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公开(公告)号：US11156162B2
公开(公告)日：2021-10-26
申请号：US15987340
申请日：2018-05-23
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Kwanwoo Kim , Hiranya Kumar Nath
Abstract: A fluid manifold assembly for a gas turbine engine, the fluid manifold assembly including a walled conduit assembly defining a fluid passage therewithin. The fluid passage defines a pair of ends separated by a length. A connecting conduit is coupled to the end of the fluid passage and to the length of the fluid passage.
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公开(公告)号：US10941939B2
公开(公告)日：2021-03-09
申请号：US15714118
申请日：2017-09-25
Applicant: General Electric Company
Inventor： Owen Graham , Kwanwoo Kim , Nicholas Magina , Sharath Nagaraja , Fei Han
Abstract: The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.
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公开(公告)号：US10513984B2
公开(公告)日：2019-12-24
申请号：US14834467
申请日：2015-08-25
Applicant: General Electric Company
Inventor： Kwanwoo Kim , Fei Han , Owen Graham
IPC: F02C7/045 , F02C7/24 , F01D25/04 , F02C3/14 , F23R3/04 , F01D9/02 , F02C3/04 , F02C7/04 , F02C9/18 , F23R3/42
Abstract: In one aspect the present subject matter is directed to a system for suppressing acoustic noise within a combustion section of a gas turbine. The system includes at least one static structure disposed forward of a combustion chamber defined within the combustion section. The static structure at least partially defines a diffuser cavity upstream of the combustion chamber. A baffle plate is coupled to the static structure. The baffle plate and the static structure at least partially define an air plenum within the combustion section forward of the combustion chamber. The baffle plate includes an aperture that provides for fluid communication between the diffuser cavity and the air plenum. The at least one static structure and the baffle plate define a Helmholtz resonator within the combustion section.
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公开(公告)号：US20190093891A1
公开(公告)日：2019-03-28
申请号：US15714118
申请日：2017-09-25
Applicant: General Electric Company
Inventor： Owen Graham , Kwanwoo Kim , Nicholas Magina , Sharath Nagaraja , Fei Han
Abstract: The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.
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公开(公告)号：US20170342912A1
公开(公告)日：2017-11-30
申请号：US15164946
申请日：2016-05-26
Applicant: General Electric Company
Inventor： Kwanwoo Kim , Raymond Floyd Martell , Alfred Albert Mancini , Clayton S. Cooper
CPC classification number: F02C9/26 , F02C7/222 , F02C7/228 , F05D2220/32 , F05D2240/35 , F05D2260/964 , F23R3/28 , F23R3/346 , Y02T50/672
Abstract: A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to the fuel manifold and configured to fluidly connect to a fuel nozzle of the plurality of fuel nozzles when the fuel delivery system is installed in the gas turbine engine. In order to reduce an amount of hydraulic instability of a fuel flow through the fuel delivery system, at least one of the fuel manifold or the pigtail fuel line includes a means for damping a hydraulic instability within the fuel delivery system.
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Patent Agency Ranking
公开(公告)号：US09416974B2
公开(公告)日：2016-08-16
申请号：US14333603
申请日：2014-07-17
Applicant: General Electric Company
Inventor： David Kaylor Toronto , Kwanwoo Kim , Abdul Rafey Khan , Luis Flamand
CPC classification number: F23R3/286 , F23D2900/14004 , F23D2900/14021 , F23R3/16 , F23R3/34 , F23R3/346 , F23R2900/03045
Abstract: The present application provides a combustor. The combustor may include an air flow path with a flow of air therein. A flow obstruction may be positioned within the air flow path and cause a wake or a recirculation zone downstream thereof. A number of fuel injectors may be positioned downstream of the flow obstruction. The fuel injectors may inject a flow of fuel into the air flow path such that the flows of fuel and air in the wake or the recirculation zone do not exceed a flammability limit.
Abstract translation: 本申请提供了一种燃烧器。 燃烧器可包括其中具有空气流的气流通道。 流动障碍物可以位于空气流动路径内并且在其下游引起尾流或再循环区域。 多个燃料喷射器可以位于流动障碍物的下游。 燃料喷射器可将燃料流注入空气流动路径，使得尾气或再循环区域中的燃料和空气流不超过可燃性极限。
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公开(公告)号：US12134986B1
公开(公告)日：2024-11-05
申请号：US18420337
申请日：2024-01-23
Applicant: General Electric Company
Inventor： Hiranya Kumar Nath , Ravindra Shankar Ganiger , Kwanwoo Kim , Dharmaraj Pachaiappan , Vivekta Sharma
IPC: F02C7/24
Abstract: Systems, apparatus, articles of manufacture, and methods are disclosed for an acoustic damping device. An example apparatus includes a first channel defining a first volume, the first channel open on a first end and closed on a second end, a second channel surrounding the first channel and defining a second volume, and a plurality of discs oriented within the first channel, respective discs of the plurality of discs including an opening in a center of the respective disc to allow at least one of a fluid or acoustic oscillation to move from the first end to the second end, the first channel including a plurality of apertures dispersed along an outer wall of the first channel and between the plurality of discs, the apertures to facilitate transfer of at least one of the fluid or the acoustic oscillation from the first channel to the second channel.
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公开(公告)号：US12072100B1
公开(公告)日：2024-08-27
申请号：US18503751
申请日：2023-11-07
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Narasimhan Suresh Sahana , Kwanwoo Kim
Abstract: A combustor for an aircraft gas turbine engine includes a dome structure, a swirler assembly connected to the dome structure, and a cowl connected to the dome structure and defining a plenum between the dome structure and the cowl, and surrounding the swirler assembly. The cowl includes an airflow opening through an upstream wall portion of the cowl for providing a flow of compressed air into the plenum. In addition, the cowl includes a cowl steam channel therewithin and a plurality of steam injection nozzles that provide a flow of steam from the cowl steam channel into the plenum.
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公开(公告)号：US11686474B2
公开(公告)日：2023-06-27
申请号：US17192613
申请日：2021-03-04
Applicant: General Electric Company
Inventor： Kwanwoo Kim , Clayton Cooper , Steven Vise , Shai Birmaher , Pradeep Naik , Andrew Wickersham
CPC classification number: F23R3/286 , F02C7/22 , F23M20/005 , F05D2240/35 , F05D2260/963 , F23R2900/00014
Abstract: A gas turbine engine may include a combustion section having a fuel nozzle, a swirler, and a ferrule configured to mount and center the fuel nozzle with the swirler. The combustion section may further include a damper on a cold side of the combustion section. The damper may have an acoustic cavity, a damper neck, and a cavity feed hole. The damper may operate as Helmholtz cavity to absorb a hydrodynamic or acoustic instability present in a region within the swirler.
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公开(公告)号：US11536457B2
公开(公告)日：2022-12-27
申请号：US17138048
申请日：2020-12-30
Applicant: General Electric Company
Inventor： Owen Graham , Kwanwoo Kim , Nicholas Magina , Sharath Nagaraja , Fei Han
Abstract: The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.
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