/02 , F05D2220/31 , F05D2230/60 , F16J15/4472
摘要： A method of assembling a sealing assembly for use in a turbomachine includes providing a rotatable element that includes an end portion with a plurality of grooves partially extending circumferentially about a portion of an outer surface of the end portion of the rotatable element. The method also includes providing a stationary portion that includes an upper section and a lower section. The method further includes inserting at least a portion of the end portion of the rotatable element into the lower section. The method also includes coupling the upper section to the lower section, thereby defining a rotor shaft cavity. The end portion of the rotatable element at least partially extends through the rotor shaft cavity, thereby defining a clearance between the end portion of the rotatable element and the stationary portion.
摘要翻译：一种组装用于涡轮机的密封组件的方法包括提供可旋转元件，该可旋转元件包括具有多个槽的端部，所述多个槽部围绕可旋转元件的端部的外表面的一部分圆周地延伸。该方法还包括提供包括上部和下部的固定部分。该方法还包括将可旋转元件的端部的至少一部分插入下部。该方法还包括将上部部分联接到下部部分，从而限定转子轴腔。可旋转元件的端部至少部分地延伸穿过转子轴腔，从而在可旋转元件的端部与固定部分之间形成间隙。

6. 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。

7. 发明授权

US09169782B2 Turbine to operate at part-load 有权
标题翻译：涡轮机在部分负载下运行
公开(公告)号：US09169782B2
公开(公告)日：2015-10-27
申请号：US13343269
申请日：2012-01-04
申请人： Moorthi Subramaniyan , Umesh Garg , Joshy John , Lakshmanan Valliappan
发明人： Moorthi Subramaniyan , Umesh Garg , Joshy John , Lakshmanan Valliappan
IPC分类号： F02C9/18 , F01D5/18 , F01D9/06 , F02C7/14
CPC分类号： F02C9/18 , F01D5/18 , F01D5/187 , F01D9/04 , F01D9/065 , F01D25/08 , F02C1/04 , F02C7/14
摘要： A turbine includes a compressor to intake a fluid and to compress the fluid, a combustion chamber to heat the fluid from the compressor, a turbine section to rotate a shaft with the heated fluid from the combustion chamber, and a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section.
摘要翻译：涡轮机包括用于吸入流体并压缩流体的压缩机，用于加热来自压缩机的流体的燃烧室，用于使来自燃烧室的加热流体旋转轴的涡轮部分，以及旁路回路以产生旁路通过从压缩机中除去一部分流体来加热旁路流，并将旁路流插入到涡轮部分。

8. 发明申请

US20130064638A1 Boundary Layer Blowing Using Steam Seal Leakage Flow 审中-公开
标题翻译：使用蒸汽密封泄漏流动的边界层吹扫
公开(公告)号：US20130064638A1
公开(公告)日：2013-03-14
申请号：US13227574
申请日：2011-09-08
申请人： Moorthi Subramaniyan , Joshy John
发明人： Moorthi Subramaniyan , Joshy John
IPC分类号： F01D11/00 , F01D25/24
CPC分类号： F01D25/305 , F01D11/04 , F05D2220/31 , F05D2250/324
摘要： A steam turbine includes a final turbine stage, a flow diffuser receiving a main flow from the final turbine stage, a diverging wall in the axial or radial flow diffuser that extends from a diffuser inlet to a diffuser exit, and a centerbody in the axial or radial flow diffuser. An opening is provided in the diverging wall and an opening is provided in the centerbody for fluidically actuating the main flow. The openings are located downstream from the diffuser inlet and upstream from a point where boundary layer separation would occur along the walls in a diffuser without the openings. A plurality of openings are provided in the diverging wall, and an end packing seal is positioned adjacent an end portion of the final turbine stage. An annular manifold collects fluid from leakage flow from the end packing seal and distributes the leakage flow to the openings.
摘要翻译：蒸汽涡轮机包括最终的涡轮级，流体扩散器，其接收来自最终涡轮级的主流，在轴向或径向流扩散器中的扩散壁，其从扩散器入口延伸到扩散器出口，以及轴向或中心体径向流扩散器。在发散壁中设置有开口，并且在中心体中设置开口以流体地驱动主流。开口位于扩散器入口的下游，并且在不具有开口的扩散器中沿着壁的边界层分离的点的上游。多个开口设置在发散壁中，并且端部填料密封件邻近最终涡轮级的端部定位。环形歧管从来自端部密封件的泄漏流收集流体，并将泄漏流分配到开口。

9. 发明申请

US20120126486A1 SEALING ASSEMBLY FOR USE IN TURBOMACHINES AND METHODS OF ASSEMBLING SAME 有权
标题翻译：用于涡轮机的密封组件和组装方法
公开(公告)号：US20120126486A1
公开(公告)日：2012-05-24
申请号：US12951128
申请日：2010-11-22
申请人： Sudhakar Neeli , Joshy John
发明人： Sudhakar Neeli , Joshy John
IPC分类号： F16J15/447 , B23P11/00
CPC分类号： F01D11/02 , F05D2220/31 , F05D2230/60 , F16J15/4472
摘要： A method of assembling a sealing assembly for use in a turbomachine includes providing a rotatable element that includes an end portion with a plurality of grooves partially extending circumferentially about a portion of an outer surface of the end portion of the rotatable element. The method also includes providing a stationary portion that includes an upper section and a lower section. The method further includes inserting at least a portion of the end portion of the rotatable element into the lower section. The method also includes coupling the upper section to the lower section, thereby defining a rotor shaft cavity. The end portion of the rotatable element at least partially extends through the rotor shaft cavity, thereby defining a clearance between the end portion of the rotatable element and the stationary portion.
摘要翻译：一种组装用于涡轮机的密封组件的方法包括提供可旋转元件，该可旋转元件包括具有多个槽的端部，所述多个槽部围绕可旋转元件的端部的外表面的一部分圆周地延伸。该方法还包括提供包括上部和下部的固定部分。该方法还包括将可旋转元件的端部的至少一部分插入下部。该方法还包括将上部部分联接到下部部分，从而限定转子轴腔。可旋转元件的端部至少部分地延伸穿过转子轴腔，从而在可旋转元件的端部与固定部分之间形成间隙。

10. 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。

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