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公开(公告)号：US20180195725A1
公开(公告)日：2018-07-12
申请号：US15404637
申请日：2017-01-12
Applicant: General Electric Company
Inventor： William Thomas Bennett , Jared Peter Buhler , Craig Alan Gonyou
Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. The forward wall defines at least one channel inlet orifice. At least one sidewall defines at least one channel outlet orifice. At least one micro channel cooling circuit is defined between the one or more channel inlet orifices and the one or more channel outlet orifices.
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公开(公告)号：US20170159451A1
公开(公告)日：2017-06-08
申请号：US15162687
申请日：2016-05-24
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/20 , F05D2240/307 , F05D2260/202 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. A tip shelf can be defined in the pressure or suction sidewalls. A film hole can extend to the tip shelf, such that the film hole can be shaped to direct a flow of cooling fluid to the film hole to improve film cooling at the tip shelf.
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公开(公告)号：US20170159450A1
公开(公告)日：2017-06-08
申请号：US14960991
申请日：2015-12-07
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/20 , F05D2220/32 , F05D2240/307 , F05D2260/202 , Y02T50/671 , Y02T50/676
Abstract: A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.
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公开(公告)号：US20140202168A1
公开(公告)日：2014-07-24
申请号：US14220434
申请日：2014-03-20
Applicant: General Electric Company
Inventor： Jason David Shapiro , Jared Peter Buhler , Brian Kenneth Corsetti
CPC classification number: F01D11/08 , F01D9/04 , F01D11/18 , F01D25/246 , F05D2300/603
Abstract: A composite annular shroud supported by a support assembly including at least one ring and at least partially disposed within the ring. The shroud is biased against and in sealing engagement with an inner flange of the ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud. The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.
Abstract translation: 由支撑组件支撑的复合环形护罩，所述支撑组件包括至少一个环并至少部分地设置在所述环内。 护罩偏压抵靠环的内凸缘并与其密封接合。 三环组件包括设置在外环的径向向内设置的中环的径向向内的内环，并且护罩至少部分地设置在内环内。 至少三个定时销从中间环径向向内延伸穿过内圈中的槽，使其处于护罩中的凹口。 中间环可以是固定地连接到发动机主干的支撑环的后端。 安装销可以压配合到中间环的销孔中，并从中间环径向向外延伸穿过外环的径向孔。
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公开(公告)号：US11033845B2
公开(公告)日：2021-06-15
申请号：US15314536
申请日：2015-05-29
Applicant: General Electric Company
Inventor： Timothy Deryck Stone , Gregory Michael Laskowski , Robert Proctor , Curtis Stover , Robert Francis Manning , Victor Hugo Silva Correia , Jared Peter Buhler , Robert Carl Murray , Corey Bourassa, Jr. , Byron Andrew Pritchard , Jonathan Russell Ratzlaff
IPC: B01D45/16 , F02C7/18 , B04C3/06 , F02C6/08 , F01D5/18 , F01D9/06 , F02C7/052 , B04C3/00 , F02K3/04
Abstract: A turbine engine having a bypass fluid conduit coupled to the turbine section includes at least one particle separator located within the bypass fluid conduit to separate particles from a bypass fluid stream prior to the bypass stream reaching the turbine section for cooling. A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser, a particle outlet, an angular velocity decreaser downstream of the angular velocity increaser, and a bend provided between the angular velocity increaser and the angular velocity decreaser.
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Patent Agency Ranking
公开(公告)号：US10704425B2
公开(公告)日：2020-07-07
申请号：US15210783
申请日：2016-07-14
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Christopher Charles Glynn , Corey Bourassa , Monty Lee Shelton , Robert Francis Manning , Victor Hugo Silva Correia
IPC: B01D39/00 , F01D25/32 , B01D46/24 , B01D45/12 , B01D46/42 , F01D25/12 , F01D9/06 , B01D45/08 , B01D45/16 , B01D50/00
Abstract: An assembly for removing entrained particles from a fluid stream passing through a gas turbine engine includes a first particle remover, a second particle remover fluidly coupled which receives a particle-laden stream from the first particle remover, and a venturi having a fluidly coupled to the second particle remover to increase the pressure differential across the assembly.
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公开(公告)号：US10450951B2
公开(公告)日：2019-10-22
申请号：US14925190
申请日：2015-10-28
Applicant: General Electric Company
Inventor： John Joseph Rahaim , Corey Bourassa , Jared Peter Buhler , Jonathan Russell Ratzlaff
Abstract: A gas turbine engine comprising a cyclonic separator provides fluid communication between the compressor section and the turbine section. The cyclonic separator comprises an annular volume receiving a flow of cooling fluid from an inlet and dividing the airflow into a cleaner air outlet and a scavenge outlet. The flow of cooling fluid is provided to the cyclonic separator in a direction tangential to the annular volume such that a cyclonic flow of cooling fluid moves within the annular volume centrifugally separating particles entrained within the airflow to the radial outer area of the annular volume for removal through the scavenge outlet and providing a cleaner airflow to the cleaner air outlet.
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公开(公告)号：US10267161B2
公开(公告)日：2019-04-23
申请号：US14960924
申请日：2015-12-07
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
IPC: F01D5/18
Abstract: An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.
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公开(公告)号：US09845691B2
公开(公告)日：2017-12-19
申请号：US13662284
申请日：2012-10-26
Applicant: General Electric Company
CPC classification number: F01D9/041 , F01D5/189 , F01D25/00 , F05B2230/237 , F05D2240/81 , F05D2260/201 , Y02T50/676
Abstract: A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity.
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公开(公告)号：US11918943B2
公开(公告)日：2024-03-05
申请号：US17993082
申请日：2022-11-23
Applicant: General Electric Company
Inventor： Timothy Deryck Stone , Gregory Michael Laskowski , Robert Proctor , Curtis Stover , Robert Francis Manning , Victor Hugo Silva Correia , Jared Peter Buhler , Robert Carl Murray , Corey Bourassa , Byron Andrew Pritchard, Jr. , Jonathan Russell Ratzlaff
IPC: B01D45/16 , B04C3/00 , B04C3/06 , F01D5/18 , F01D9/06 , F02C6/08 , F02C7/052 , F02C7/18 , F02K3/04
CPC classification number: B01D45/16 , B04C3/06 , F01D5/189 , F01D9/065 , F02C6/08 , F02C7/052 , F02C7/18 , B04C2003/003 , B04C2003/006 , F02K3/04 , F05D2260/607 , Y02T50/60
Abstract: A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.
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