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公开(公告)号：US09995172B2
公开(公告)日：2018-06-12
申请号：US14880575
申请日：2015-10-12
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Stephen Paul Wassynger
CPC classification number: F01D25/12 , F01D9/041 , F05D2220/32 , F05D2240/128 , F05D2240/81 , F05D2260/202 , F05D2260/204 , Y02T50/676
Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define inner and outer flow boundaries of the turbine nozzle. At least one of the inner band and the outer band defines a plurality of cooling channels formed and a coolant discharge plenum beneath a gas side surface of the corresponding inner or outer band that is in fluid communication with the cooling channels. The coolant discharge plenum is formed within the inner band or the outer band downstream from the cooling channels and upstream from a plurality of coolant discharge ports.
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公开(公告)号：US09845690B1
公开(公告)日：2017-12-19
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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公开(公告)号：US11635750B2
公开(公告)日：2023-04-25
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：US10267156B2
公开(公告)日：2019-04-23
申请号：US14290076
申请日：2014-05-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Dwight Eric Davidson , Michael David McDufford , Brian Denver Potter , Stephen Joseph Balsone , Stephen Paul Wassynger
Abstract: A turbine bucket assembly and turbine system are disclosed. The turbine bucket assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a segmented airfoil having a root segment extending radially outward from the platform and a tip segment coupled to the root segment, the tip segment having a second axial length, which is less than the first axial length; and a turbine wheel defining a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The tip segment includes a tip segment material, the root segment includes a root segment material, and the turbine wheel includes a turbine wheel material, the root segment material and the turbine wheel material having a lower heat resistance and a higher thermal expansion than the tip segment material.
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公开(公告)号：US09528381B2
公开(公告)日：2016-12-27
申请号：US14143599
申请日：2013-12-30
Applicant: General Electric Company
Inventor： Stephen Paul Wassynger , Aaron Ezekiel Smith
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/188 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: A turbine blade having an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may include a rib configuration that partitions the chamber and defines a flow passage having a first and a second side. The flow passage may include a port formed through the first side. A projection of a center axis of the port through the flow passage may define a strike point on the second side of the flow passage, and a backstrike recess may be positioned on the second side of the flow passage so to contain the strike point.
Abstract translation: 一种具有由凹形压力侧外壁和凸形吸入侧外壁限定的翼型件的涡轮机叶片，其沿着前缘和后缘连接，并且在它们之间形成用于接收冷却剂流动的径向延伸室。 涡轮机叶片可以包括肋构造，其分隔室并限定具有第一侧和第二侧的流动通道。 流路可以包括通过第一侧形成的端口。 通过流动通道的端口的中心轴线的突起可以限定流动通道的第二侧上的撞击点，并且反冲击凹口可以定位在流动通道的第二侧上以便容纳撞击点。
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Patent Agency Ranking
公开(公告)号：US20150198059A1
公开(公告)日：2015-07-16
申请号：US14152103
申请日：2014-01-10
Applicant: General Electric Company
Inventor： Alston Ilford Scipio , Sanji Ekanayake , Stephen Paul Wassynger
CPC classification number: F01D25/002 , F01D25/007
Abstract: A gas turbine engine may be manually cleaned by removing a compressor casing and a turbine casing from the gas turbine engine, cleaning stator vanes of the gas turbine engine, and applying an organic acid solution to metallic surfaces of the gas turbine engine. The organic acid solution may be rinsed from the gas turbine engine and an anticorrosive solution may be applied to the metallic surfaces of the gas turbine engine.
Abstract translation: 可以通过从燃气涡轮发动机移除压缩机壳体和涡轮机壳体，清洁燃气涡轮发动机的定子叶片，并将有机酸溶液施加到燃气涡轮发动机的金属表面来手动清洁燃气涡轮发动机。 可以从燃气涡轮发动机冲洗有机酸溶液，并且可以将防腐溶液施加到燃气涡轮发动机的金属表面。
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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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公开(公告)号：US09835087B2
公开(公告)日：2017-12-05
申请号：US14476366
申请日：2014-09-03
Applicant: General Electric Company
Inventor： Stephen Paul Wassynger
CPC classification number: F02C7/12 , F01D5/187 , F05D2240/304 , F05D2240/307
Abstract: A turbine bucket includes a leading edge, a trailing edge, a root portion, and a tip portion. The turbine bucket also includes one or more cooling passages extending through a body of the turbine bucket from an inlet to an outlet. The cooling passages are configured to route a cooling flow of fluid through the turbine bucket. The turbine bucket further includes a plenum defined within the tip portion to receive the fluid from the outlet of the cooling passages for expulsion of the cooling flow of fluid into a main flow path via at least one outlet hole proximate the trailing edge of the turbine bucket.
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公开(公告)号：US20170067346A1
公开(公告)日：2017-03-09
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
CPC classification number: F01D5/22 , F05D2220/32 , F05D2250/312 , F05D2250/41 , Y02T50/671
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.
Abstract translation: 用于阻尼与转子盘耦合的相邻涡轮叶片的阻尼器销包括第一细长体，其具有设置在第一端部和第二端部之间的中心部分。 第一端部，中心部分和第二端部限定第一细长主体的大致弓形顶部。 第一细长体限定了轴向延伸穿过其中的狭槽。 减震器销还包括具有大致弓形顶部的第二细长主体。 所述第二细长体至少部分地设置在所述槽内，并且能够与所述第一细长体在轴向方向上可滑动地接合。
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公开(公告)号：US20150184523A1
公开(公告)日：2015-07-02
申请号：US14143599
申请日：2013-12-30
Applicant: General Electric Company
Inventor： Stephen Paul Wassynger , Aaron Ezekiel Smith
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/188 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: A turbine blade having an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may include a rib configuration that partitions the chamber and defines a flow passage having a first and a second side. The flow passage may include a port formed through the first side. A projection of a center axis of the port through the flow passage may define a strike point on the second side of the flow passage, and a backstrike recess may be positioned on the second side of the flow passage so to contain the strike point.
Abstract translation: 一种具有由凹形压力侧外壁和凸形吸入侧外壁限定的翼型件的涡轮机叶片，其沿着前缘和后缘连接，并且在它们之间形成用于接收冷却剂流动的径向延伸室。 涡轮机叶片可以包括肋构造，其分隔室并限定具有第一侧和第二侧的流动通道。 流路可以包括通过第一侧形成的端口。 通过流动通道的端口的中心轴线的突起可以限定流动通道的第二侧上的撞击点，并且反冲击凹口可以定位在流动通道的第二侧上以便容纳撞击点。
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