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公开(公告)号：US11421884B2
公开(公告)日：2022-08-23
申请号：US17231750
申请日：2021-04-15
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Duane Douglas Thomsen , Michael A. Benjamin
Abstract: A System for Aerodynamic Premixer for Reduced Emissions comprising a premixer is generally cylindrical in form and defined by the relationship in physical space between a first ring, a second ring, and a plurality of radial vanes. The first and second rings are found to be generally equidistant, one from the other, at all points along their facing surfaces. Radial vanes connect the first ring to the second ring and thereby form the premixer.
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公开(公告)号：US11015808B2
公开(公告)日：2021-05-25
申请号：US13657924
申请日：2012-10-23
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Duane Douglas Thomsen
Abstract: A System for Aerodynamic Premixer for Reduced Emissions comprising a premixer is generally cylindrical in form and defined by the relationship in physical space between a first ring, a second ring, and a plurality of radial vanes. The first and second rings are found to be generally equidistant, one from the other, at all points along their facing surfaces. Radial vanes connect the first ring to the second ring and thereby form the premixer.
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公开(公告)号：US20190024899A1
公开(公告)日：2019-01-24
申请号：US15656194
申请日：2017-07-21
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Alfred Albert Mancini , Duane Douglas Thomsen , Michael Anthony Benjamin
Abstract: The present disclosure is directed to a fuel nozzle assembly for a gas turbine engine. The fuel nozzle assembly includes a centerbody extended along a nozzle centerline axis and generally concentric thereto and an outer sleeve surrounding the centerbody and extended along the nozzle centerline axis and generally concentric thereto. The centerbody defines an outer wall extended at least partially along the nozzle centerline axis in which the centerbody defines a first fuel passage therewithin and one or more first fuel exit openings through the outer wall. Each first fuel exit opening is discrete from another along the outer wall. The outer sleeve and centerbody together define a first air passage therebetween. The first fuel passage and the first fuel exit opening are in fluid communication with the first air passage. The fuel nozzle assembly provides a first flow of fuel through the first fuel passage and first exit opening and a first flow of air through the first air passage, the first flow of fuel defines a jet in crossflow mixing with the first flow of air.
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公开(公告)号：US20180266692A1
公开(公告)日：2018-09-20
申请号：US15459309
申请日：2017-03-15
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Alfred Albert Mancini , Duane Douglas Thomsen , Michael Anthony Benjamin
IPC: F23R3/34
CPC classification number: F23R3/343 , F23R3/28 , F23R2900/00004
Abstract: A fuel nozzle for a gas turbine engine includes an outer body defining a plurality of openings in an exterior surface. The fuel nozzle also includes a main injection ring disposed at least partially inside the outer body. The main injection ring includes a plurality of fuel posts extending into or through the plurality of openings of the outer body. The plurality of fuel posts include an LP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the LP fuel post extending in the top surface in a first direction relative to the centerline axis away from the main fuel orifice. The plurality of fuel posts also include an HP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the HP fuel post extending in the top surface fin a second direction relative to the centerline axis away from the main fuel orifice, the second direction being at least ninety degrees different than the first direction.
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公开(公告)号：US20160161123A1
公开(公告)日：2016-06-09
申请号：US14946109
申请日：2015-11-19
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Alfred Albert Mancini , Duane Douglas Thomsen
IPC: F23R3/28
CPC classification number: F23R3/28 , F02C7/22 , F02C7/222 , F02C7/224 , F02C7/232 , F02C7/262 , F02C9/34 , F23K5/06 , Y02T50/671
Abstract: In one aspect, a fuel supply system may include a fuel injector having a primary and a secondary pilot fuel nozzle in fluid communication with a primary and a secondary fuel circuit, respectively, and a main fuel nozzle in fluid communication with a main fuel circuit. The fuel injector may also define a by-pass fuel circuit connected between the primary circuit and the secondary circuit and/or the main circuit. The system may also include a primary fuel manifold configured to be fluidly connected to the primary pilot fuel nozzle via the primary fuel circuit. Moreover, the system may include a by-pass valve provided in operative association with the by-pass fuel circuit. The by-pass valve may be configured to be opened such that a portion of the fuel flowing through the primary circuit from the primary fuel manifold is directed to the secondary circuit and/or the main circuit.
Abstract translation: 在一个方面，燃料供应系统可以包括燃料喷射器，其具有分别与主燃料回路和次燃料回路流体连通的主要和次要先导燃料喷嘴以及与主燃料回路流体连通的主燃料喷嘴。 燃料喷射器还可以限定连接在初级电路和次级电路和/或主电路之间的旁路燃料电路。 该系统还可以包括主燃料歧管，其构造成经由主燃料回路流体地连接到主引燃燃料喷嘴。 此外，该系统可以包括与旁通燃料回路可操作地相关联的旁通阀。 旁通阀可以被构造成打开，使得从主燃料歧管流过主回路的燃料的一部分被引导到次级回路和/或主回路。
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Patent Agency Ranking
公开(公告)号：US11112117B2
公开(公告)日：2021-09-07
申请号：US16037389
申请日：2018-07-17
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Ying Huang , Duane Douglas Thomsen
Abstract: A fuel nozzle for a combustor assembly of a heat engine is generally provided. The fuel nozzle defines a fuel nozzle centerline therethrough and a radial direction extended from the nozzle centerline. The fuel nozzle includes a first wall extended along the radial direction. The first wall defines a first cooling passage and a second cooling passage each extended therethrough. The first cooling passage is defined at a first acute angle relative to the nozzle centerline. The second cooling passage is defined at a second acute angle 90 degrees or less relative to the first acute angle.
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公开(公告)号：US11054139B2
公开(公告)日：2021-07-06
申请号：US15907978
申请日：2018-02-28
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Duane Douglas Thomsen
Abstract: A fuel nozzle apparatus for a gas turbine engine includes: a first pilot fuel injector disposed on a centerline axis of the fuel nozzle which defines a direction of air flow through the fuel nozzle, the first pilot fuel injector being of a pressure atomizing type; an annular second pilot fuel injector at least partially surrounding the first pilot fuel injector, the second pilot fuel injector being of an air blast type and having a fuel outlet disposed axially downstream and radially outboard of the first pilot fuel injector; an annular venturi surrounding the first and second pilot fuel injectors, the venturi including a throat of minimum diameter; an array of inner swirl vanes extending between the first pilot fuel injector and the second pilot fuel injector; and an array of outer swirl vanes extending between the second pilot fuel injector and the venturi.
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公开(公告)号：US10823416B2
公开(公告)日：2020-11-03
申请号：US15673882
申请日：2017-08-10
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Daniel Kirtley , Duane Douglas Thomsen , Neeraj Kumar Mishra , Adam Robert Kahn
Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a bulkhead wall extended generally along a radial direction relative to a combustor centerline and a mixer disposed concentric to the nozzle centerline. The bulkhead wall defines one or more openings therethrough adjacent to a combustion chamber. Each of the openings defines a nozzle centerline extended along a lengthwise direction. The mixer comprises a retaining wall extended along a radial direction relative to the nozzle centerline and coupled to the upstream side of the bulkhead wall. The mixer further comprises an annular shroud extended at least partially through the one or more openings of the bulkhead wall. The mixer defines a cooling passage through the retaining wall and the annular shroud. The cooling passage defines an inlet opening through the retaining wall and an outlet opening through the annular shroud.
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公开(公告)号：US10591164B2
公开(公告)日：2020-03-17
申请号：US14645959
申请日：2015-03-12
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Duane Douglas Thomsen
Abstract: A fuel nozzle apparatus for a gas turbine engine includes: an annular outer body extending parallel to a centerline axis, with an exterior surface having a plurality of openings; a main injection ring disposed inside the outer body and including: a circumferential main fuel gallery; and a plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and aligned with one of the openings; a venturi disposed inside the main injection ring; an annular splitter disposed inside the venturi, and including inner and outer walls spaced-apart from each other defining a splitter cavity, and a plurality of discharge holes communicating with the splitter cavity; an array of outer swirl vanes extending between the venturi and the splitter; a pilot fuel injector within the splitter; and an array of inner swirl vanes extending between the splitter and the pilot fuel injector.
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公开(公告)号：US20200025384A1
公开(公告)日：2020-01-23
申请号：US16037389
申请日：2018-07-17
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Ying Huang , Duane Douglas Thomsen
Abstract: A fuel nozzle for a combustor assembly of a heat engine is generally provided. The fuel nozzle defines a fuel nozzle centerline therethrough and a radial direction extended from the nozzle centerline. The fuel nozzle includes a first wall extended along the radial direction. The first wall defines a first cooling passage and a second cooling passage each extended therethrough. The first cooling passage is defined at a first acute angle relative to the nozzle centerline. The second cooling passage is defined at a second acute angle 90 degrees or less relative to the first acute angle.
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