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公开(公告)号：US20140193273A1
公开(公告)日：2014-07-10
申请号：US13737031
申请日：2013-01-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Harrish Bommanakatte , Jalindar Appa Walunj , Anthony Louis Giglio , Jason Douglas Herzlinger
IPC: F01D5/18
CPC classification number: F01D5/189 , F01D5/187 , F05D2240/303 , F05D2260/201 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: An interior cooling configuration formed within an airfoil of a blade of a combustion turbine engine is provided. The interior cooling configuration may include a first flow passage and a second flow passage that have a side-by-side configuration for a segment, and multiple lateral crossover passages extending between and fluidly connecting the first flow passage to the second flow passage. The crossover passages may be staggered.
Abstract translation: 提供了形成在燃气涡轮发动机的叶片的翼型内的内部冷却构造。 内部冷却构造可以包括具有用于段的并排构造的第一流动通道和第二流动通道，以及在第一流动通道和第二流动通道之间延伸并且将流体连接到第二流动通道的多个横向跨接通道。 交叉通道可能交错。
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公开(公告)号：US20200165918A1
公开(公告)日：2020-05-28
申请号：US16199353
申请日：2018-11-26
Applicant: General Electric Company
Inventor： Jalindar Appa Walunj , Sylvain Pierre , Prem Venugopal
Abstract: A turbine rotor blade including an airfoil that extends from a platform. The platform may include a first portion of a nominal platform contour substantially in accordance with Cartesian coordinate values of X′, Y′, and Z′ as set forth in Table II. The Cartesian coordinate values of X′, Y′, and Z′ are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X′, Y′, and Z′ by a height of the airfoil defined along a Z′ axis. The X′ and Y′ values of the first portion are coordinate values that, when connected by smooth continuing arcs, define contour lines of the first portion of the nominal airfoil profile at each Z′ coordinate value. The contour lines may be joined smoothly with one another to form the first portion.
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公开(公告)号：US20170226864A1
公开(公告)日：2017-08-10
申请号：US15019516
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Mark Steven Honkomp , Xiaoyong Fu , Paul Kendall Smith , Jalindar Appa Walunj
IPC: F01D5/14
CPC classification number: F01D5/141 , F01D5/143 , F01D5/147 , F05D2220/30 , F05D2250/74 , Y02T50/673
Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.
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公开(公告)号：US11236628B1
公开(公告)日：2022-02-01
申请号：US17155427
申请日：2021-01-22
Applicant: General Electric Company
Inventor： Neil Devin Ristau , Russell Pierson DeForest , Jalindar Appa Walunj
Abstract: A turbine nozzle for a gas turbine includes: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs that define airfoil profile sections at each distance Z along at least a portion of the airfoil, and the airfoil profile sections at the Z distances are joined smoothly with one another to form the nominal profile.
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公开(公告)号：US20180355727A1
公开(公告)日：2018-12-13
申请号：US15620896
申请日：2017-06-13
Applicant: General Electric Company
Inventor： Jalindar Appa Walunj , Shashwat Swami Jaiswal , Stephen Paul Wassynger , Xiuzhang James Zhang
Abstract: A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.
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Patent Agency Ranking
公开(公告)号：US20170306765A1
公开(公告)日：2017-10-26
申请号：US15137341
申请日：2016-04-25
Applicant: General Electric Company
Inventor： Jalindar Appa Walunj , Mark Steven Honkomp
CPC classification number: F01D5/187 , F01D5/147 , F02C7/12 , F05D2220/32 , F05D2240/304 , F05D2240/35 , F05D2250/184 , F05D2260/202 , F05D2260/2212
Abstract: The present disclosure is directed to an airfoil for a gas turbine rotor blade. The airfoil includes a pressure side wall and a suction side wall connected to the pressure side wall at a leading edge portion and a trailing edge portion. The pressure side wall and the suction side wall collectively define an internal cavity within the airfoil. A plurality of pins is disposed within the internal cavity. The trailing edge portion defines a first cooling passage having a first inlet spaced apart from a first outlet by a first length and a second cooling passage comprising a second inlet spaced apart from a second outlet by a second length. The first length is greater than the second length.
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公开(公告)号：US11384640B2
公开(公告)日：2022-07-12
申请号：US16199353
申请日：2018-11-26
Applicant: General Electric Company
Inventor： Jalindar Appa Walunj , Sylvain Pierre , Prem Venugopal
Abstract: A turbine rotor blade including an airfoil that extends from a platform. The platform may include a first portion of a nominal platform contour substantially in accordance with Cartesian coordinate values of X′, Y′, and Z′ as set forth in Table II. The Cartesian coordinate values of X′, Y′, and Z′ are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X′, Y′, and Z′ by a height of the airfoil defined along a Z′ axis. The X′ and Y′ values of the first portion are coordinate values that, when connected by smooth continuing arcs, define contour lines of the first portion of the nominal airfoil profile at each Z′ coordinate value. The contour lines may be joined smoothly with one another to form the first portion.
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公开(公告)号：US10704406B2
公开(公告)日：2020-07-07
申请号：US15620896
申请日：2017-06-13
Applicant: General Electric Company
Inventor： Jalindar Appa Walunj , Shashwat Swami Jaiswal , Stephen Paul Wassynger , Xiuzhang James Zhang
Abstract: A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.
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公开(公告)号：US10156146B2
公开(公告)日：2018-12-18
申请号：US15137341
申请日：2016-04-25
Applicant: General Electric Company
Inventor： Jalindar Appa Walunj , Mark Steven Honkomp
Abstract: The present disclosure is directed to an airfoil for a gas turbine rotor blade. The airfoil includes a pressure side wall and a suction side wall connected to the pressure side wall at a leading edge portion and a trailing edge portion. The pressure side wall and the suction side wall collectively define an internal cavity within the airfoil. A plurality of pins is disposed within the internal cavity. The trailing edge portion defines a first cooling passage having a first inlet spaced apart from a first outlet by a first length and a second cooling passage comprising a second inlet spaced apart from a second outlet by a second length. The first length is greater than the second length.
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公开(公告)号：US10001014B2
公开(公告)日：2018-06-19
申请号：US15019516
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Mark Steven Honkomp , Xiaoyong Fu , Paul Kendall Smith , Jalindar Appa Walunj
IPC: F01D5/14
CPC classification number: F01D5/141 , F01D5/143 , F01D5/147 , F05D2220/30 , F05D2250/74 , Y02T50/673
Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.
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