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公开(公告)号：US20170191373A1
公开(公告)日：2017-07-06
申请号：US14983779
申请日：2015-12-30
Applicant: General Electric Company
Inventor： Carlos Miguel Miranda , Stanley Kevin Widener
CPC classification number: F01D17/145 , F01D5/02 , F01D9/00 , F01D17/085 , F01D17/141 , F01D25/12 , F05D2220/30 , F05D2260/2212 , F05D2300/5021 , F16K31/002 , G05D23/02 , G05D23/022 , Y02T50/675
Abstract: A passive flow modulation device according to an embodiment includes: a temperature sensitive element disposed within a first area; a piston coupled to the temperature sensitive element, the piston extending through a wall to a second area, wherein the first area is at a higher temperature than the second area; and a valve arrangement disposed in the second area and actuated by a distal end portion of the piston, the valve arrangement tangentially injecting a supply of cooling air through an angled orifice from the second area into the first area in response an increase in temperature in the first area.
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公开(公告)号：US09267436B2
公开(公告)日：2016-02-23
申请号：US13845422
申请日：2013-03-18
Applicant: General Electric Company
Inventor： Lucas John Stoia , Patrick Benedict Melton , Stanley Kevin Widener , William Michael Poschel
Abstract: A fuel distribution manifold for a combustor of a gas turbine includes an annular flange having an outer surface that extends circumferentially around the flange. A primary fuel plenum extends circumferentially within the flange. A first orifice and a second orifice extend radially through the outer surface of the flange to provide for fluid communication into the primary fuel plenum. The first orifice includes an inlet that is adjacent to the outer surface. The second orifice includes an inlet that is adjacent to the outer surface. A fuel distribution cap extends partially across the outer surface of the flange. The fuel distribution cap includes an inlet port. A fuel distribution plenum is at least partially defined within the fuel distribution cap. The fuel distribution plenum is in fluid communication with the inlet port and with the first orifice inlet and the second orifice inlet.
Abstract translation: 用于燃气涡轮机的燃烧器的燃料分配歧管包括具有围绕凸缘周向延伸的外表面的环形凸缘。 主燃料增压室在凸缘内周向延伸。 第一孔口和第二孔口径向延伸穿过凸缘的外表面以提供流体连通到主燃料增压室中。 第一孔包括邻近外表面的入口。 第二孔包括与外表面相邻的入口。 燃料分配帽部分地延伸穿过凸缘的外表面。 燃料分配盖包括入口端口。 燃料分配室至少部分地限定在燃料分配盖内。 燃料分配气室与入口端口和第一孔口入口和第二孔口入口流体连通。
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13.发明申请TURBOMACHINE FUEL-AIR MIXER COMPONENT INCLUDING AN ADDITIVELY MANUFACTURED PORTION JOINED TO A NON-ADDITIVELY MANUFACTURED PORTION AND METHOD 有权涡轮发动机燃油混合器组件，包括加入非均质制造部件和方法的附加制造部件公开(公告)号：US20140361447A1
公开(公告)日：2014-12-11
申请号：US13911348
申请日：2013-06-06
Applicant: General Electric Company
Inventor： Stanley Kevin Widener , Attila Szabo
IPC: F23R3/04
CPC classification number: F23R3/04 , B01F3/04 , F02C1/00 , F02G3/00 , F23R3/286 , F23R2900/00018 , Y10T29/49229
Abstract: A turbomachine fuel-air mixer component includes a first component portion formed from a non-additive manufacturing process. The first component portion includes a plurality of tube elements each having an end portion. A second, additively manufactured component portion is additively joined to the first component portion. The second, additively manufactured component portion includes a plurality of additively manufactured tube sections constructed at, and fluidically connected with, respective ones of each end portion of the plurality of tube elements. The first and second component portions collectively defining at least a portion of the turbomachine fuel-air mixer component.
Abstract translation: 涡轮机械燃料 - 空气混合器部件包括由非附加制造工艺形成的第一部件部分。 第一部件部分包括多个具有端部的管件。 第二个相加制造的部件部分被附加地连接到第一部件部分。 第二个相加制造的部件部分包括多个相加制造的管部分，多个管元件的每个端部中的相应的部分构成并流体连接。 第一和第二部件部分共同限定了涡轮机燃料 - 空气混合器部件的至少一部分。
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公开(公告)号：US10731471B2
公开(公告)日：2020-08-04
申请号：US16235095
申请日：2018-12-28
Applicant: General Electric Company
Inventor： Stanley Kevin Widener , John McConnell Delvaux , Matthew Troy Hafner , James Zhang , Peter de Diego
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral portions in which: a base portion is made from a first material; and a top portion is made from a second material. The airfoil may include a connector securing the base portion to the top portion of the airfoil, wherein the connector comprises a wire-lock connector that includes: a tab extending from one of the base portion and the top portion; a complimentary slot for receiving the tab formed in the other one of the base portion and the top portion; a first groove formed in a side of the tab; a second groove formed in a side of the slot; a retaining aperture formed cooperatively via an alignment of the first and second grooves upon the tab being received into the slot; and a retaining wire housed within the retaining aperture.
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公开(公告)号：US20200173306A1
公开(公告)日：2020-06-04
申请号：US16205799
申请日：2018-11-30
Applicant: General Electric Company
Inventor： Stanley Kevin Widener
Abstract: Hot gas path (HGP) components for turbine systems are disclosed. The HGP component may include a body including a forward end, an aft end, and an inner portion positioned adjacent a hot gas flow path for the turbine system. The body may also include an outer portion formed radially opposite the inner portion, and a plurality of nozzles extending through the outer portion. Additionally, body may include an intermediate portion formed between the inner portion and the outer portion, and a plurality of venturi extending through the intermediate portion. The plurality of venturi may be in fluid communication with the plurality of nozzles.
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Patent Agency Ranking
公开(公告)号：US10337739B2
公开(公告)日：2019-07-02
申请号：US15237795
申请日：2016-08-16
Applicant: General Electric Company
Inventor： Stanley Kevin Widener , Carlos Miguel Miranda
Abstract: A combustor for a gas turbine, including: a combustor chamber; a casing enclosing the combustor chamber and defining an area therebetween for passing compressor discharge air into the combustor chamber for use in combustion; and at least one passive bypass valve for selectively extracting a portion of the compressor discharge air from the area between the combustor chamber and the casing to adjust a temperature in the combustor.
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公开(公告)号：US10094571B2
公开(公告)日：2018-10-09
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
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.
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公开(公告)号：US20170138267A1
公开(公告)日：2017-05-18
申请号：US14944298
申请日：2015-11-18
Applicant: General Electric Company
Inventor： Michael John Hughes , Stanley Kevin Widener , Jonathan Dwight Berry
CPC classification number: F02C7/222 , F02C7/22 , F05D2220/32 , F05D2240/35 , F23D14/62 , F23D14/64 , F23R3/04 , F23R3/045 , F23R3/10 , F23R3/12 , F23R3/14 , F23R3/28 , F23R3/286 , F23R3/32 , F23R3/36
Abstract: A bundled tube fuel nozzle assembly includes a fuel injector and a tube bundle comprising a plurality of tubes that provide for fluid communication through a forward plate, a fuel plenum and an aft plate of the bundled tube fuel nozzle assembly. Each tube includes an inlet defined at an upstream end of the tube and an outlet defined at a downstream end of the tube. The fuel injector is disposed upstream from the inlets of each of the tubes. The upstream end of each tube is noncircular and includes at least one side portion that abuts a complementary upstream end side portion of an immediately adjacent tube of the plurality of tubes. The downstream end of each tube may be circular and is spaced apart from the downstream ends of immediately adjacent tubes of the plurality of tubes.
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公开(公告)号：US09303562B2
公开(公告)日：2016-04-05
申请号：US13741797
申请日：2013-01-15
Applicant: General Electric Company
Inventor： Fabien Thibault Codron , John Edward Pritchard , Stanley Kevin Widener
Abstract: Methods and systems for operating a gas turbine engine including a fuel delivery system and a plurality of combustor assemblies are provided. The fuel delivery system comprises a primary fuel circuit configured to continuously supply fuel to each of the plurality of combustor assemblies during a first mode of operation and a second mode of operation. At least one secondary fuel circuit of the fuel delivery system is configured to supply fuel to each of the plurality of combustor assemblies during the second mode of operation. The secondary fuel circuit includes at least one isolation valve coupled in flow communication with each of the plurality of combustor assemblies. The at least one isolation valve facilitates preventing fluid flow upstream into the secondary fuel circuit during the first mode of operation. The fuel delivery system, using the isolation valve, replaces a purging system in the gas turbine engine.
Abstract translation: 提供了用于操作包括燃料输送系统和多个燃烧器组件的燃气涡轮发动机的方法和系统。 燃料输送系统包括主燃料回路，其被配置为在第一操作模式和第二操作模式期间向多个燃烧器组件中的每一个连续供应燃料。 燃料输送系统的至少一个次级燃料回路构造成在第二操作模式期间向多个燃烧器组件中的每一个供应燃料。 二次燃料回路包括与多个燃烧器组件中的每一个流体连通地连接的至少一个隔离阀。 所述至少一个隔离阀有助于在第一操作模式期间阻止在二次燃料回路中上游的流体流动。 使用隔离阀的燃料输送系统代替燃气涡轮发动机中的清洗系统。
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公开(公告)号：US10830442B2
公开(公告)日：2020-11-10
申请号：US15464400
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes , James Scott Flanagan
Abstract: A segmented annular combustion system with dual fuel capability includes an alternating arrangement of fuel injection modules and integrated combustor nozzles. The fuel injection module includes a bundled tube fuel nozzle portion and fuel injection lances, which are fluidly coupled via conduits to respective fuel plenums. A liquid fuel cartridge is disposed within the bundled tube fuel nozzle portion, within one of the plurality of fuel injection lances, or within both the bundled tube fuel nozzle portion and one of the plurality of fuel injection lances. A gas turbine having the segmented annular combustion system is also provided.
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