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Patent Agency Ranking
公开(公告)号：US09482579B2
公开(公告)日：2016-11-01
申请号：US14016580
申请日：2013-09-03
Applicant: General Electric Company
Inventor： Vivek Venugopal Badami , Daniel Francesco Driscoll , Scott Francis Johnson , Paul Joseph Martin , Nilesh Tralshawala , Guanghua Wang
CPC classification number: G01J5/0088 , F01D17/085 , F01D25/30 , F05D2270/8041 , G01J5/0014 , G01J2005/0077 , G01J2005/106
Abstract: Various embodiments include systems and apparatuses adapted for detecting two-dimensional turbomachine exhaust temperature. In some embodiments, a system includes a two-dimensional grid sized to mount within an exhaust path of a gas turbomachine, a radiation detection device for detecting radiation emitted from the two-dimensional grid at a plurality of points on the two-dimensional grid, the radiation detection device being mountable proximate the exhaust path and the two-dimensional grid and at least one computing device connected with the radiation detection device, the at least one computing device configured to generate a planar map of the temperature of the exhaust from the gas turbomachine based upon the intensity of the radiation emitted from two-dimensional grid detected at the plurality of points on the two-dimensional grid.
Abstract translation: 各种实施例包括适于检测二维涡轮机排气温度的系统和装置。 在一些实施例中，系统包括尺寸设置成安装在气体涡轮机的排气路径内的二维网格，用于检测在二维网格上的多个点处从二维网格发射的辐射的辐射检测装置， 所述辐射检测装置可安装在所述排气路径和所述二维栅格附近，以及与所述辐射检测装置连接的至少一个计算装置，所述至少一个计算装置被配置为生成来自所述气体的排气温度的平面图 基于在二维网格上的多个点处检测到的从二维网格发射的辐射的强度的涡轮机。
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公开(公告)号：US10392945B2
公开(公告)日：2019-08-27
申请号：US15599912
申请日：2017-05-19
Applicant: General Electric Company
Inventor： Sandip Dutta , Scott Francis Johnson , Joseph Anthony Weber
Abstract: The present disclosure is directed to a cooling system for a turbomachine. The cooling system includes a turbomachine component defining a turbomachine component cavity. The cooling system also includes an insert positioned within the turbomachine component cavity for cooling the turbomachine component. The insert includes an insert body and a spring body. The spring body includes a first portion fixedly coupled to the insert body, a second portion in sliding engagement with the turbomachine component, and a third portion in sliding engagement with the insert body.
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公开(公告)号：US20150063412A1
公开(公告)日：2015-03-05
申请号：US14016580
申请日：2013-09-03
Applicant: General Electric Company
Inventor： Vivek Venugopal Badami , Daniel Francesco Driscoll , Scott Francis Johnson , Paul Joseph Martin , Nilesh Tralshawala , Guanghua Wang
IPC: G01J5/00
CPC classification number: G01J5/0088 , F01D17/085 , F01D25/30 , F05D2270/8041 , G01J5/0014 , G01J2005/0077 , G01J2005/106
Abstract: Various embodiments include systems and apparatuses adapted for detecting two-dimensional turbomachine exhaust temperature. In some embodiments, a system includes a two-dimensional grid sized to mount within an exhaust path of a gas turbomachine, a radiation detection device for detecting radiation emitted from the two-dimensional grid at a plurality of points on the two-dimensional grid, the radiation detection device being mountable proximate the exhaust path and the two-dimensional grid and at least one computing device connected with the radiation detection device, the at least one computing device configured to generate a planar map of the temperature of the exhaust from the gas turbomachine based upon the intensity of the radiation emitted from two-dimensional grid detected at the plurality of points on the two-dimensional grid.
Abstract translation: 各种实施例包括适于检测二维涡轮机排气温度的系统和装置。 在一些实施例中，系统包括尺寸设置成安装在气体涡轮机的排气路径内的二维网格，用于检测在二维网格上的多个点处从二维网格发射的辐射的辐射检测装置， 所述辐射检测装置可安装在所述排气路径和所述二维栅格附近，以及与所述辐射检测装置连接的至少一个计算装置，所述至少一个计算装置被配置为生成来自所述气体的排气温度的平面图 基于在二维网格上的多个点处检测到的从二维网格发射的辐射的强度的涡轮机。
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公开(公告)号：US11035247B2
公开(公告)日：2021-06-15
申请号：US15088768
申请日：2016-04-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner , Scott Francis Johnson , James Joseph Murray
Abstract: A turbine apparatus is disclosed including a first article and a second article disposed between the first article and a hot gas path of a turbine. The first article includes at least one first article cooling channel in fluid communication with and downstream from a cooling fluid source, and the second article includes at least one second article cooling channel in fluid communication with and downstream from the at least one first article cooling channel. A method for redundant cooling of the turbine apparatus is disclosed including flowing a cooling fluid from the cooling fluid source through at least one first article cooling channel, exhausting the cooling fluid from the at least one first article cooling channel into at least one second article cooling channel, and flowing the cooling fluid through the at least one second article cooling channel.
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公开(公告)号：US20180334910A1
公开(公告)日：2018-11-22
申请号：US15599912
申请日：2017-05-19
Applicant: General Electric Company
Inventor： Sandip Dutta , Scott Francis Johnson , Joseph Anthony Weber
CPC classification number: F01D5/189 , F01D5/147 , F01D5/187 , F01D5/188 , F05D2250/184 , F05D2260/20 , F05D2260/201 , F05D2260/202 , F05D2260/2214 , F05D2260/38
Abstract: The present disclosure is directed to a cooling system for a turbomachine. The cooling system includes a turbomachine component defining a turbomachine component cavity. The cooling system also includes an insert positioned within the turbomachine component cavity for cooling the turbomachine component. The insert includes an insert body and a spring body. The spring body includes a first portion fixedly coupled to the insert body, a second portion in sliding engagement with the turbomachine component, and a third portion in sliding engagement with the insert body.
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