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公开(公告)号：US20200378268A1
公开(公告)日：2020-12-03
申请号：US16994751
申请日：2020-08-17
Applicant: General Electric Company
IPC: F01D9/04 , C04B35/515 , C04B35/571 , C04B35/573 , C04B37/00 , F01D11/00 , F01D25/00 , F01D25/24
Abstract: Flow path assemblies and methods for forming such flow path assemblies for gas turbine engines are provided. For example, a flow path assembly for a gas turbine engine has a boundary structure, an airfoil, and a locking feature. The boundary structure and the airfoil are formed from a composite material. The boundary structure defines an opening and a cutout proximate the opening, and the airfoil is sized to fit within the opening of the boundary structure. The locking feature is received within the cutout defined by the boundary structure to interlock the airfoil with the boundary structure.
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公开(公告)号：US20200318831A1
公开(公告)日：2020-10-08
申请号：US16907013
申请日：2020-06-19
Applicant: General Electric Company
Inventor： Jinjie Shi , Stephen Gerard Schadewald , Jason Paul Hoppa , Kirk Douglas Gallier , Christopher Edward Wolfe , Robert Proctor
Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.
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公开(公告)号：US10746035B2
公开(公告)日：2020-08-18
申请号：US15690346
申请日：2017-08-30
Applicant: General Electric Company
IPC: F01D9/04 , F01D11/00 , F01D25/00 , F01D25/24 , C04B35/573 , C04B35/80 , C04B37/00 , C04B35/571
Abstract: Flow path assemblies and methods for forming such flow path assemblies for gas turbine engines are provided. For example, a method for assembling an airfoil with a boundary structure to form a flow path assembly is provided. The method includes machining an opening into the boundary structure. The opening is sized to receive an airfoil or other component. The method also includes machining a cutout into the boundary structure proximate the opening. A locking feature is inserted into the cutout. When the airfoil is inserted into the opening, the locking feature interlocks the airfoil with the boundary structure. To seal the airfoil with the boundary structure, the airfoil is pressed against or into the boundary structure. When the airfoil is pressed, the locking feature is compressed such that a seal is formed between the airfoil and the boundary structure to seal the flow path assembly.
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公开(公告)号：US20200040769A1
公开(公告)日：2020-02-06
申请号：US16593094
申请日：2019-10-04
Applicant: General Electric Company
Inventor： Kirk Douglas Gallier , Charles William Craig, III
Abstract: Shrouds and shroud segments for gas turbine engines are provided. In one embodiment, a shroud segment for a gas turbine engine having a rotor blade stage and a nozzle stage is provided. The shroud segment comprises a forward end defining an outer wall of the rotor blade stage and an aft end defining an outer wall of the nozzle stage. The aft end defines at least a portion of an opening therethrough for receipt of a nozzle, and the forward end and the aft end form a single, continuous component. In another embodiment, a gas turbine engine is provided, having a shroud with a forward end positioned near a leading edge of a plurality of rotor blades of a rotor blade stage and an aft end positioned near a trailing edge of a plurality of nozzles of a nozzle stage. Methods of assembling a gas turbine engine also are provided.
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公开(公告)号：US10519779B2
公开(公告)日：2019-12-31
申请号：US15071443
申请日：2016-03-16
Applicant: General Electric Company
Inventor： Robert Charles Groves, II , Kirk Douglas Gallier , Ronald Scott Bunker
Abstract: An airfoil having a radial direction extending away from an engine axis is provided. The airfoil includes an airfoil wall having an airfoil outer surface and an airfoil inner surface, with the airfoil extending radially from a first end to a second end. The airfoil defines a cooling channel interior to the inner surface with a thickness being defined between the airfoil outer surface and the airfoil inner surface. The thickness varies in the radial direction from the first end to the second end along at least one radial cross-section of the airfoil. A turbine nozzle of a turbine engine is also provided, which may include an outer band, an inner band, and the airfoil.
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Patent Agency Ranking
公开(公告)号：US10253637B2
公开(公告)日：2019-04-09
申请号：US14967069
申请日：2015-12-11
Applicant: General Electric Company
Inventor： Eric Joseph Schroeder , Paul Hadley Vitt , Timothy John Swenson , Kirk Douglas Gallier , Aspi Rustom Wadia
Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
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公开(公告)号：US20190063246A1
公开(公告)日：2019-02-28
申请号：US15690346
申请日：2017-08-30
Applicant: General Electric Company
CPC classification number: F01D9/044 , C04B35/571 , C04B35/573 , C04B35/806 , C04B37/001 , C04B2235/48 , C04B2237/38 , C04B2237/61 , C04B2237/84 , F01D9/041 , F01D11/003 , F01D11/005 , F01D25/005 , F01D25/24 , F05D2220/32 , F05D2230/10 , F05D2230/23 , F05D2230/31 , F05D2230/60 , F05D2250/75 , F05D2260/30 , F05D2260/36 , F05D2300/603 , F05D2300/6033
Abstract: Flow path assemblies and methods for forming such flow path assemblies for gas turbine engines are provided. For example, a method for assembling an airfoil with a boundary structure to form a flow path assembly is provided. The method includes machining an opening into the boundary structure. The opening is sized to receive an airfoil or other component. The method also includes machining a cutout into the boundary structure proximate the opening. A locking feature is inserted into the cutout. When the airfoil is inserted into the opening, the locking feature interlocks the airfoil with the boundary structure. To seal the airfoil with the boundary structure, the airfoil is pressed against or into the boundary structure. When the airfoil is pressed, the locking feature is compressed such that a seal is formed between the airfoil and the boundary structure to seal the flow path assembly.
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公开(公告)号：US20170362943A1
公开(公告)日：2017-12-21
申请号：US15182651
申请日：2016-06-15
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Kirk Douglas Gallier , Ronald Scott Bunker
CPC classification number: F01D5/282 , F01D5/187 , F05D2260/941 , F05D2300/5024 , F05D2300/522 , F05D2300/6033 , Y02T50/672 , Y02T50/676
Abstract: A component for a gas turbine engine includes a first region formed substantially of a first CMC material, wherein first region defines a first thermal conductivity. The component further includes a second region formed substantially of a second CMC material, wherein the second region defines a second thermal conductivity. Further, the component defines a thickness and the first region is positioned adjacent to the second region along the thickness, wherein the first thermal conductivity is different than the second thermal conductivity to alert a thermal profile of the component.
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69.发明授权Metalized ceramic leading edge nozzle Kiels for high-temperature turbine applications 有权金属化陶瓷前缘喷嘴Kiels用于高温涡轮机应用公开(公告)号：US09128005B2
公开(公告)日：2015-09-08
申请号：US13632842
申请日：2012-10-01
Applicant: General Electric Company
Abstract: A pressure probe includes an elongated cable provided with a sensing tip, a portion of the elongated cable and sensing tip enclosed within a ceramic shroud, the ceramic shroud at least partially formed of a metalized ceramic material.
Abstract translation: 压力探测器包括细长电缆，其设有感测尖端，细长电缆的一部分和包围在陶瓷罩内的感测尖端，陶瓷护罩至少部分由金属化陶瓷材料形成。
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70.发明申请METALIZED CERAMIC LEADING EDGE NOZZLE KIELS FOR HIGH-TEMPERATURE TURBINE APPLICATIONS 有权用于高温涡轮机应用的金属化陶瓷顶尖喷嘴公开(公告)号：US20140090457A1
公开(公告)日：2014-04-03
申请号：US13632842
申请日：2012-10-01
Applicant: General Electric Company
IPC: G01M15/14
Abstract: A pressure probe includes an elongated cable provided with a sensing tip, a portion of the elongated cable and sensing tip enclosed within a ceramic shroud, the ceramic shroud at least partially formed of a metalized ceramic material.
Abstract translation: 压力探测器包括细长电缆，其设有感测尖端，细长电缆的一部分和包围在陶瓷罩内的感测尖端，陶瓷护罩至少部分由金属化陶瓷材料形成。
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