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公开(公告)号：US11313560B2
公开(公告)日：2022-04-26
申请号：US16038758
申请日：2018-07-18
Applicant: General Electric Company
Inventor： Anne Dord , Nayan Vinodbhai Patel
Abstract: A combustor assembly for a heat engine is generally provided. The combustor assembly defines a fuel nozzle centerline and a radial direction extended from the nozzle centerline. The combustor assembly includes a fuel nozzle disposed at least partially concentric to the nozzle centerline. The fuel nozzle defines a fuel injection opening. A deflector assembly is defined around the nozzle centerline extended therethrough. The deflector assembly includes a deflector wall extended at least partially along the radial direction. The deflector assembly includes a conical portion defined around the nozzle centerline. The conical portion defines a fuel nozzle opening. A plurality of openings is defined through the conical portion radially adjacent to the fuel injection opening at the fuel nozzle.
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公开(公告)号：US20210285642A1
公开(公告)日：2021-09-16
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：US20210277796A1
公开(公告)日：2021-09-09
申请号：US16809830
申请日：2020-03-05
Applicant: General Electric Company
Inventor： Michael Scott McCambridge , Nayan Vinodbhai Patel , Eric John Kress , Kevin Richard Graziano , Brendon Matthew Leeker
Abstract: A method and system for fuel nozzle cleaning during engine operation is provided. The steps or operations include operating the compressor section to provide the flow of oxidizer to the combustion chamber, operating the fuel system at a first fuel flow condition, in which the first fuel flow condition provides a fuel-oxidizer ratio at the combustion chamber, operating the fuel system at a second fuel flow condition, in which the second fuel flow condition provides the fuel-oxidizer ratio at the combustion chamber equal at the first fuel flow condition and the second fuel flow condition, and operating the fuel system at a third fuel flow condition after operating the fuel system at the second fuel flow condition.
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公开(公告)号：US20210231307A1
公开(公告)日：2021-07-29
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：US10739006B2
公开(公告)日：2020-08-11
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
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 f in 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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Patent Agency Ranking
公开(公告)号：US10352570B2
公开(公告)日：2019-07-16
申请号：US15086384
申请日：2016-03-31
Applicant: General Electric Company
Inventor： Krishnakumar Venkatesan , Michael Anthony Benjamin , Shih-Yang Hsieh , Yuxin Zhang , Owen James Sullivan Rickey , Nayan Vinodbhai Patel , Duane Douglas Thomsen , Kevin Vandevoorde
Abstract: A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.
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公开(公告)号：US20180216825A1
公开(公告)日：2018-08-02
申请号：US15422759
申请日：2017-02-02
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , James Russo , Duane Douglas Thomsen , Daniel Kirtley
Abstract: A combustor assembly for a gas turbine engine includes a dome and a deflector positioned adjacent to the dome. One or both of the dome and the deflector define an opening, a component axis extending through the opening, and a radial direction relative to the component axis. The combustor assembly also includes a retainer having an outer member contacting the dome, the deflector or both. The outer member of the retainer defines at least in part a retainer cavity inward of the outer member along the radial direction. The dome, the deflector, or both define a plurality of cooling holes for providing a cooling airflow from the retainer cavity to the opening.
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公开(公告)号：US10012387B2
公开(公告)日：2018-07-03
申请号：US14946109
申请日：2015-11-19
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Alfred Albert Mancini , Duane Douglas Thomsen
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.
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公开(公告)号：US10001281B2
公开(公告)日：2018-06-19
申请号：US14689765
申请日：2015-04-17
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 and having an exterior surface, and having a ring of forward openings passing through the exterior surface, and a ring of aft openings passing through the exterior surface, the aft openings positioned axially aft of the forward openings; an annular main injection ring disposed inside the outer body and including: a forward main fuel gallery extending in a circumferential direction; an aft main fuel gallery extending in a circumferential direction; a ring of forward main fuel orifices communicating with the forward main fuel gallery and each aligned with one of the forward openings; a ring of aft main fuel orifices, communicating with the aft main fuel gallery and each aligned with one of the aft openings; and a pilot fuel injector disposed along the centerline axis.
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公开(公告)号：US20170284678A1
公开(公告)日：2017-10-05
申请号：US15086384
申请日：2016-03-31
Applicant: General Electric Company
Inventor： Krishnakumar Venkatesan , Michael Anthony Benjamin , Shih-Yang Hsieh , Yuxin Zhang , Owen James Sullivan Rickey , Nayan Vinodbhai Patel , Duane Douglas Thomsen , Kevin Vandevoorde
CPC classification number: F23R3/38 , F02C7/22 , F23D2900/11101 , F23R3/14 , F23R3/28
Abstract: A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.
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