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公开(公告)号：US09932838B2
公开(公告)日：2018-04-03
申请号：US14977228
申请日：2015-12-21
Applicant: General Electric Company
CPC classification number: F01D5/187 , F02C3/04 , F05D2220/32 , F05D2240/305 , F05D2240/307 , F05D2250/185 , F05D2260/202
Abstract: A cooling system according to an embodiment includes: a three-pass serpentine cooling circuit; and an air feed cavity for supplying cooling air to the three-pass serpentine cooling circuit; wherein the three-pass serpentine cooling circuit extends radially outward from and at least partially covers at least one central plenum and a first set of near wall cooling channels of a multi-wall blade.
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公开(公告)号：US09909427B2
公开(公告)日：2018-03-06
申请号：US14978235
申请日：2015-12-22
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , David Wayne Weber
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/304 , F05D2260/201 , F05D2260/203 , F05D2260/22141 , Y02T50/676
Abstract: One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section; and a pressure side panel having a third pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.
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公开(公告)号：US20180051575A1
公开(公告)日：2018-02-22
申请号：US15239968
申请日：2016-08-18
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D5/186 , F01D9/02 , F01D25/12 , F02C3/04 , F05D2220/32 , F05D2240/303 , F05D2240/35 , F05D2260/201 , F05D2260/202
Abstract: A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the first leading edge cavity with a second leading edge cavity.
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公开(公告)号：US20170328218A1
公开(公告)日：2017-11-16
申请号：US15152690
申请日：2016-05-12
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D9/041 , F05D2240/121 , F05D2240/303 , F05D2250/18 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/676
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
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公开(公告)号：US09759081B2
公开(公告)日：2017-09-12
申请号：US14049020
申请日：2013-10-08
Applicant: General Electric Company
Inventor： Victor John Morgan , Gregory Thomas Foster , Neelesh Nandkumar Sarawate , David Wayne Weber
CPC classification number: F01D11/08 , F01D9/041 , F01D11/003 , F05D2230/60 , F05D2260/38 , Y10T29/4932
Abstract: A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member.
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Patent Agency Ranking
公开(公告)号：US20170175548A1
公开(公告)日：2017-06-22
申请号：US14977270
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster
CPC classification number: F01D5/187 , F01D5/186 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/202 , F05D2260/204 , Y02T50/676
Abstract: A cooling system according to an embodiment includes: a leading edge cooling circuit including a pressure side serpentine circuit and a suction side serpentine circuit; a first mid-blade cooling circuit including a suction side serpentine circuit; a second mid-blade cooling circuit including a pressure side serpentine circuit; a trailing edge cooling circuit; and at least one air feed for supplying cooling air to the leading edge cooling circuit, the first mid-blade cooling circuit, the second mid-blade cooling circuit, and the trailing edge cooling circuit.
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公开(公告)号：US20170175545A1
公开(公告)日：2017-06-22
申请号：US14977200
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Gregory Thomas Foster , Elisabeth Kraus Black , Michelle Jessica Iduate , Brendon James Leary , Jacob Charles Perry, II , David Wayne Weber
CPC classification number: F01D5/187 , F05D2230/10 , F05D2240/81 , F05D2260/202
Abstract: A cooling system for a turbine bucket including a multi-wall blade and a platform. A cooling circuit for the multi-wall blade includes: an outer cavity circuit and a central cavity for collecting cooling air from the outer cavity circuit; a platform core air feed for receiving the cooling air from the central cavity; and an air passage for fluidly connecting the platform core air feed to a platform core of the platform.
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公开(公告)号：US20170175541A1
公开(公告)日：2017-06-22
申请号：US14977102
申请日：2015-12-21
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Gary Michael Itzel , Brendon James Leary , Joseph Anthony Weber
CPC classification number: F01D5/187 , F01D5/18 , F01D5/186 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2240/127 , F05D2240/307 , F05D2240/35 , F05D2260/202 , F05D2260/22141
Abstract: A cooling system according to an embodiment includes: a pin fin bank cooling circuit; and an air feed cavity for supplying cooling air to the pin fin bank cooling circuit; wherein the pin fin bank cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade and a first set of near wall cooling channels of the multi-wall blade.
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公开(公告)号：US20170173672A1
公开(公告)日：2017-06-22
申请号：US14977028
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Gregory Thomas Foster , David Wayne Weber , Michelle Jessica Iduate , Brendon James Leary , Joseph Anthony Weber
CPC classification number: B22C9/103 , B22C9/108 , B22C9/12 , B22C9/24 , B22C21/14 , F01D5/187 , F05D2220/32 , F05D2230/21 , F05D2260/20 , G01B17/02 , G01B21/08
Abstract: A core for a turbine airfoil casting according to an embodiment includes: a center plenum section; and a plurality of outer passage sections; wherein the center plenum section includes at least one boss extending outwardly from the center plenum to an outer profile of the core.
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公开(公告)号：US20160169520A1
公开(公告)日：2016-06-16
申请号：US14567791
申请日：2014-12-11
Applicant: General Electric Company
Inventor： Lewis Berkley Davis, Jr. , Gregory Thomas Foster , Kaitlin Marie Graham , Krishnakumar Venkataraman , Stanley Kevin Widener
IPC: F23R3/20
CPC classification number: F23R3/34 , F02C9/28 , F23N1/00 , F23N5/003 , F23N2023/04 , F23N2023/08 , F23N2041/20 , F23R2900/03341
Abstract: Embodiments of the present disclosure provide an apparatus including: a first injector located on a surface of a turbine nozzle of a turbine stage positioned downstream of a reheat combustor, wherein the turbine stage includes the turbine nozzle and a turbine blade row; a second injector located on a wall of the reheat combustor; and at least one conduit in fluid communication with each of the first injector and the second injector, wherein the at least one conduit delivers at least one of a fuel from a fuel supply line and a carrier gas to an aft section of the reheat combustor through at least one of the first injector and the second injector, and wherein the aft section is positioned downstream of a combustion reaction zone in the reheat combustor.
Abstract translation: 本公开的实施例提供了一种装置，包括：位于涡轮级的涡轮喷嘴的位于再热燃烧器下游的表面的第一喷射器，其中涡轮级包括涡轮喷嘴和涡轮叶片排; 位于再热燃烧器的壁上的第二喷射器; 以及与所述第一注射器和所述第二注射器中的每一个流体连通的至少一个管道，其中所述至少一个管道将来自燃料供应管线和载气的燃料中的至少一个输送到所述再热燃烧室的后部，通过 所述第一喷射器和所述第二喷射器中的至少一个，并且其中所述后部段位于所述再热燃烧器中的燃烧反应区的下游。
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