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公开(公告)号：US20230226476A1
公开(公告)日：2023-07-20
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
CPC classification number: B01D45/16 , B04C3/06 , F01D5/189 , F01D9/065 , F02C6/08 , F02C7/18 , F02C7/052 , B04C2003/003 , F05D2260/607
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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公开(公告)号：US20190046999A9
公开(公告)日：2019-02-14
申请号：US14713119
申请日：2015-05-15
Applicant: General Electric Company
IPC: B04C3/06
Abstract: An inertial separator for removing particles from a fluid stream includes a body defining a through passage, with at least one separator inlet and at least one separator outlet, a turn provided in the body between the at least one separator inlet and the at least one separator outlet, and a flow splitter having at least one particle outlet fluidly coupled to the outside of the through passage.
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公开(公告)号：US20160045923A1
公开(公告)日：2016-02-18
申请号：US14713119
申请日：2015-05-15
Applicant: General Electric Company
IPC: B04C3/06
CPC classification number: B04C3/06 , B01D45/04 , B01D45/16 , B04C3/00 , B04C2003/003 , F01D5/081 , F01D11/08 , F05D2260/607 , Y02T50/676
Abstract: An inertial separator for removing particles from a fluid stream includes a body defining a through passage, with at least one separator inlet and at least one separator outlet, a turn provided in the body between the at least one separator inlet and the at least one separator outlet, and a flow splitter having at least one particle outlet fluidly coupled to the outside of the through passage.
Abstract translation: 用于从流体流中除去颗粒的惯性分离器包括限定穿过通道的主体，具有至少一个分离器入口和至少一个分离器出口，设置在主体中的至少一个分离器入口与至少一个分离器 出口和分流器，其具有流体地联接到通路的外部的至少一个颗粒出口。
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公开(公告)号：US20210275951A1
公开(公告)日：2021-09-09
申请号：US17325650
申请日：2021-05-20
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
Abstract: A turbine engine having an inducer assembly. The inducer assembly includes a centrifugal separator fluidly coupled to an inducer with an inducer inlet and an inducer outlet. The centrifugal separator includes a body, an angular velocity increaser to form a concentrated-particle stream and a reduced-particle stream, a flow splitter, and an exit conduit fluidly coupled to the body to receive the reduced-particle stream and define a separator outlet.
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公开(公告)号：US20160123154A1
公开(公告)日：2016-05-05
申请号：US14861522
申请日：2015-09-22
Applicant: General Electric Company
Inventor： Robert Francis MANNING , Victor Hugo Silva CORREIA , Jared Peter BUHLER , Byron Andrew PRITCHARD, JR. , William Collins Vining , Corey BOURASSA , Gregory Michael LASKOWSKI , David Vickery PARKER
IPC: F01D5/14
CPC classification number: F01D5/147 , F02C7/05 , F02C7/052 , F05D2260/607 , Y02T50/675
Abstract: An engine component for a turbine engine includes a particle collector having a substrate configured to retain at least some particles from a particle-laden stream passing through a portion of the engine. A fluid bypass around the substrate of the collector enables the particle-laden stream to bypass the substrate if the substrate is filled with particles.
Abstract translation: 用于涡轮发动机的发动机部件包括具有基板的颗粒收集器，该基板被配置为保持来自穿过发动机的一部分的载有颗粒的流的至少一些颗粒。 如果衬底填充有颗粒，围绕集电器衬底的流体旁路使得载有颗粒的流能绕过衬底。
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Patent Agency Ranking
公开(公告)号：US20250010231A1
公开(公告)日：2025-01-09
申请号：US18442719
申请日：2024-02-15
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
Abstract: A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft. A bypass conduit couples the compressor section to the turbine section. At least one centrifugal separator is fluidly coupled to the bypass stream, where the at least one centrifugal separator includes a body, a center body, a separator inlet, and a separator outlet fluidly coupled with the turbine section to output a reduced-particle stream that is provided to the turbine section for cooling. The centrifugal separator includes an angular velocity increaser, a flow splitter, a first outlet passage defined by an inner annular wall that receives the reduced-particle stream, and an angular velocity decreaser located downstream of the flow splitter. A second outlet passage receives the concentrated-particle stream.
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公开(公告)号：US20170114720A1
公开(公告)日：2017-04-27
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
CPC classification number: B01D45/16 , B04C3/06 , B04C2003/003 , B04C2003/006 , F02C6/08 , F02C7/18 , F05D2260/607 , Y02T50/675
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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公开(公告)号：US20170101896A1
公开(公告)日：2017-04-13
申请号：US15314341
申请日：2015-05-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Robert Francis MANNING , Timothy Deryck STONE , Jared Peter BUHLER , Victor Hugo Silva CORREIA , Gregory Michael LASKOWSKI , Robert Carl MURRAY , Jonathan Russell RATZLAFF , Robert PROCTOR , John Howard STARKWEATHER , Curtis Walton STOVER
CPC classification number: F01D25/32 , B01D45/16 , B04C3/00 , B04C3/06 , B04C2003/003 , B04C2003/006 , B64D33/08 , B64D2033/022 , B64D2033/024 , B64D2033/0246 , F01D5/08 , F01D25/12 , F02C3/04 , F02C7/05 , F02C7/052 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2240/35
Abstract: A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced-particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.
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公开(公告)号：US20170058684A1
公开(公告)日：2017-03-02
申请号：US14706003
申请日：2015-05-07
Applicant: General Electric Company
Inventor： Victor Hugo Silva CORREIA , Brian Kenneth CORSETTI , Mark BROOMER
CPC classification number: F01D9/041 , F01D9/04 , F01D25/005 , F01D25/10 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/128 , F05D2240/91 , F05D2250/185 , F05D2260/2212 , F05D2260/22141 , F05D2260/941 , F05D2300/50212
Abstract: A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.
Abstract translation: 燃气涡轮发动机弓形段包括弓形凸缘，其具有远离环形壁延伸的抗弦装置。 抗弦装置可以包括插入或结合到凸缘并且由环形壁不同的α材料制成。 抗弦装置可以是用于加热法兰的加热装置。 加热装置包括从嵌入凸缘中的周向延伸的加热流动通道到出口和出口，并且还可以包括用于加热流动通道的冷空气入口。 加热流路可以是具有起伏加热流路的蛇形加热流路。 涡轮喷嘴段包括在内和外弓形带段之间径向延伸的一个或多个翼型件，并且从外弧形带段径向延伸的前后外凸缘包括防弦装置。 弓形涡轮机护罩段包括具有防弦装置的前后导轨段。
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公开(公告)号：US20160369633A1
公开(公告)日：2016-12-22
申请号：US14901450
申请日：2014-07-03
Applicant: GENERAL ELECTRIC COMPANY
Inventor： George Joe-Kueng CHAN , Ronald Scott Bunker , Victor Hugo Silva CORREIA , Christopher Kanoa HOFFMAN
CPC classification number: F01D5/187 , F01D5/143 , F01D5/18 , F01D5/186 , F01D9/041 , F01D25/12 , F04D29/324 , F04D29/542 , F04D29/5846 , F05D2220/32 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: An airfoil comprises at least one wall defining a leading edge, a trailing edge, a pressure side extending between the leading edge and the trailing edge, and a suction side extending between the leading edge and the trailing edge. The airfoil is curved in three dimensions and has one or more cavities defined by an interior surface of the at least one wall. A plurality of cooling film holes extending between the cavity and at least one cooling trench located on at least one of the pressure side and the suction side, spaced from the leading edge. The at least one trench has a floor spaced from an outer surface of the airfoil. The plurality of cooling film holes extend through the floor at an angle other than perpendicular.
Abstract translation: 翼型件包括限定前缘，后缘，在前缘和后缘之间延伸的压力侧的至少一个壁和在前缘和后缘之间延伸的吸力侧。 翼型件在三维中弯曲并具有由至少一个壁的内表面限定的一个或多个空腔。 多个冷却膜孔，其在所述空腔和位于所述压力侧和所述吸入侧中的至少一个上的至少一个冷却沟槽之间延伸，与所述前缘间隔开。 至少一个沟槽具有与翼型件的外表面间隔开的底板。 多个冷却膜孔以与垂直不同的角度延伸穿过地板。
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