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公开(公告)号：US11421885B2
公开(公告)日：2022-08-23
申请号：US17231771
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：US10775048B2
公开(公告)日：2020-09-15
申请号：US15459345
申请日：2017-03-15
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Alfred Albert Mancini , Duane Douglas Thomsen
Abstract: A fuel nozzle for a gas turbine engine includes an outer body extending generally along a centerline axis and defining a plurality of openings in an exterior surface. The fuel nozzle additionally includes a main injection ring disposed at least partially inside the outer body, the main injection ring including a fuel post extending into or through one of the plurality of openings of the outer body. The fuel post defines a spray well and a main fuel orifice, the spray well defining a bottom surface, a side wall, and a taper in the bottom surface extending from the main fuel orifice towards the side wall.
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公开(公告)号：US10760793B2
公开(公告)日：2020-09-01
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：US20190049113A1
公开(公告)日：2019-02-14
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：US20180356095A1
公开(公告)日：2018-12-13
申请号：US15450308
申请日：2017-03-06
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Chad Holden Sutton , Duane Douglas Thomsen
CPC classification number: F23R3/283 , F02C3/04 , F05D2240/35 , F23R3/00 , F23R3/002 , F23R3/10 , F23R3/28 , F23R3/286
Abstract: A combustion section for gas turbine engine includes an inner liner, an outer liner, and a dome attached to the inner liner and to the outer liner. A heat shield is attached to the dome, with the dome, the heat shield, or both define an opening. The combustion section also includes a fuel nozzle extending at least partially into the opening, the fuel nozzle defining a fuel nozzle axis and a radial direction relative to the fuel nozzle axis. The fuel nozzle defines an aft end, the aft end of the fuel nozzle positioned forward of the aft surface of the heat shield along the fuel nozzle axis such that the aft end of the fuel nozzle defines a minimum separation from the aft surface of the heat shield along the fuel nozzle axis of at least about 0.15 inches.
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Patent Agency Ranking
公开(公告)号：US10041676B2
公开(公告)日：2018-08-07
申请号：US14794016
申请日：2015-07-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nayan Vinodbhai Patel , Kwanwoo Kim , Chad Holden Sutton , Duane Douglas Thomsen , Craig Alan Gonyou , Harris Daniel Abramson , James A. Russo , Robert Andrew Stowers , Shanwu Wang , Anquan Wang
Abstract: A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.
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公开(公告)号：US20170009986A1
公开(公告)日：2017-01-12
申请号：US14794016
申请日：2015-07-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nayan Vinodbhai Patel , Kwanwoo Kim , Chad Holden Sutton , Duane Douglas Thomsen , Craig Alan Gonyou , Harris Daniel Abramson , James A. Russo , Robert Andrews Stowers , Shanwu Wang , Anquan Wang
CPC classification number: F23R3/002 , F02C3/04 , F23R3/50 , F23R3/60 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
Abstract: A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.
Abstract translation: 提供了一种用于限定轴向方向的燃气涡轮发动机的燃烧器组件。 燃烧器组件通常包括衬套，环形圆顶和偏转板。 衬垫至少部分地限定燃烧室。 环形拱顶限定第一腔并且具有多个冲击孔，并且偏转板限定锥形表面和平坦表面，其中多个冷却孔限定穿过偏转板。 环形圆顶和偏转板被定位在一起以限定通过多个冲击孔与第一空腔流体连通的第二腔。 此外，第二空腔通过多个冷却孔与燃烧室流体连通。
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公开(公告)号：US09453461B2
公开(公告)日：2016-09-27
申请号：US14580301
申请日：2014-12-23
Applicant: General Electric Company
CPC classification number: F02C7/22 , F05D2220/32 , F23R3/283 , F23R3/346
Abstract: A gas turbine engine fuel nozzle apparatus includes: an annular outer body, the outer body extending parallel to a centerline axis, and having a generally cylindrical exterior surface extending between forward and aft ends, and having a plurality of openings passing through the exterior surface; an annular main injection ring disposed inside the outer body, the main injection ring including an annular array of fuel posts extending radially outward therefrom; a main fuel gallery extending within the main injection ring in a circumferential direction; a plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and extending through one of the fuel posts; and a suspension structure connecting the main injection ring to the outer body, the suspension structure configured to substantially rigidly locate the position of the main ring in axial and lateral directions while permitting controlled deflection in a radial direction.
Abstract translation: 燃气涡轮发动机燃料喷嘴装置包括：环形外体，外体平行于中心线轴线延伸，并且具有在前端和后端之间延伸的大致圆柱形外表面，并且具有穿过外表面的多个开口; 设置在所述外主体内的环形主注射环，所述主注射环包括从其径向向外延伸的燃料柱的环形阵列; 在主注射环内沿圆周方向延伸的主燃料库; 多个主燃料喷口，每个主燃料孔与主燃料通道连通并延伸通过其中一个燃料柱; 以及将所述主注射环连接到所述外体的悬挂结构，所述悬架结构构造成基本上将所述主环的位置基本上刚性地定位在轴向和横向方向上，同时允许沿径向方向受到控制。
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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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