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1. 发明授权

US09587505B2 L brush seal for turbomachinery application 有权
标题翻译： L刷密封用于涡轮机械应用
公开(公告)号：US09587505B2
公开(公告)日：2017-03-07
申请号：US14097753
申请日：2013-12-05
申请人： General Electric Company
发明人： Debabrata Mukhopadhyay , Xiaoqing Zheng
IPC分类号： F01D11/08 , F16J15/32 , F01D11/00
CPC分类号： F01D11/08 , F01D11/001 , F05D2240/56 , F16J15/3288 , F16J15/441 , F16J15/4472
摘要： 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.
摘要翻译：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。

2. 发明授权

US10907545B2 Cooling system for a turbine engine 有权
公开(公告)号：US10907545B2
公开(公告)日：2021-02-02
申请号：US15985737
申请日：2018-05-22
申请人： General Electric Company
发明人： Rajesh Mavuri , Debabrata Mukhopadhyay
IPC分类号： F02C7/141 , F04D29/58 , F02C7/18 , F02C6/08 , F04D29/32 , F01D5/08 , F01D25/12
摘要： 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.

3. 发明授权

US10119471B2 Turbine engine assembly and method of operating thereof 有权
公开(公告)号：US10119471B2
公开(公告)日：2018-11-06
申请号：US14879470
申请日：2015-10-09
申请人： General Electric Company
发明人： Debabrata Mukhopadhyay , Pugalenthi Nandagopal , James Adaickalasamy
IPC分类号： F01D11/24 , F01K23/10 , F02C3/04 , F02C7/14 , F02C7/18
摘要： 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.

4. 发明申请

US20170101933A1 TURBINE ENGINE ASSEMBLY AND METHOD OF OPERATING THEREOF 审中-公开
公开(公告)号：US20170101933A1
公开(公告)日：2017-04-13
申请号：US14879470
申请日：2015-10-09
申请人： General Electric Company
发明人： Debabrata Mukhopadhyay , Pugalenthi Nandagopal , James Adaickalasamy
IPC分类号： F02C7/18 , F01K23/10 , F02C3/04
CPC分类号： F02C7/185 , F01D11/24 , F01K23/10 , F02C3/04 , F02C7/14 , F05D2220/32 , F05D2220/72 , F05D2260/213
摘要： 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.

5. 发明授权

US09322287B2 Brush seal for turbine 有权
标题翻译：涡轮刷刷密封
公开(公告)号：US09322287B2
公开(公告)日：2016-04-26
申请号：US14294812
申请日：2014-06-03
申请人： General Electric Company
发明人： Xiaoqing Zheng , Michael Dennis Mack , Debabrata Mukhopadhyay
IPC分类号： F16J15/32 , F01D11/02 , F01D11/00 , F04D29/08
CPC分类号： F01D11/001 , F01D5/225 , F01D11/127 , F04D29/083 , F04D29/102 , F05D2240/56 , F05D2250/312 , F05D2250/75 , F16J15/006 , F16J15/3288
摘要： 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.
摘要翻译：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。

6. 发明申请

US20180149085A1 EXHAUST FRAME COOLING VIA COOLING FLOW REVERSAL 审中-公开
公开(公告)号：US20180149085A1
公开(公告)日：2018-05-31
申请号：US15362202
申请日：2016-11-28
申请人： General Electric Company
发明人： Veerraju Chennoju , Debabrata Mukhopadhyay , Rohit Pruthi
IPC分类号： F02C7/18
CPC分类号： F02C7/18 , F01D9/065 , F01D25/125 , F01D25/162 , F01D25/30 , F05D2260/232
摘要： 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.

7. 发明申请

US20180027190A1 INFRARED NON-DESTRUCTIVE EVALUATION OF COOLING HOLES USING EVAPORATIVE MEMBRANE 审中-公开
公开(公告)号：US20180027190A1
公开(公告)日：2018-01-25
申请号：US15215632
申请日：2016-07-21
申请人： General Electric Company
发明人： Dheepa Srinivasan , Joel John Bosco , Debabrata Mukhopadhyay , Paul Stephen DiMascio
IPC分类号： H04N5/33 , G06T7/00 , G01J5/10 , G01F1/688 , G01J5/00
CPC分类号： H04N5/33 , G01F1/688 , G01J5/0014 , G01J5/10 , G01J2005/0077 , G01N25/72 , G06T7/0004 , G06T2207/30164
摘要： A system and method for thermal inspection of a component having at least one cooling hole is disclosed, that uses an evaporative membrane for direct evaporative cooling of an exhausted working fluid. A working fluid is supplied to at least one internal passage of a component that is configured to exhaust the working fluid from the internal passage sequentially through the cooling holes and the wetted evaporative membrane disposed in direct air-tight contact with the component. An imager captures a time series of images corresponding to a transient evaporative response of the exhausted working fluid to determine a plurality of temperature values for the exhausted working fluid after passage through the evaporative membrane. A processor circuit is configured to evaluate the transient evaporative response of the exhausted working fluid.

8. 发明申请

US20140193243A1 SEAL ASSEMBLY FOR TURBINE SYSTEM 有权
标题翻译：密封组件用于涡轮机系统
公开(公告)号：US20140193243A1
公开(公告)日：2014-07-10
申请号：US13738339
申请日：2013-01-10
申请人： GENERAL ELECTRIC COMPANY
发明人： Revanth Krishna Nallam , Debabrata Mukhopadhyay , Karthik Srinivasan
IPC分类号： F01D25/24
CPC分类号： F01D25/24 , F01D11/02
摘要： The disclosure includes a sealing assembly for a turbine system. In one embodiment, the sealing assembly is for a turbine having a rotor blade and a stator nozzle. The sealing assembly includes a pair of oppositely facing seal teeth including concave surfaces. The pair of oppositely facing seal teeth are positioned on one of the rotor blade and the stator nozzle, and are for sealingly engaging the other of the rotor blade and the stator nozzle during operation of the turbine.
摘要翻译：本公开包括用于涡轮机系统的密封组件。在一个实施例中，密封组件用于具有转子叶片和定子喷嘴的涡轮机。密封组件包括一对相对的密封齿，其包括凹面。一对相对的密封齿定位在转子叶片和定子喷嘴中的一个上，并且在涡轮机的运行期间用于密封地接合转子叶片和定子喷嘴中的另一个。

9. 发明授权

US10919119B2 Method for repairing a component by additive manufacturing 有权
公开(公告)号：US10919119B2
公开(公告)日：2021-02-16
申请号：US16042355
申请日：2018-07-23
申请人： General Electric Company
发明人： Dheepa Srinivasan , Joydeep Pal , Debabrata Mukhopadhyay
IPC分类号： B23P6/00 , B33Y10/00 , F01D5/00 , B23K26/342 , B22F3/105 , B22F5/00 , B22F5/04 , C22C1/04 , C22C33/02 , B22F7/06
摘要： 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.

10. 发明申请

US20180202360A1 Rotor Shaft Cooling 审中-公开
公开(公告)号：US20180202360A1
公开(公告)日：2018-07-19
申请号：US15408465
申请日：2017-01-18
申请人： General Electric Company
发明人： Debabrata Mukhopadhyay , Sanjeev Kumar Jain , Sendilkumaran Soundiramourty , Rajesh Mavuri , Jagdish Prasad Tyagi
IPC分类号： F02C7/18 , F02C3/04 , F02C3/14 , F02C7/28 , F01D25/24
CPC分类号： F02C7/18 , F01D5/085 , F01D25/12 , F01D25/24 , F02C7/28 , F05D2240/60 , F05D2260/213 , Y02E20/16
摘要： 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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