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1. 发明公开

EP3246631A1 TRANSITION DUCT ASSEMBLY WITH LATE INJECTION FEATURES 有权转让
标题翻译：过渡管道组件具有注射功能
公开(公告)号：EP3246631A1
公开(公告)日：2017-11-22
申请号：EP17161635.2
申请日：2017-03-17
申请人： General Electric Company
发明人： LEBEGUE, Jeffrey Scott , MCMAHAN, Kevin Weston , FLANAGAN, James Scott
IPC分类号： F23R3/46 , F23R3/34 , F23R3/42
CPC分类号： F23R3/346 , F23R3/425 , F23R3/46 , F23R2900/03041 , F23R2900/03044
摘要： A turbomachine 10 includes a plurality of transition ducts 50 disposed in a generally annular array. Each of the plurality of transition ducts 50 includes an inlet 52 an outlet 54, and a passage 56 defining an interior 57 and extending between the inlet 52 and the outlet 54 and defining a longitudinal axis 90, a radial axis 94, and a tangential axis 92. The outlet 54, of each of the plurality of transition ducts 50 is offset from the inlet 52 along the longitudinal axis 90 and the tangential axis 92. The turbomachine 10 includes a support ring assembly downstream of the plurality of transition ducts 50 along a hot gas path 104, and a plurality of mechanical fasteners 200 connecting at least one transition duct 50 of the plurality of transition ducts 50 to the support ring assembly. The turbomachine 10 includes a late injection assembly 210 providing fluid communication for an injection fluid to flow into the interior 57 downstream of the inlet 52 of at least one transition duct 50 of the plurality of transition ducts 50.
摘要翻译：涡轮机10包括布置成大致环形阵列的多个过渡管道50。多个过渡导管50中的每一个包括入口52和出口54以及限定内部57并且在入口52和出口54之间延伸并限定纵向轴线90，径向轴线94和切向轴线的通道56 92.多个过渡导管50中的每一个的出口54沿着纵向轴线90和切向轴线92偏离入口52.涡轮机10包括在多个过渡导管50下游的支撑环组件热气路径104以及将多个过渡导管50中的至少一个过渡导管50连接到支撑环组件的多个机械紧固件200。涡轮机10包括后注射组件210，其提供流体连通以使注射流体流入多个过渡导管50的至少一个过渡导管50的入口52下游的内部57中。

2. 发明公开

EP3222817A1 TRANSITION DUCT ASSEMBLY WITH LATE INJECTION FEATURES 有权转让
标题翻译：过渡管道组件具有注射功能
公开(公告)号：EP3222817A1
公开(公告)日：2017-09-27
申请号：EP17160481.2
申请日：2017-03-13
申请人： General Electric Company
发明人： FLANAGAN, James Scott , MCMAHAN, Kevin Weston , LEBEGUE, Jeffrey Scott
IPC分类号： F01D9/02 , F23R3/46 , F23R3/34
CPC分类号： F02C7/222 , F01D5/02 , F01D9/023 , F05D2220/32 , F05D2270/08 , F23R3/346 , F23R3/46
摘要： A turbomachine 10 includes a plurality of transition ducts 50 disposed in a generally annular array. Each transition duct 50 includes an inlet 52, an outlet 54, and a passage 56 defining an interior 57 and extending between the inlet 52 and the outlet 54 and defining a longitudinal axis 90, a radial axis 94, and a tangential axis 92. The outlet 54 of each transition duct 50 is offset from the inlet 52 along the longitudinal axis 90 and the tangential axis 92. Each transition duct 50 further includes an upstream portion 170 and a downstream portion 172. The turbomachine 10 further includes a late injection assembly 250 disposed between the upstream portion 170 and the downstream portion 172 of a transition duct 50 and which provides fluid communication for an injection fluid to flow into the interior 57 downstream of the inlet 52 of the transition duct 50. The late injection assembly 250 includes a late injection ring 252.
摘要翻译：涡轮机10包括布置成大致环形阵列的多个过渡管道50。每个过渡管道50包括入口52，出口54和限定内部57并且在入口52和出口54之间延伸并限定纵向轴线90，径向轴线94和切向轴线92的通道56. 每个过渡管道50的出口54沿着纵向轴线90和切向轴线92从入口52偏移。每个过渡管道50还包括上游部分170和下游部分172.涡轮机10还包括后注射组件250 其布置在过渡管道50的上游部分170和下游部分172之间，并且提供流体连通以使注入流体流入过渡管道50的入口52下游的内部57中。晚注射组件250包括晚注入环252。

3. 发明公开

EP2247830A1 TURBINE COMPRISING A FLEXIBLE SEAL AND CORRESPONDING FLEXIBLE SEAL FOR A GAS TURBINE ENGINE 有权转让
标题翻译：柔性密封件综合涡轮机和相关的柔性密封件的燃气涡轮发动机
公开(公告)号：EP2247830A1
公开(公告)日：2010-11-10
申请号：EP08873312.6
申请日：2008-02-27
申请人： General Electric Company
发明人： CHILA, Ronald James , MCMAHAN, Kevin Weston , REPIKOV, Timur
IPC分类号： F01D9/02 , F02C7/28 , F01D11/00 , F16J15/10 , F16J15/08
CPC分类号： F01D9/023 , F01D11/005 , F02C7/28 , F05D2240/57 , F16J15/0887 , F16J15/104
摘要： A turbine includes a static member, a moveable member fluidly connected to the static member, and a flexible seal. The flexible seal includes a spring component having a base section mounted to one of the static member and the moveable member of the turbine and a plurality of biasing members. Each of the plurality of biasing members includes a first portion extending from the base section and a cantilevered portion. The flexible seal further includes a seal component provided on the cantilevered portion of each of the plurality of biasing members. The seal component is biased into contact with the other of the static member and the moveable member.

4. 发明授权

EP2247830B1 FLEXIBLE SEAL FOR A TURBINE AND CORRESPONDING TURBINE 有权转让
公开(公告)号：EP2247830B1
公开(公告)日：2019-04-10
申请号：EP08873312.6
申请日：2008-02-27
申请人： General Electric Company
发明人： CHILA, Ronald James , MCMAHAN, Kevin Weston , REPIKOV, Timur
IPC分类号： F01D9/02 , F02C7/28 , F01D11/00 , F16J15/10 , F16J15/08

5. 发明公开

EP3584410A1 CURVED SEAL FOR ADJACENT GAS TURBINE COMPONENTS 有权转让
公开(公告)号：EP3584410A1
公开(公告)日：2019-12-25
申请号：EP19167788.9
申请日：2019-04-08
申请人： General Electric Company
发明人： SARAWATE, Neelesh N. , BERRY, Jonathan Dwight , DeFOREST, Russell Pierson , MCMAHAN, Kevin Weston , MORGAN, Victor John , SEZER, Ibrahim , TRIVEDI, Deepak
IPC分类号： F01D9/02 , F01D9/04 , F01D11/00 , F23R3/28
摘要： A flexible seal 160 for sealing between two adjacent gas turbine components includes a forward end 162, an aft end axially separated from the forward end, and an intermediate portion 164 between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.

6. 发明公开

EP3222820A1 TRANSITION DUCT ASSEMBLY 有权转让
标题翻译：过渡管道组件
公开(公告)号：EP3222820A1
公开(公告)日：2017-09-27
申请号：EP17162637.7
申请日：2017-03-23
申请人： General Electric Company
发明人： MCMAHAN, Kevin Weston , LEBEGUE, Jeffrey Scott , FLANAGAN, James Scott
IPC分类号： F01D9/02 , F01D11/00 , F01D25/26
CPC分类号： F01D9/023 , F01D11/003 , F01D11/005 , F01D25/265 , F01D25/28 , F05D2220/32 , F05D2240/55 , F05D2260/30 , F05D2260/31
摘要： A turbomachine (10) includes a plurality of transition ducts (50) disposed in a generally annular array and including a first transition duct (130) and a second transition duct (132). Each of the plurality of transition ducts (50) includes an inlet (52), an outlet (54), and a passage (56) extending between the inlet (52, 162) and the outlet (54, 164) and defining a longitudinal axis (90), a radial axis (94), and a tangential axis (92), the outlet (54) of each of the plurality of transition ducts (50) offset from the inlet (52) along the longitudinal axis (90) and the tangential axis (92). The turbomachine further includes a support ring assembly downstream of the plurality of transition ducts (50) along a hot gas path (104), and a plurality of mechanical fasteners (200) connecting at least one transition duct (50) of the plurality of transition ducts (50) to the support ring assembly.
摘要翻译：涡轮机（10）包括以大致环形阵列布置并且包括第一过渡管道（130）和第二过渡管道（132）的多个过渡管道（50）。多个过渡导管（50）中的每一个都包括入口（52），出口（54）和在入口（52,162）和出口（54,164）之间延伸的通道（56）所述多个过渡导管（50）中的每一个的所述出口（54）沿着所述纵向轴线（90）偏离所述入口（52），所述轴线（90），径向轴线（94）和切向轴线（92）和切向轴线（92）。涡轮机还包括沿着热气体路径（104）在多个过渡管道（50）下游的支撑环组件，以及多个机械紧固件（200），其连接多个过渡部件导管（50）连接到支撑环组件。

7. 发明公开

EP3586062A1 COMBUSTION SYSTEM WITH AXIALLY STAGED FUEL INJECTION 有权转让
公开(公告)号：EP3586062A1
公开(公告)日：2020-01-01
申请号：EP18708289.6
申请日：2018-02-15
申请人： General Electric Company
发明人： MCMAHAN, Kevin Weston , BERRY, Jonathan Dwight , HUGHES, Michael John
IPC分类号： F23R3/34 , F23R3/06

8. 发明公开

EP3470628A1 AFT FRAME ASSEMBLY FOR GAS TURBINE TRANSITION PIECE 有权转让
公开(公告)号：EP3470628A1
公开(公告)日：2019-04-17
申请号：EP18198359.4
申请日：2018-10-02
申请人： General Electric Company
发明人： SIMMONS, Scott Robert , CHILA, Ronald James , DAVIS, Charles Lewis, III , CHEN, Wei , MCMAHAN, Kevin Weston
IPC分类号： F01D5/18 , F01D9/02 , F01D25/12
摘要： An aft frame assembly (92) for a gas turbine transition piece (72) has a main body (100) with an upstream facing surface (110), a downstream facing surface (112), a radially outer facing surface (114) and a radially inner facing surface (115). A plurality of feedhole inlets (120) are located on the upstream facing surface. Each of the feed hole inlets are coupled to one of a plurality of cooling channels (122) passing through the main body towards the radially inner facing surface. A plurality of microchannels (124) are formed near the radially inner facing surface and extend at least partially along the downstream facing surface. The cooling channels are connected to and terminate in the microchannels. A pre-sintered preform (126) is located on the radially inner facing surface of the main body.

9. 发明授权

EP3222818B1 TRANSITION DUCT ASSEMBLY 失效
公开(公告)号：EP3222818B1
公开(公告)日：2019-02-13
申请号：EP17161006.6
申请日：2017-03-15
申请人： General Electric Company
发明人： FLANAGAN, James Scott , MCMAHAN, Kevin Weston , LEBEGUE, Jeffrey Scott
IPC分类号： F01D9/02

10. 发明公开

EP3372795A1 TRANSITION SEAL SYSTEM AND CORRESPONDING METHOD FOR COOLLING THE TRANSITION SEAL SYSTEM 有权转让
公开(公告)号：EP3372795A1
公开(公告)日：2018-09-12
申请号：EP18160305.1
申请日：2018-03-06
申请人： General Electric Company
发明人： BIDKAR, Rahul Anil , SARAWATE, Neelesh Nandkumar , MCMAHAN, Kevin Weston , CHILA, Ronald James
IPC分类号： F01D25/30 , F01D25/24 , F01D25/08 , F01D25/12 , F01D25/28 , F01D9/02 , F01D11/00 , F23R3/00
CPC分类号： F01D25/12 , F01D9/023 , F01D11/003 , F01D11/005 , F01D25/08 , F01D25/243 , F01D25/28 , F01D25/30 , F04D29/545 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F05D2260/201 , F23R3/002 , F23R3/005 , F23R3/60 , F23R2900/00012
摘要： A system includes a web plate (36) axially disposed between a transition piece (32) and a turbine nozzle (34). The web plate (36) includes a radial arm (114) extending in a radial direction between an inner surface (112) and an outer surface (110) of the web plate (36). The radial arm (114), the inner surface (112), and the outer surface (110) are disposed about an axial passage (82) configured to facilitate a flow of combustion products (61) from the transition piece (32) to the turbine nozzle (34). The transition piece (32) is disposed within a compressor discharge cavity (28) configured to receive an oxidant (60). The radial arm (114) includes an upstream face (134) in fluid communication with the compressor discharge cavity (28). The radial arm (114) also includes an arm passage (172, 173, 174, 175) that extends an axial length (182) in an axial direction (72) from the upstream face (134) through at least an axial depth (180) of the radial arm (114). The arm passage (172, 173, 174, 175) is configured to receive a portion of the oxidant (60) through the upstream face (134).

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