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公开(公告)号：US20220349419A1
公开(公告)日：2022-11-03
申请号：US17245005
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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公开(公告)号：US11326620B1
公开(公告)日：2022-05-10
申请号：US17244995
申请日：2021-04-30
Applicant: General Electric Company
Inventor： Matthew John McKeever , Michael James Healy , Bruce Clark Busbey , Damir Novak , Robin Charles Payne , Thomas Peter Sommer , Olivier Anthony Bron , Carlos Alberto Cardoza , Lukasz Marcin Maczka , Damir Fanjak , Lance William Smith , Alex David Hollanshead , Wilfried Rick , Yu Wang
Abstract: A stator vane 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, Table IX, Table X, Table XI, or Table XII. 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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公开(公告)号：US09464531B2
公开(公告)日：2016-10-11
申请号：US14055095
申请日：2013-10-16
Applicant: General Electric Company
Inventor： Christian Michael Hansen , Michael James Healy , Brian Denver Potter
CPC classification number: F01D5/303 , F01D5/3038 , F01D5/32
Abstract: Locking spacer assemblies, rotor assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a first end piece and a second end piece each configured to fit into a space between platforms of adjacent rotor blades, the first end piece and second end piece each comprising an outer surface and an inner surface, the outer surface having a profile adapted to project into an attachment slot, wherein the inner surfaces of the first and second end pieces generally face each other. The locking spacer assembly further includes an actuator movable between the inner surfaces, the actuator comprising a projection configured to engage the inner surface, the actuator further comprising a plurality of locating protrusions extending from the projection, the locating protrusions configured to fit within locating channels defined in the first end piece and the second end piece.
Abstract translation: 提供了锁定间隔件组件，转子组件和涡轮机。 在一个实施例中，锁定间隔件组件包括第一端部件和第二端部件，每个第一端部件和第二端部件被构造成装配到相邻转子叶片的平台之间的空间中，第一端部件和第二端件每个包括外表面和内表面， 所述外表面具有适于突出到附接槽中的轮廓，其中所述第一和第二端片的内表面通常面对彼此。 所述锁定间隔件组件还包括可在所述内表面之间移动的致动器，所述致动器包括构造成接合所述内表面的突出部，所述致动器还包括从所述突起延伸的多个定位突起，所述定位突起被配置成适合定位的定位通道 在第一端件和第二端件中。
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公开(公告)号：US20160186593A1
公开(公告)日：2016-06-30
申请号：US14587752
申请日：2014-12-31
Applicant: General Electric Company
Inventor： Michael James Healy
CPC classification number: F01D11/008 , F01D5/143 , F01D5/3007 , F01D5/326 , F01D11/001 , F04D29/322 , F05D2260/30 , 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：US11519272B2
公开(公告)日：2022-12-06
申请号：US17245005
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：US11414996B1
公开(公告)日：2022-08-16
申请号：US17245011
申请日：2021-04-30
Applicant: General Electric Company
Inventor： Matthew John McKeever , Michael James Healy , Robin Charles Payne , Damir Novak , Bruce Clark Busbey , Wilfried Rick , Thomas Peter Sommer , Ervin Alimani , Kevin Michael Barnett , Carlos Alberto Cardoza , Gerrit Ruch , Dejan Mikasinovic , Denis Stanković , Josip Galic , Olivier Anthony Bron
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, Table IX, Table X, Table XI, or Table XII. 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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公开(公告)号：US20180087528A1
公开(公告)日：2018-03-29
申请号：US15274352
申请日：2016-09-23
Applicant: General Electric Company
Inventor： MIchael James Dutka , Michael James Healy
CPC classification number: F04D29/544 , F01D5/141 , F02C3/04 , F04D29/324 , F04D29/384 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74
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：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：US20160186574A1
公开(公告)日：2016-06-30
申请号：US14583865
申请日：2014-12-29
Applicant: General Electric Company
Inventor： Joseph Anthony Weber , Michael James Healy
CPC classification number: F01D5/187 , F05D2230/11 , F05D2230/12 , F05D2230/211 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: A blade for a turbine of a gas turbine engine that includes an airfoil, the airfoil having a leading edge, a trailing edge, an outboard tip, and an inboard end. The airfoil may further include a cooling configuration that includes a plurality of cooling channels for receiving and directing a coolant. The cooling channels may include a linear cooling channel and a curved cooling channel. The blade may also include a contoured shape defined by the airfoil between the inboard end and the outboard tip, with the contoured shape being configured so to include a target area inaccessible to a linear reference line extending radially from a position at the inboard end of the airfoil. The curved cooling channels may be configured to extend between an upstream end and a downstream end so to intersect the target area therebetween.
Abstract translation: 一种用于燃气涡轮发动机的涡轮机的叶片，其包括翼型件，所述翼型件具有前缘，后缘，外侧翼尖和内侧端部。 翼型件还可以包括冷却构造，其包括用于接收和引导冷却剂的多个冷却通道。 冷却通道可以包括线性冷却通道和弯曲的冷却通道。 叶片还可以包括由内侧端部和外侧端部之间的翼型件限定的轮廓形状，其中轮廓形状被构造成包括不能从在内侧端部处的位置处的位置径向延伸的线性参考线的目标区域 翼型。 弯曲的冷却通道可以被配置为在上游端和下游端之间延伸以与其间的目标区域相交。
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公开(公告)号：US09341071B2
公开(公告)日：2016-05-17
申请号：US14055124
申请日：2013-10-16
Applicant: General Electric Company
Inventor： Michael James Healy , Brian Denver Potter
CPC classification number: F01D5/303 , F01D5/3038 , F01D5/32
Abstract: Locking spacer assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a spacer, the spacer including a platform and a plurality of legs extending generally radially inward from the platform. The locking spacer assembly further includes a clamp configured to contact and cause elastic deformation of each of the plurality of legs in a generally axial direction towards each other. The locking spacer assembly further includes a locking lug configured to contact and impart a force against each of the plurality of legs in an opposite generally axial direction.
Abstract translation: 提供了锁定间隔件组件和涡轮机。 在一个实施例中，锁定间隔件组件包括间隔件，间隔件包括平台和从平台大致径向向内延伸的多个腿。 锁定间隔件组件还包括夹具，该夹具构造成使多个腿中的每一个在大致轴向方向上彼此接触并引起弹性变形。 锁定间隔件组件还包括锁定凸耳，所述锁定凸耳构造成在相反的大致轴向方向上接触并向所述多个支腿中的每一个施加力。
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