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公开(公告)号：US09587505B2
公开(公告)日：2017-03-07
申请号：US14097753
申请日：2013-12-05
Applicant: General Electric Company
Inventor： Debabrata Mukhopadhyay , Xiaoqing Zheng
CPC classification number: F01D11/08 , F01D11/001 , F05D2240/56 , F16J15/3288 , F16J15/441 , F16J15/4472
Abstract: A seal arrangement between radially-opposed rotating and stationary components in a turbomachine includes a first rotating component, a second stationary component, and a brush seal located radially therebetween. The brush seal has an axially-extending portion secured to the second stationary component, and an inwardly-extending portion extending across a gap between the first and second components. An inner ring portion of the second stationary component is located radially inward of, and in engagement with the axially-extending portion and at least part of the inwardly-extending portion of the brush seal, wherein an end of the axially-extending portion of the brush seal remote from the inwardly-extending portion is sandwiched between a pair of side rails fixed between the inner ring portion and an outer ring portion of the second stationary component.
Abstract translation: 在涡轮机中的径向相对的旋转和静止部件之间的密封装置包括第一旋转部件，第二固定部件和径向位于其间的刷子密封件。 刷密封具有固定到第二固定部件的轴向延伸部分，以及延伸穿过第一和第二部件之间的间隙的向内延伸的部分。 第二固定部件的内环部分位于电刷密封件的轴向延伸部分和向内延伸部分的至少部分的径向内侧并与其接合，其中轴向延伸部分的端部 远离所述向内延伸部分的刷密封夹在固定在所述第二固定部件的所述内环部分和外环部分之间的一对侧轨之间。
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公开(公告)号：US10907545B2
公开(公告)日：2021-02-02
申请号：US15985737
申请日：2018-05-22
Applicant: General Electric Company
Inventor： Rajesh Mavuri , Debabrata Mukhopadhyay
Abstract: A cooling system for a turbine engine is provided. The turbine engine includes a compressor, a compressor discharge chamber (CDC), a combustor assembly, and a turbine coupled in a serial flow relationship such that a first portion of air from the CDC is channeled to the combustor assembly. The turbine is coupled to the compressor via a rotor. The cooling system includes an air duct configured to channel a second portion of air from the CDC to a mid-rotor region of the rotor, and a fluid supply system coupled to the air duct at a coupling. The fluid supply system is configured to channel a flow of fluid to the coupling. The coupling is configured to cool the second portion of CDC air via absorption of heat by the fluid from the second portion of CDC air.
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公开(公告)号：US10119471B2
公开(公告)日：2018-11-06
申请号：US14879470
申请日：2015-10-09
Applicant: General Electric Company
Inventor： Debabrata Mukhopadhyay , Pugalenthi Nandagopal , James Adaickalasamy
Abstract: A turbine engine assembly is provided. The assembly includes a compressor, and an air duct coupled in flow communication with the compressor. The air duct is configured to channel a flow of bleed air from the compressor therethrough. The assembly also includes a fluid supply system coupled in flow communication with the air duct, wherein the fluid supply system is configured to channel a flow of fluid towards the air duct to modify a temperature of the bleed air based on an operating condition of the turbine engine assembly.
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公开(公告)号：US20170101933A1
公开(公告)日：2017-04-13
申请号：US14879470
申请日：2015-10-09
Applicant: General Electric Company
Inventor： Debabrata Mukhopadhyay , Pugalenthi Nandagopal , James Adaickalasamy
CPC classification number: F02C7/185 , F01D11/24 , F01K23/10 , F02C3/04 , F02C7/14 , F05D2220/32 , F05D2220/72 , F05D2260/213
Abstract: A turbine engine assembly is provided. The assembly includes a compressor, and an air duct coupled in flow communication with the compressor. The air duct is configured to channel a flow of bleed air from the compressor therethrough. The assembly also includes a fluid supply system coupled in flow communication with the air duct, wherein the fluid supply system is configured to channel a flow of fluid towards the air duct to modify a temperature of the bleed air based on an operating condition of the turbine engine assembly.
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公开(公告)号：US09322287B2
公开(公告)日：2016-04-26
申请号：US14294812
申请日：2014-06-03
Applicant: General Electric Company
Inventor： Xiaoqing Zheng , Michael Dennis Mack , Debabrata Mukhopadhyay
CPC classification number: F01D11/001 , F01D5/225 , F01D11/127 , F04D29/083 , F04D29/102 , F05D2240/56 , F05D2250/312 , F05D2250/75 , F16J15/006 , F16J15/3288
Abstract: A brush seal for a turbine including an annular layer of filaments having a generally L-shape including an axial portion of the filaments and a radial portion of filaments, wherein a first end of the filaments is at an end of the radial portion and faces a rotating component of the turbine and a second end region of the filaments is at an end of the axial portion of the filaments and is fastened to a stationary component of the turbine.
Abstract translation: 一种用于涡轮机的刷子密封件，包括具有大致L形的细丝的环形层，其包括长丝的轴向部分和长丝的径向部分，其中长丝的第一端位于径向部分的端部并且面向 涡轮机的旋转部件和长丝的第二端部区域处于长丝的轴向部分的端部并且紧固到涡轮机的静止部件。
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Patent Agency Ranking
公开(公告)号：US10919119B2
公开(公告)日：2021-02-16
申请号：US16042355
申请日：2018-07-23
Applicant: General Electric Company
Inventor： Dheepa Srinivasan , Joydeep Pal , Debabrata Mukhopadhyay
IPC: B23P6/00 , B33Y10/00 , F01D5/00 , B23K26/342 , B22F3/105 , B22F5/00 , B22F5/04 , C22C1/04 , C22C33/02 , B22F7/06
Abstract: A method for repairing a component is disclosed. The method includes removing a portion originally including a plurality of cooling holes, of the component to form a cavity, forming by additive manufacturing a replacement portion including a plurality of cooling holes, and varying a surface roughness and a diameter of at least one cooling hole of the plurality of cooling holes during the forming by additive manufacturing the replacement portion. The replacement portion replaces the portion of the component.
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公开(公告)号：US20180202360A1
公开(公告)日：2018-07-19
申请号：US15408465
申请日：2017-01-18
Applicant: General Electric Company
Inventor： Debabrata Mukhopadhyay , Sanjeev Kumar Jain , Sendilkumaran Soundiramourty , Rajesh Mavuri , Jagdish Prasad Tyagi
CPC classification number: F02C7/18 , F01D5/085 , F01D25/12 , F01D25/24 , F02C7/28 , F05D2240/60 , F05D2260/213 , Y02E20/16
Abstract: A gas turbine casing with an internal heat exchange system. The gas turbine extends between an inlet section and an exhaust section and defines a downstream direction from the inlet section to the exhaust section. The casing includes a forward end, an aft end downstream of the forward end, a first exterior surface facing radially outward, a second exterior surface facing radially inward, and an internal body at least partially defined between the first exterior surface and the second exterior surface. The heat exchange system includes an inlet and an outlet formed in an exterior surface of the casing proximate the aft end, a supply bore extending upstream from the inlet through the interior body of the casing, and a return bore extending downstream to the outlet through the interior body of the casing.
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公开(公告)号：US20170107902A1
公开(公告)日：2017-04-20
申请号：US14886171
申请日：2015-10-19
Applicant: General Electric Company
Inventor： Pagalenthi Nandagopal , Rex allen Morgan , Sendikumaran Soundiramourty , Debabrata Mukhopadhyay
CPC classification number: F02C3/04 , F01D25/12 , F02C3/305 , F02C7/16 , F05D2220/32 , F05D2260/212 , F05D2270/112
Abstract: The present application provides a gas turbine engine intended to be used in part in hot ambient conditions. The gas turbine engine may include a compressor, a turbine with a wheel space adjacent to a number of rotor wheels, and a wheel space water cooling system in communication with the wheel space to provide a flow of water thereto.
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公开(公告)号：US20140154066A1
公开(公告)日：2014-06-05
申请号：US13693610
申请日：2012-12-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Debabrata Mukhopadhyay , Steven Sebastian Burdgick , Prashant Prabhakar Sankolli , Moorthi Subramaniyan
IPC: F01D9/02
CPC classification number: F01D5/187 , F01D5/186 , F01D9/02 , F01D11/001 , F05D2220/31 , F05D2240/122
Abstract: Various embodiments include a steam turbine nozzle and turbomachinery including such a nozzle. In various particular embodiments, a steam turbine nozzle includes: a body having: a first sidewall and a second sidewall opposite the first sidewall; a pressure side and a suction side each extending between the first sidewall and the second sidewall; and a leading edge section at a first junction of the pressure side and the suction side, and a trailing edge section at a second junction of the pressure side and the suction side; and a bypass fluid conduit including: a channel having an opening to at least one of the first sidewall or the second sidewall; and an outlet passageway fluidly connected with the channel between the first sidewall and the second sidewall, the outlet passageway including a first opening on at least one of the pressure side of the body, the suction side of the body or the trailing edge section.
Abstract translation: 各种实施例包括蒸汽轮机喷嘴和包括这种喷嘴的涡轮机械。 在各种具体实施例中，蒸汽轮机喷嘴包括：主体，其具有：与第一侧壁相对的第一侧壁和第二侧壁; 压力侧和吸力侧，每个在所述第一侧壁和所述第二侧壁之间延伸; 以及在压力侧和吸力侧的第一接合处的前缘部分和在压力侧和吸力侧的第二接合处的后缘部分; 以及旁通流体导管，包括：通道，具有至少一个第一侧壁或第二侧壁的开口; 以及出口通道，其与所述第一侧壁和所述第二侧壁之间的通道流体连接，所述出口通道包括在所述主体的所述压力侧，所述主体的吸力侧或所述后缘部分中的至少一个上的第一开口。
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公开(公告)号：US20180149085A1
公开(公告)日：2018-05-31
申请号：US15362202
申请日：2016-11-28
Applicant: General Electric Company
Inventor： Veerraju Chennoju , Debabrata Mukhopadhyay , Rohit Pruthi
IPC: F02C7/18
CPC classification number: F02C7/18 , F01D9/065 , F01D25/125 , F01D25/162 , F01D25/30 , F05D2260/232
Abstract: This application provides exhaust frame cooling systems for use with gas turbine engines. Example systems may include an exhaust system for use with a gas turbine engine. The exhaust system may include a strut positioned between an inner barrel and an outer barrel. The strut may include an inner body and an outer body. The exhaust system may include at least one strut hole formed in the inner body, where the at least one strut hole forms a first cooling path for cooling flow in a first direction, a cavity between the inner body and the outer body, where the cavity forms a second cooling path for the cooling flow in a second direction, and a purge outlet to purge the cooling flow at the inner barrel.
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