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公开(公告)号：US10337345B2
公开(公告)日：2019-07-02
申请号：US14627431
申请日：2015-02-20
Applicant: General Electric Company
Abstract: A sealing system for a multi-stage turbine includes multiple interstage seal segments disposed circumferentially about a turbine rotor wheel assembly and extending axially between a forward turbine stage and an aft turbine stage. Each of the interstage seal segments includes a forward end portion including an outer seal surface and an inner support face, an aft end portion, including an outer seal surface and an inner support face and a main body portion extending axially from the forward end portion to the aft end. The main body portion includes at least two support webs coupling the outer seal surfaces and the inner support faces. The outer seal surfaces are configured to be retained in a radial direction by a land support on each of a forward and aft stage turbine buckets, such that substantially all the centrifugal load from the multiple interstage seal segments is transferred to the forward and aft stage turbine buckets. A method of assembling the sealing system is disclosed.
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公开(公告)号：US10100656B2
公开(公告)日：2018-10-16
申请号：US14834866
申请日：2015-08-25
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Stephen Francis Bancheri , Venkat Subramaniam Venkataramani , Glen Harold Kirby , Neelesh Nandkumar Sarawate , Nicholas Edward Antolino , Edip Sevincer , Anthony Christopher Marin
Abstract: A coated seal slot system for turbomachinery includes a first turbine component comprising a first groove having at least one first coating attached to at least a portion of the first groove of the first turbine component, a second turbine component comprising a second groove having at least one second coating attached to at least a portion of the second groove of the second turbine component. The first and the second turbine components are disposable adjacent to each other with the first groove having the first coating and the second groove having the second coating together forming a coated seal slot extending across a gap between the first turbine component and the second turbine component. A seal is disposable in the coated seal slot and extendable across the gap between the first and the second turbine components and engageable with the first coating and the second coating to inhibit leakage of gas through the gap.
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公开(公告)号：US20160153302A1
公开(公告)日：2016-06-02
申请号：US14556305
申请日：2014-12-01
Applicant: General Electric Company
Abstract: A sealing system for a multi-stage turbine includes multiple first interstage seal subsystems disposed circumferentially about a rotor wheel shaft of the multi-stage turbine and extending axially between a first turbine stage and a second turbine stage of the multi-stage turbine. Each of the first interstage seal subsystems includes multiple near flow path seal segments. The first interstage seal subsystem also includes a forward coverplate disposed axially between a first turbine wheel of the first turbine stage and the near flow path seal segment and an aft coverplate disposed axially between the near flow path seal segment and a second turbine wheel of the second turbine stag. Further, each of the forward coverplate and the aft coverplate extends radially to a first stage bucket and a second stage bucket respectively.
Abstract translation: 用于多级涡轮机的密封系统包括多个第一级间密封子系统，其围绕多级涡轮机的转子轮轴周向设置，并且在多级涡轮机的第一涡轮级和第二涡轮级之间轴向延伸。 第一级间密封子系统中的每一个包括多个近流路密封段。 第一级间密封子系统还包括轴向设置在第一涡轮机台的第一涡轮机叶轮和近流动路径密封段之间的前盖板，以及轴向设置在近流路密封段和第二涡轮机叶轮的第二涡轮机叶轮之间的后盖板 涡轮机 此外，前盖板和后盖板中的每一个分别径向延伸到第一级铲斗和第二级铲斗。
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公开(公告)号：US20150354374A1
公开(公告)日：2015-12-10
申请号：US14299538
申请日：2014-06-09
Applicant: General Electric Company
Inventor： Douglas Carl Hofer , Rajiv Sampath , Edip Sevincer , Ganesh Krishnamoorthy , Chiranjeev Singh Kalra
CPC classification number: F01D5/225 , B23P15/006 , F01D5/34 , F05D2230/11 , F05D2230/25 , F05D2230/53 , Y10T29/49323
Abstract: A turbine blisk is provided. The turbine blisk includes an inner rim, a plurality of adjacent rotor blades extending radially outward from said inner rim, a shroud segment integrally coupled to each of the plurality of adjacent rotor blades, thereby forming a plurality of adjacent shroud segments, and a gap defined between each of the adjacent shroud segments. The gap has a geometry that facilitates interlocking the plurality of adjacent shroud segments when a torsional force is applied to the plurality of adjacent rotor blades.
Abstract translation: 提供涡轮叶片。 涡轮叶片包括内边缘，从所述内边缘径向向外延伸的多个相邻的转子叶片，与多个相邻的转子叶片中的每一个整体连接的护罩段，从而形成多个相邻的护罩段， 在每个相邻的护罩段之间。 当扭转力施加到多个相邻的转子叶片时，该间隙具有便于将多个相邻的护罩段互锁的几何形状。
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公开(公告)号：US20190128126A1
公开(公告)日：2019-05-02
申请号：US15973364
申请日：2018-05-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Douglas Carl Hofer , Rajiv Sampath , Edip Sevincer , Ganesh Krishnamoorthy , Chiranjeev Singh Kalra
Abstract: A turbine blisk is provided. The turbine blisk includes an inner rim, a plurality of adjacent rotor blades extending radially outward from said inner rim, a shroud segment integrally coupled to each of the plurality of adjacent rotor blades, thereby forming a plurality of adjacent shroud segments, and a gap defined between each of the adjacent shroud segments. The gap has a geometry that facilitates interlocking the plurality of adjacent shroud segments when a torsional force is applied to the plurality of adjacent rotor blades.
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Patent Agency Ranking
公开(公告)号：US20180003067A1
公开(公告)日：2018-01-04
申请号：US15397278
申请日：2017-01-03
Applicant: General Electric Company
Inventor： Rahul Anil Bidkar , Azam Mihir Thatte , Jifeng Wang , Xiaoqing Zheng , Edip Sevincer
CPC classification number: F01D11/003 , F01D5/02 , F01D9/041 , F01D25/16 , F01D25/183 , F01D25/22 , F05D2220/32 , F05D2230/60 , F05D2240/55 , F16J15/342 , F16J15/3468 , F16J15/3488 , F16J15/442
Abstract: A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, and a face seal assembly including a first segmented seal ring and a second segmented seal ring. The first segmented seal ring includes a plurality of joints and a first flat-contact surface and the second segmented seal ring includes a plurality of segment ends and a second flat-contact surface. One of the first and second segmented seal rings includes a seal bearing face. The second segmented seal ring is coupled to the first segmented seal ring such that the second flat-contact surface is in contact with the first flat-contact surface. The plurality of segment ends is circumferentially offset from the plurality of joints. The first segmented seal ring is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces.
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公开(公告)号：US20170370239A1
公开(公告)日：2017-12-28
申请号：US15189122
申请日：2016-06-22
Applicant: General Electric Company
Inventor： Venkat Subramaniam Venkataramani , Neelesh Nandkumar Sarawate , Anthony Christopher Marin , Wayne Charles Hasz , Stephen Francis Bancheri , Edip Sevincer
CPC classification number: F01D11/005 , F01D11/08 , F01D25/005 , F05D2240/11 , F05D2240/55 , F05D2240/57 , F05D2250/62 , F05D2300/21 , F05D2300/2112 , F05D2300/2118 , F05D2300/2283 , F05D2300/5021 , F05D2300/5023 , F05D2300/518 , F05D2300/6033 , F05D2300/609 , F16J15/102
Abstract: A turbine system including a sealing component is presented. The sealing component includes a ceramic material. The ceramic material includes grains having an average grain size of less than 10 microns. A turbine shroud assembly including the sealing component is also presented.
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公开(公告)号：US11181002B2
公开(公告)日：2021-11-23
申请号：US15280067
申请日：2016-09-29
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Venkat Subramaniam Venkataramani , Anthony Christopher Marin , Stephen Francis Bancheri , Larry Steven Rosenzweig , Edip Sevincer
Abstract: A turbine system including a sealing component is presented. The sealing component is positioned in a gap between adjacent turbine components of the turbine system. The sealing component includes a metallic shim including a high-temperature-resistant alloy in a single crystal form. A turbine shroud assembly including the sealing component is also presented.
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公开(公告)号：US10415707B2
公开(公告)日：2019-09-17
申请号：US15397317
申请日：2017-01-03
Applicant: General Electric Company
Inventor： Rahul Anil Bidkar , Azam Mihir Thatte , Jifeng Wang , Xiaoqing Zheng , Edip Sevincer
Abstract: A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, a face seal assembly, a first pressure cavity, and a second pressure cavity. The face seal assembly includes a seal ring including a seal bearing face, a first pressure cavity, and a plurality of isolated hydrostatic ports extending from the first pressure cavity to the seal bearing face. The face seal assembly is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces. The second and third pressure cavities are defined by the stator, the rotor, and the face seal assembly. The third pressure cavity is disposed downstream of the second pressure cavity with reference to flow of a process fluid along the stator and rotor. The first pressure cavity is isolated from the second and third pressure cavities.
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10.发明申请公开(公告)号：US20160245106A1
公开(公告)日：2016-08-25
申请号：US14627431
申请日：2015-02-20
Applicant: General Electric Company
CPC classification number: F01D11/006 , F01D5/06 , F01D5/12 , F01D5/3007 , F01D11/001 , F01D11/005 , F01D11/02 , F05D2220/30 , F05D2230/60 , F05D2240/24 , F05D2240/55 , F05D2260/97
Abstract: A sealing system for a multi-stage turbine includes multiple interstage seal segments disposed circumferentially about a turbine rotor wheel assembly and extending axially between a forward turbine stage and an aft turbine stage. Each of the interstage seal segments includes a forward end portion including an outer seal surface and an inner support face, an aft end portion, including an outer seal surface and an inner support face and a main body portion extending axially from the forward end portion to the aft end. The main body portion includes at least two support webs coupling the outer seal surfaces and the inner support faces. The outer seal surfaces are configured to be retained in a radial direction by a land support on each of a forward and aft stage turbine buckets, such that substantially all the centrifugal load from the multiple interstage seal segments is transferred to the forward and aft stage turbine buckets. A method of assembling the sealing system is disclosed.
Abstract translation: 用于多级涡轮机的密封系统包括围绕涡轮机转子轮组件周向设置并且在正向涡轮机台架和后涡轮机台架之间轴向延伸的多个级间密封段。 每个级间密封段包括前端部分，其包括外密封表面和内支撑面，后端部分包括外密封表面和内支撑面以及主体部分，其从前端部轴向延伸到 后端 主体部分包括联接外密封表面和内支撑面的至少两个支撑腹板。 外密封表面被构造成通过在前级和后级涡轮机叶片中的每一个上的陆部支撑件沿径向保持，使得来自多个级间密封段的基本上所有的离心载荷被传递到前级和后级涡轮机 水桶 公开了一种组装密封系统的方法。
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