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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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Patent Agency Ranking
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：US11174735B2
公开(公告)日：2021-11-16
申请号：US16724852
申请日：2019-12-23
Applicant: General Electric Company
Inventor： Matthew Ryan Ferslew , Katherine Courtlyn MacManus , Srinivas Ravi , John Herbert Dimmick , Jonathan Michael Webster , Gang Liu
IPC: F01D5/00 , F01D5/02 , F01D25/00 , F04D29/04 , F04D29/044 , F04D29/054 , F16D1/02 , F01D11/12
Abstract: Shaft assemblies, turbomachines, and methods of servicing a turbomachine are provided. A shaft assembly includes a first shaft having a first rabbet annularly defined therein. The first rabbet includes a first axially extending face and a first radially extending face. A second shaft coupled to the first shaft. The second shaft includes a second rabbet annularly defined therein and positioned opposite the first rabbet. The second rabbet includes a second axially extending face and a second radially extending face. A patch ring is mounted between the first rabbet and the second rabbet. The patch ring includes a main body positioned between and in contact with the first axially extending face and the second axially extending face. A first arm extends radially outward from the main body, and a second arm extends radially inward from the main body.
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4.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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公开(公告)号：US20210189899A1
公开(公告)日：2021-06-24
申请号：US16724852
申请日：2019-12-23
Applicant: General Electric Company
Inventor： Matthew Ryan Ferslew , Katherine Courtlyn MacManus , Srinivas Ravi , John Herbert Dimmick , Jonathan Michael Webster , Gang Liu
Abstract: Shaft assemblies, turbomachines, and methods of servicing a turbomachine are provided. A shaft assembly includes a first shaft having a first rabbet annularly defined therein. The first rabbet includes a first axially extending face and a first radially extending face. A second shaft coupled to the first shaft. The second shaft includes a second rabbet annularly defined therein and positioned opposite the first rabbet. The second rabbet includes a second axially extending face and a second radially extending face. A patch ring is mounted between the first rabbet and the second rabbet. The patch ring includes a main body positioned between and in contact with the first axially extending face and the second axially extending face. A first arm extends radially outward from the main body, and a second arm extends radially inward from the main body.
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公开(公告)号：US10662793B2
公开(公告)日：2020-05-26
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.
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