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公开(公告)号：US20170074281A1
公开(公告)日：2017-03-16
申请号：US14854237
申请日：2015-09-15
Applicant: General Electric Company
Inventor： Qiang Li , Aaron Phillip King , Toby George Darkins, JR. , Anthony Joseph Maurer
CPC classification number: F04D29/324 , F01D5/14 , F01D5/26 , F01D5/303 , F01D5/3038 , F04D29/668 , F05B2240/80 , F05D2220/32 , F05D2240/30 , F05D2240/80 , F05D2250/712 , F05D2260/96 , Y02T50/673
Abstract: A gas turbine engine compressor blade includes an airfoil and a root section connected to a blade platform therebetween and an at least partially curved cropped corner of the blade platform. The corner shape and size may avoid resonance of blade during engine operation. Corner may be J-shaped including a straight section extending from pressure side edge towards suction side edge of platform and curved section extending from straight section to uncropped portion of platform trailing edge of the platform. A method of designing the cropped corner includes choosing shapes sizes of the cropped corner for numerically analyzing and determining shape and size for cropped corner using numerical model to iteratively numerically analyze aerodynamically cropped platform with different shapes and sizes of cropped corner. Numerical model may be validated with engine or component testing of blade having a cropped platform with at least one of the shapes and sizes.
Abstract translation: 燃气涡轮发动机压缩机叶片包括翼型件和连接到它们之间的叶片平台的根部部分和刀片平台的至少部分弯曲的裁剪角部。 角形和尺寸可以避免发动机运转时叶片的共振。 角部可以是J形，包括从压力侧边缘朝向平台的吸力侧边缘延伸的直线部分，以及从平台的直线部分延伸到平台后缘的未裁剪部分的弯曲部分。 设计裁剪角的方法包括选择裁剪角的形状大小进行数值分析，并使用数值模型确定裁剪角的形状和尺寸，以迭代数值分析具有不同形状和尺寸的裁剪角的空气动力学裁剪平台。 数值模型可以用具有具有至少一种形状和尺寸的裁剪平台的叶片的发动机或部件测试来验证。
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公开(公告)号：US10519788B2
公开(公告)日：2019-12-31
申请号：US14893639
申请日：2014-05-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Qiang Li , Nicholas Joseph Kray , Scott Roger Finn
Abstract: A composite airfoil comprises a leading edge and a trailing edge, a pressure side and a suction side extending between the leading edge and the trailing edge, a tip at a radial outer end of the airfoil, a shank at a radial inner end of the airfoil, a dovetail connected to the shank, and a metal patch disposed between the dovetail and the shank.
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公开(公告)号：US09745851B2
公开(公告)日：2017-08-29
申请号：US14597278
申请日：2015-01-15
Applicant: General Electric Company
Inventor： Qiang Li , Nicholas Joseph Kray
CPC classification number: F01D5/147 , F01D5/143 , F01D5/282 , F01D5/3007 , F05D2200/36 , F05D2220/32 , F05D2240/303 , F05D2300/10 , Y02T50/672 , Y02T50/673
Abstract: A composite blade includes a composite airfoil section having airfoil pressure and suction sides extending chordwise between airfoil leading and trailing edges, a dovetail root attached to airfoil section and a blade shank therebetween, and a metallic leading edge shield covering an axially extending portion of airfoil section including at least a portion of airfoil leading edge and a radially and chordwise extending portion of a leading edge portion of the blade shank. Leading edge portion may be cut back from airfoil leading edge and a shank leading edge aft or downstream of airfoil leading edge. A nose may extend along a shield leading edge of the metallic leading edge shield with pressure and suction side legs extending aftwardly from nose along airfoil pressure and suction sides. Light weight insert may be located between nose and airfoil leading edges.
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公开(公告)号：US11047058B2
公开(公告)日：2021-06-29
申请号：US15304682
申请日：2015-04-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Qiang Li , Nicholas Joseph Kray , Michael W. Peretti , Tod Winton Davis
Abstract: A method for making a metallic leading edge guard of the type having a nose with first and second wings extending therefrom is disclosed. The method includes machining from a metallic blank a first half comprising a first portion of the nose and one of the wings, wherein the first portion of the nose includes an interface surface; and electroforming a second half comprising a second portion of the nose and the second wing, wherein the second half is joined to the first half at the interface surface.
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公开(公告)号：US10738630B2
公开(公告)日：2020-08-11
申请号：US15898690
申请日：2018-02-19
Applicant: General Electric Company
Inventor： Qiang Li , Nicholas Joseph Kray , Gerald Alexander Pauley , Ming Xie , Jorge Orlando Lamboy , Tod Winton Davis
Abstract: A platform apparatus for a propulsion rotor having an annular array of airfoils carried by a rotor disk. The apparatus includes: at least one forward segment comprising an arcuate forward body having a plurality of spaced-apart axially-extending forward fingers, each of the forward fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by an aft edge, wherein the forward segment defines a flow path surface and an opposed back surface; at least one aft segment comprising an arcuate aft body having a plurality of spaced-apart actually-extending aft fingers, each of the aft fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by a forward edge, wherein the aft segment defines a flow path surface and an opposed back surface, and wherein the aft edges have a shape complementary to a shape of the forward edges.
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Patent Agency Ranking
公开(公告)号：US20190257210A1
公开(公告)日：2019-08-22
申请号：US15898690
申请日：2018-02-19
Applicant: General Electric Company
Inventor： Qiang Li , Nicholas Joseph Kray , Gerald Alexander Pauley , Ming Xie , Jorge Orlando Lamboy , Tod Winton Davis
Abstract: A platform apparatus for a propulsion rotor having an annular array of airfoils carried by a rotor disk. The apparatus includes: at least one forward segment comprising an arcuate forward body having a plurality of spaced-apart axially-extending forward fingers, each of the forward fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by an aft edge, wherein the forward segment defines a flow path surface and an opposed back surface; at least one aft segment comprising an arcuate aft body having a plurality of spaced-apart actually-extending aft fingers, each of the aft fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by a forward edge, wherein the aft segment defines a flow path surface and an opposed back surface, and wherein the aft edges have a shape complementary to a shape of the forward edges.
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7.发明授权Control system and method for mitigating rotor imbalance on a wind turbine 有权用于减轻风力涡轮机转子不平衡的控制系统和方法公开(公告)号：US09587627B2
公开(公告)日：2017-03-07
申请号：US13932692
申请日：2013-07-01
Applicant: General Electric Company
Inventor： Xu Fu , Na Ni , Qiang Li , Zhilin Wu , Lihan He , Hai Qiu , Yong Yang , Gerald Addison Curtin, Jr. , Myungkeun Yoon
IPC: F03D7/02
CPC classification number: F03D7/0224 , F03D17/00 , F03D80/00 , F05B2260/84 , F05B2260/96 , F05B2270/1095 , F05B2270/328 , F05B2270/331 , F05B2270/332 , F05B2270/807 , Y02E10/722 , Y02E10/723
Abstract: A wind turbine includes multiple blades, multiple Micro Inertial Measurement Units (MIMUs) for sensing parameter signals of the blades, and a control system. The control system includes a blade bending moment calculation unit, a blade bending moment error signal calculation unit, and a pitch angle compensation command calculation unit. The blade bending moment calculation unit is used for calculating blade bending moment values of the blades based at least on the sensed parameters. The blade bending moment error signal calculation unit is used for calculating blade bending moment error signals of the blades based on the calculated blade bending moment values of the blades and multiple blade bending moment commands. The pitch angle compensation command calculation unit is used for calculating pitch angle compensation commands of the blades based on the calculated blade bending moment error signals to adjust pitch angles of the blades respectively.
Abstract translation: 风力涡轮机包括多个叶片，用于感测叶片的参数信号的多个微惯性测量单元（MIMU）和控制系统。 控制系统包括叶片弯矩计算单元，叶片弯矩误差信号计算单元和俯仰角补偿指令计算单元。 叶片弯矩计算单元用于至少基于所感测的参数来计算叶片的叶片弯矩值。 刀片弯矩误差信号计算单元用于根据叶片的计算叶片弯矩值和多叶片弯矩命令来计算叶片的叶片弯矩误差信号。 桨距角补偿指令计算单元用于基于所计算的叶片弯矩误差信号来计算叶片的俯仰角补偿命令，以分别调节叶片的桨距角。
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公开(公告)号：US10190595B2
公开(公告)日：2019-01-29
申请号：US14854237
申请日：2015-09-15
Applicant: General Electric Company
Inventor： Qiang Li , Aaron Phillip King , Toby George Darkins, Jr. , Anthony Joseph Maurer
Abstract: A gas turbine engine compressor blade includes an airfoil and a root section connected to a blade platform therebetween and an at least partially curved cropped corner of the blade platform. The corner shape and size may avoid resonance of blade during engine operation. The corner may be J-shaped including a straight section extending from the pressure side edge towards the suction side edge of the platform and a curved section extending from the straight section to an uncropped portion of the platform trailing edge of the platform. A method of designing the cropped corner includes choosing shapes and sizes of the cropped corner for numerically analyzing and determining shape and size for the cropped corner using a numerical model to iteratively numerically analyze aerodynamically the cropped platform with different shapes and sizes of the cropped corner. The numerical model may be validated with engine or component testing of the blade having a cropped platform with at least one of the shapes and sizes.
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公开(公告)号：US20160341043A1
公开(公告)日：2016-11-24
申请号：US14717861
申请日：2015-05-20
Applicant: General Electric Company
Inventor： Qiang Li , Toby George Darkins, JR.
CPC classification number: F01D5/005 , F01D5/02 , F01D5/12 , F01D25/24 , F01D25/243 , F04D29/324 , F04D29/522 , F04D29/644 , F05D2230/72 , F05D2230/80 , F05D2260/80 , Y02E20/16
Abstract: A system includes a turbomachine with a plurality of blades, a casing disposed about the rotor and the plurality of blades, an access opening disposed in the casing, and an access panel selectively coupled to the access opening, such that the access opening is sized to enable repair or replacement of at least one blade of the plurality of blades.
Abstract translation: 一种系统包括具有多个叶片的涡轮机，围绕转子和多个叶片设置的壳体，设置在壳体中的进入开口，以及选择性地联接到进入开口的进入面板，使得进入口的尺寸设定为 能够修复或更换多个叶片中的至少一个叶片。
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公开(公告)号：US20160208615A1
公开(公告)日：2016-07-21
申请号：US14597278
申请日：2015-01-15
Applicant: General Electric Company
Inventor： Qiang Li , Nicholas Joseph Kray
CPC classification number: F01D5/147 , F01D5/143 , F01D5/282 , F01D5/3007 , F05D2200/36 , F05D2220/32 , F05D2240/303 , F05D2300/10 , Y02T50/672 , Y02T50/673
Abstract: A composite blade includes a composite airfoil section having airfoil pressure and suction sides extending chordwise between airfoil leading and trailing edges, a dovetail root attached to airfoil section and a blade shank therebetween, and a metallic leading edge shield covering an axially extending portion of airfoil section including at least a portion of airfoil leading edge and a radially and chordwise extending portion of a leading edge portion of the blade shank. Leading edge portion may be cut back from airfoil leading edge and a shank leading edge aft or downstream of airfoil leading edge. A nose may extend along a shield leading edge of the metallic leading edge shield with pressure and suction side legs extending aftwardly from nose along airfoil pressure and suction sides. Light weight insert may be located between nose and airfoil leading edges.
Abstract translation: 复合叶片包括具有翼型压力的复合翼型部分，并且在翼型件前缘和后缘之间沿翼弦方向延伸的吸力侧，连接到翼型部分的燕尾根和其间的叶片柄以及覆盖翼型部分的轴向延伸部分的金属前缘屏蔽 包括叶片前缘的至少一部分和叶片柄的前缘部分的径向和弦向延伸部分。 前缘部分可以从机翼前缘和柄部前缘或翼型前缘的下游切割。 鼻子可以沿着金属前缘护罩的屏蔽前缘延伸，压力和吸力侧腿从鼻翼沿翼型压力和吸力侧向后延伸。 轻型插入件可以位于鼻翼和翼型前缘之间。
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