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公开(公告)号：US10287886B2
公开(公告)日：2019-05-14
申请号：US15273340
申请日：2016-09-22
Applicant: General Electric Company
Inventor： Paul Griffin Delvernois , Patrick Daniel Noble
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US09664058B2
公开(公告)日：2017-05-30
申请号：US14587714
申请日：2014-12-31
Applicant: General Electric Company
CPC classification number: F01D11/008 , F01D5/3007 , F04D29/164 , F04D29/321 , F04D29/322 , F04D29/329 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.
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公开(公告)号：US20180080328A1
公开(公告)日：2018-03-22
申请号：US15273340
申请日：2016-09-22
Applicant: General Electric Company
Inventor： Paul Griffin DeIvernois , Patrick Daniel Noble
IPC: F01D5/14
CPC classification number: F01D5/141 , F04D29/324 , F04D29/544 , F05D2250/74 , Y02T50/673
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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Patent Agency Ranking
公开(公告)号：US20160186591A1
公开(公告)日：2016-06-30
申请号：US14587714
申请日：2014-12-31
Applicant: General Electric Company
CPC classification number: F01D11/008 , F01D5/3007 , F04D29/164 , F04D29/321 , F04D29/322 , F04D29/329 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.
Abstract translation: 一种具有流路的燃气轮机，其具有转子组件，该转子组件包括：第一转子轮，其支撑具有限定所述流路内边界的第一轴向部分的平台的第一转子叶片; 支撑第二转子叶片的第二转子轮，所述第二转子叶片具有限定所述流动路径的内边界的第二轴向部分的平台; 以及环形填料，其包括外侧表面，所述外侧表面限定出现在所述流动路径的内边界的所述第一轴向部分和所述第二轴向部分之间的所述流动路径的内边界的第三轴向部分的至少一部分。 第一转子轮可以包括用于轴向接合形成在第一转子叶片的径向最内表面上的配合表面的轴向连接器和形成在环形填料的径向最内表面上的配合表面。
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公开(公告)号：US20150118055A1
公开(公告)日：2015-04-30
申请号：US14068456
申请日：2013-10-31
Applicant: General Electric Company
Inventor： Patrick Daniel Noble
CPC classification number: F01D5/3007 , F01D5/22 , F01D11/006 , F05D2220/32 , F05D2230/60 , F05D2240/80 , Y02T50/672 , Y10T29/49321
Abstract: A rotor assembly includes a rotor disc including a plurality of circumferentially-spaced diskposts and a plurality of dovetail slots. Each dovetail slot is defined between a pair of circumferentially-adjacent diskposts. A plurality of rotor blades are coupled to the rotor disc. Each rotor blade includes a dovetail portion that is configured to slidably engage a respective dovetail slot. A plurality of platform sections are coupled to the rotor disc such that each platform section is adjacent a respective rotor blade. Each platform section includes a diskpost slot that is configured to receive one of the plurality of diskposts such that each dovetail slot receives a respective dovetail portion and at least a portion of at least one of the platform sections adjacent the rotor blade.
Abstract translation: 转子组件包括转子盘，该转子盘包括多个周向间隔开的柱状物和多个燕尾槽。 每个燕尾槽被定义在一对周向相邻的骨架柱之间。 多个转子叶片联接到转子盘。 每个转子叶片包括燕尾部分，其构造成可滑动地接合相应的燕尾槽。 多个平台部分联接到转子盘，使得每个平台部分相邻于相应的转子叶片。 每个平台部分包括一个被配置成接收多个磁盘阵列之一的磁盘空间插槽，使得每个燕尾槽容纳相应的燕尾部分和与转子叶片相邻的至少一个平台部分的至少一部分。
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公开(公告)号：US11333026B2
公开(公告)日：2022-05-17
申请号：US16883158
申请日：2020-05-26
Applicant: General Electric Company
Inventor： Jeremy Peter Latimer , Patrick Daniel Noble
IPC: F01D5/22
Abstract: A vibration-damping system for turbomachine blade(s) in a turbomachine is provided. Each turbomachine blade includes a platform having a radially inner surface. The system includes a spacer axially adjacent the platform of at least one turbomachine blade in the turbomachine, e.g., adjacent a turbomachine blade stage. The spacer includes a body. A damping element coupler is on the body of the spacer, and a vibration-damping element is configured to couple to the damping element coupler. The vibration-damping element and the damping element coupler are disposed to cause the vibration-damping element to engage the radially inner surface of the platform of the turbomachine blade(s) to dampen vibration of the turbomachine blade(s), e.g., during operation of the turbomachine.
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公开(公告)号：US20210372287A1
公开(公告)日：2021-12-02
申请号：US16883158
申请日：2020-05-26
Applicant: General Electric Company
Inventor： Jeremy Peter Latimer , Patrick Daniel Noble
IPC: F01D5/22
Abstract: A vibration-damping system for turbomachine blade(s) in a turbomachine is provided. Each turbomachine blade includes a platform having a radially inner surface. The system includes a spacer axially adjacent the platform of at least one turbomachine blade in the turbomachine, e.g., adjacent a turbomachine blade stage. The spacer includes a body. A damping element coupler is on the body of the spacer, and a vibration-damping element is configured to couple to the damping element coupler. The vibration-damping element and the damping element coupler are disposed to cause the vibration-damping element to engage the radially inner surface of the platform of the turbomachine blade(s) to dampen vibration of the turbomachine blade(s), e.g., during operation of the turbomachine.
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公开(公告)号：US09896946B2
公开(公告)日：2018-02-20
申请号：US14068456
申请日：2013-10-31
Applicant: General Electric Company
Inventor： Patrick Daniel Noble
CPC classification number: F01D5/3007 , F01D5/22 , F01D11/006 , F05D2220/32 , F05D2230/60 , F05D2240/80 , Y02T50/672 , Y10T29/49321
Abstract: A rotor assembly includes a rotor disc including a plurality of circumferentially-spaced diskposts and a plurality of dovetail slots. Each dovetail slot is defined between a pair of circumferentially-adjacent diskposts. A plurality of rotor blades are coupled to the rotor disc. Each rotor blade includes a dovetail portion that is configured to slidably engage a respective dovetail slot. A plurality of platform sections are coupled to the rotor disc such that each platform section is adjacent a respective rotor blade. Each platform section includes a diskpost slot that is configured to receive one of the plurality of diskposts such that each dovetail slot receives a respective dovetail portion and at least a portion of at least one of the platform sections adjacent the rotor blade.
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