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公开(公告)号：US20180017074A1
公开(公告)日：2018-01-18
申请号：US15208913
申请日：2016-07-13
Applicant: General Electric Company
Inventor： Sharan Shanti , Nandakumar AR , Christian Michael Hansen , Jeremy Peter Latimer
CPC classification number: F04D29/542 , F01D9/042 , F04D29/644 , F05B2220/302 , F05B2230/60 , F05D2230/642 , F05D2260/40 , Y02T50/673
Abstract: This disclosure provides systems and methods for reducing stress in vane shroud assemblies by defining a gap between adjacent portions of the airfoil and the shroud whereby stress from the securing force is relieved in a portion of the shroud. The airfoil has a distal end with a contact surface and a tenon. The shroud has a contact surface with the airfoil and accommodates the tenon. An attachment device provides the securing force between the airfoil and shroud contact surfaces through the shroud and the gap serves to reduce stress on the shroud.
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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：US09476310B2
公开(公告)日：2016-10-25
申请号：US13655147
申请日：2012-10-18
Applicant: General Electric Company
Inventor： Jeremy Peter Latimer , Donald Joseph Kasperski , Thomas R. Tipton
CPC classification number: F01D5/3053 , F01D5/3007 , F01D5/326
Abstract: Embodiments of the present disclosure include a gas turbine engine system. The system may include a rotor wheel having a number of blades mounted about a periphery of the rotor wheel. Further, the system may include a retention device. The retention device may include a number of projections extending from a radial surface of the rotor wheel to form a number of circumferential slots about the rotor wheel. The retention device may also include a number of elongated members positioned within the circumferential slots to impede axial movement of the blades.
Abstract translation: 本公开的实施例包括燃气涡轮发动机系统。 该系统可以包括具有围绕转子轮的周边安装的多个叶片的转子轮。 此外，系统可以包括保持装置。 保持装置可以包括从转子轮的径向表面延伸的多个突起，以形成围绕转子轮的多个周向槽。 保持装置还可以包括定位在周向槽内的多个细长构件以阻止叶片的轴向运动。
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公开(公告)号：US20140112793A1
公开(公告)日：2014-04-24
申请号：US13655147
申请日：2012-10-18
Applicant: General Electric Company
Inventor： Jeremy Peter Latimer , Donald Joseph Kasperski , Thomas R. Tipton
IPC: F01D5/30
CPC classification number: F01D5/3053 , F01D5/3007 , F01D5/326
Abstract: Embodiments of the present disclosure include a gas turbine engine system. The system may include a rotor wheel having a number of blades mounted about a periphery of the rotor wheel. Further, the system may include a retention device. The retention device may include a number of projections extending from a radial surface of the rotor wheel to form a number of circumferential slots about the rotor wheel. The retention device may also include a number of elongated members positioned within the circumferential slots to impede axial movement of the blades.
Abstract translation: 本公开的实施例包括燃气涡轮发动机系统。 该系统可以包括具有围绕转子轮的周边安装的多个叶片的转子轮。 此外，系统可以包括保持装置。 保持装置可以包括从转子轮的径向表面延伸的多个突起，以形成围绕转子轮的多个周向槽。 保持装置还可以包括定位在周向槽内的多个细长构件以阻止叶片的轴向运动。
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公开(公告)号：US11441427B1
公开(公告)日：2022-09-13
申请号：US17245002
申请日：2021-04-30
Applicant: General Electric Company
Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.
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Patent Agency Ranking
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：US20220372879A1
公开(公告)日：2022-11-24
申请号：US17445203
申请日：2021-08-17
Applicant: General Electric Company
Inventor： Marc Edward Blohm , Vasantharuban S , Michael James Dutka , Nandakumar A R , Sharan Shanti , Prakash Dalsania , Corey Lynn Hubbert , Siddaraja Mallikarjuna Devangada , Joshy John , Nancy Chaudhary , Abel Christena Francis , Brandon Lamar Bush , Jeremy Peter Latimer
IPC: F01D5/14
Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.
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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：US20230250724A1
公开(公告)日：2023-08-10
申请号：US18192162
申请日：2023-03-29
Applicant: General Electric Company
Inventor： Marc Edward Blohm , Vasantharuban S , Michael James Dutka , Nandakumar A R , Sharan Shanti , Prakash Dalsania , Corey Lynn Hubbert , Siddaraja Mallikarjuna Devangada , Joshy John , Nancy Chaudhary , Abel Christena Francis , Brandon Lamar Bush , Jeremy Peter Latimer
IPC: F01D5/14
CPC classification number: F01D5/141 , F05D2240/301 , F05D2240/306 , F05D2220/3219 , F05D2220/3217 , F05D2250/74
Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.
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