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公开(公告)号：US20150044059A1
公开(公告)日：2015-02-12
申请号：US13963322
申请日：2013-08-09
Applicant: General Electric Company
Inventor： Stephen Paul Wassynger , John Wesley Harris, JR. , Michael James Healy
CPC classification number: F01D5/147 , F01D5/005 , F01D5/186 , F01D5/187 , F05D2230/22 , F05D2240/122 , F05D2240/304 , Y10T29/49318
Abstract: An airfoil includes a main portion formed of a base material. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising at least one pre-sintered preform (PSP) material operatively coupled to the base material proximate the trailing edge region.
Abstract translation: 机翼包括由基材形成的主体部。 还包括主要部分的后缘区域。 还包括后缘补充结构，其包括至少一个可操作地连接到靠近后缘区域的基底材料的预烧结预成型件（PSP）材料。
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公开(公告)号：US20210132598A1
公开(公告)日：2021-05-06
申请号：US16668602
申请日：2019-10-30
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A measurement system for a gas turbine engine is provided. The measurement system comprises a sensor assembly. The measurement system also includes multiple sensors coupled to the sensor assembly. The sensor assembly is configured to be removably inserted within a space defined by a circumferential track embedded within an inner diameter of a casing of the gas turbine engine without having to disassemble the casing.
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公开(公告)号：US10472975B2
公开(公告)日：2019-11-12
申请号：US14844280
申请日：2015-09-03
Applicant: General Electric Company
Inventor： Spencer A. Kareff , Poorna Krishnakumar , Kevin Lee Worley , Christopher Michael Penny , Stephen Paul Wassynger
IPC: F01D5/22
Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor disk comprises a first elongated body having a center portion disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion define a generally arcuate top portion of the first elongated body. The first elongated body defines a slot that extends axially therethrough. The damper pin further includes a second elongated body having a generally arcuate top portion. The second elongated body is at least partially disposed within the slot and is slideably engaged in an axial direction with the first elongated body.
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公开(公告)号：US20170350263A1
公开(公告)日：2017-12-07
申请号：US15172944
申请日：2016-06-03
Applicant: General Electric Company
Inventor： Andrew Paul Giametta , James Tyson Balkcum, III , David Richard Johns , Stephen Paul Wassynger
CPC classification number: F01D9/023 , F01D11/006 , F05D2240/55 , F05D2240/57 , F16J15/025
Abstract: This disclosure provides systems and methods for sealing flow path components, such as turbomachine airfoils, with a front-leaded seal. A seal channel is defined between a portion of the suction side surface of a first flow path component and a portion of the pressure side of a second flow path component. A seal is retained within the seal channel formed by the pressure side portion and the suction side portion and the seal channel defines a forward opening through which the seal is inserted during installation.
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15.发明申请TURBOMACHINE INCLUDING A TRANISTION PIECE TO TURBINE PORTION VARIABLE PURGE FLOW SEAL MEMBER 审中-公开涡轮机，其中包括一个运输部件，用于涡轮机部件，可变流量密封件公开(公告)号：US20160131041A1
公开(公告)日：2016-05-12
申请号：US14534934
申请日：2014-11-06
Applicant: General Electric Company
Inventor： Stephen Paul Wassynger , Joe Timothy Brown , Sivaraman Vedhagiri
CPC classification number: F01D9/023 , Y02T50/675
Abstract: A turbomachine includes a compressor portion, and a turbine portion operatively connected to the compressor portion. The turbine portion includes a compressor discharge portion, a hot gas path and a first stage nozzle arranged at the hot gas path. A combustor assembly is fluidically connected to the compressor portion. A transition piece has an inlet portion fluidically connected to the combustor assembly and an outlet portion fluidically connected to the turbine portion. A seal member is operatively connected relative to one of the transition piece and the first stage nozzle of the turbine portion. The seal member extends from a first end to a second, cantilevered end through an intermediate portion including one or more openings that provide a purge fluid flow path from the compressor discharge portion toward the hot gas path.
Abstract translation: 涡轮机包括压缩机部分和可操作地连接到压缩机部分的涡轮机部分。 涡轮部包括设置在热气路径处的压缩机排出部，热气路径和第一级喷嘴。 燃烧器组件流体地连接到压缩机部分。 过渡件具有流体连接到燃烧器组件的入口部分和与涡轮部分流体连接的出口部分。 密封构件相对于涡轮机部分的过渡件和第一级喷嘴中的一个可操作地连接。 密封构件从第一端延伸到第二悬臂端，穿过包括一个或多个开口的中间部分，该开口提供从压缩机排放部朝向热气路径的清洗流体流动路径。
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Patent Agency Ranking
公开(公告)号：US20140154063A1
公开(公告)日：2014-06-05
申请号：US13705804
申请日：2012-12-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Xiuzhang James Zhang , Stephen Paul Wassynger , Aaron Ezekiel Smith , Anthony Louis Giglio
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/186 , F05D2240/81 , Y02T50/673 , Y02T50/676
Abstract: An airfoil includes an outer surface having a leading edge, a trailing edge downstream from the leading edge, and a convex surface between the leading and trailing edges. A cavity is inside the outer surface, and a platform is connected to the outer surface and defines a top surface around at least a portion of the outer surface. A first plurality of trenches is beneath the top surface of the platform upstream from the leading edge, wherein each trench in the first plurality of trenches is in fluid communication with the cavity inside the outer surface. A first plurality of cooling passages provide fluid communication from the first plurality of trenches through the top surface of the platform.
Abstract translation: 翼型件包括具有前缘的外表面，在前缘下游的后缘以及前缘和后缘之间的凸面。 空腔在外表面内，并且平台连接到外表面并且围绕外表面的至少一部分限定顶表面。 第一多个沟槽位于平台的顶表面上方的前缘上游，其中第一多个沟槽中的每个沟槽与外表面内的空腔流体连通。 第一多个冷却通道提供从第一多个沟槽通过平台的顶表面的流体连通。
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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：US10156145B2
公开(公告)日：2018-12-18
申请号：US14923697
申请日：2015-10-27
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal , Stephen Paul Wassynger
Abstract: A turbine bucket according to various embodiments includes: a base; a blade coupled to the base and extending radially outward from the base, the blade including: a body having: a pressure side; a suction side opposing the pressure side; a leading edge between the pressure side and the suction side; and a trailing edge between the pressure side and the suction side on a side opposing the leading edge; a plurality of radially extending cooling passageways within the body; and at least one bleed aperture fluidly coupled with at least one of the plurality of radially extending cooling passageways, the at least one bleed aperture extending through the body at the trailing edge; and a shroud coupled to the blade radially outboard of the blade.
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公开(公告)号：US20180052946A1
公开(公告)日：2018-02-22
申请号：US15240279
申请日：2016-08-18
Applicant: General Electric Company
Inventor： Truman Blake Horner , Sze Bun Brian Chan , John Robert Korsedal , Joseph Leonard Moroso , Ian Darnall Reeves , Birol Turan , Stephen Paul Wassynger
IPC: G06F17/50
CPC classification number: G06F17/5086 , G01M5/0016 , G01M5/005 , G01M5/0091 , G01M15/14 , G01N2021/8887
Abstract: Various embodiments include a system having: a computing device configured to detect deformation in a manufactured component by: obtaining a post-deployment three-dimensional (3D) depiction of the manufactured component; obtaining a model of the manufactured component including: a nominal shape model indicating a nominal shape of the manufactured component prior to operational deployment, and an expected deformation model indicating expected deformation of the manufactured component after operational deployment; aligning a localized region of the manufactured component in the post-deployment 3D depiction with the localized region of the manufactured component in the nominal shape model; identifying a first set of points in the localized region not subject to deformation between the post-deployment 3D depiction and the nominal shape model; and identifying a second set of points in the localized region subject to deformation between the post-deployment 3D depiction and the nominal shape model.
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公开(公告)号：US20170114648A1
公开(公告)日：2017-04-27
申请号：US14923697
申请日：2015-10-27
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal , Stephen Paul Wassynger
CPC classification number: F01D5/187 , F01D5/02 , F01D5/225 , F01D9/02 , F05D2220/32 , F05D2240/304 , F05D2260/20
Abstract: A turbine bucket according to various embodiments includes: a base; a blade coupled to the base and extending radially outward from the base, the blade including: a body having: a pressure side; a suction side opposing the pressure side; a leading edge between the pressure side and the suction side; and a trailing edge between the pressure side and the suction side on a side opposing the leading edge; a plurality of radially extending cooling passageways within the body; and at least one bleed aperture fluidly coupled with at least one of the plurality of radially extending cooling passageways, the at least one bleed aperture extending through the body at the trailing edge; and a shroud coupled to the blade radially outboard of the blade.
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