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公开(公告)号：US10060629B2
公开(公告)日：2018-08-28
申请号：US14627709
申请日：2015-02-20
Applicant: United Technologies Corporation
Inventor： Wookyung Kim , Zhongtao Dai , Kristin Kopp-Vaughan
Abstract: A combustor is provided. The combustor may comprise an axial fuel delivery system, and a radial fuel delivery system aft of the axial fuel delivery system. The radial fuel delivery system may be configured to direct fuel at least partially towards the axial fuel delivery system. A radial fuel delivery system is also provided. The system may comprise a combustor including a combustor liner, a mixer coupled to the combustor liner, and a nozzle disposed within the mixer, wherein the mixer and the nozzle are configured to direct fuel in a direction at least partially forward.
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公开(公告)号：US20180156464A1
公开(公告)日：2018-06-07
申请号：US15371653
申请日：2016-12-07
Applicant: United Technologies Corporation
Inventor： Zhongtao Dai , Lance L. Smith , Jeffrey M. Cohen
CPC classification number: F23R3/286 , F23R3/14 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
Abstract: A main mixer including a swirler along an axis, the swirler including an outer swirler with a multiple of outer vanes, and a center swirler with a multiple of center vanes and a swirler hub along the axis, the swirler hub including a fuel manifold and an inner swirler with a multiple of inner vanes that support a centerbody, the multiple of inner vanes interconnect the fuel manifold and the centerbody.
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公开(公告)号：US20180156463A1
公开(公告)日：2018-06-07
申请号：US15371615
申请日：2016-12-07
Applicant: United Technologies Corporation
Inventor： Zhongtao Dai , Lance L. Smith , Jeffrey M. Cohen
Abstract: A main mixer including a swirler along an axis, the swirler including an outer swirler with a multiple of outer vanes, and a center swirler with a multiple of center vanes and a swirler hub along the axis, the swirler hub including a fuel manifold and an inner swirler with a multiple of inner vanes that support a centerbody, the multiple of inner vanes interconnect the fuel manifold and the centerbody.
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公开(公告)号：US09791153B2
公开(公告)日：2017-10-17
申请号：US14634057
申请日：2015-02-27
Applicant: United Technologies Corporation
Inventor： Zhongtao Dai , Kristin Kopp-Vaughan , Dave Hyland , Russell B. Hanson , Lexia Kironn
CPC classification number: F23R3/28 , F02C3/04 , F02C7/22 , F05D2220/32 , F05D2240/35 , F23D17/002 , F23R3/14 , F23R3/286 , F23R3/343 , F23R3/36 , F23R3/60 , F23R2900/00004 , F23R2900/00018
Abstract: In various embodiments, a fuel injector may comprise a fuel nozzle and a pilot stage. The fuel nozzle may define a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area. The main fuel channel may be disposed about at least a portion of the simplex fuel channel. The secondary fuel channel may be disposed about at least a portion of the simplex fuel channel. The heat shield area may be configured to separate and protect the fuel channels from a heat load to prevent fuel coking. The pilot stage may be operatively coupled to the fuel nozzle and may be configured to receive fuel from the secondary fuel channel or the simplex fuel channel. The main stage may be operatively coupled to the fuel nozzle. The main stage may be configured to receive fuel from the main fuel channel.
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公开(公告)号：US20150219338A1
公开(公告)日：2015-08-06
申请号：US14335334
申请日：2014-07-18
Applicant: United Technologies Corporation
Inventor： Zhongtao Dai , Jeffrey M. Cohen , Kristin Kopp-Vaughan , James B. Hoke
CPC classification number: F23R3/346 , F02C7/22 , F23R3/06 , F23R3/34 , F23R3/50 , F23R2900/00013 , F23R2900/00014
Abstract: A combustor assembly includes a first wall, a second wall, a bulkhead and a plurality of fuel injectors. The bulkhead forms a combustion chamber with the first and the second walls. The fuel injectors are configured with the first wall in a unique and/or a fluctuating pattern.
Abstract translation: 燃烧器组件包括第一壁，第二壁，隔板和多个燃料喷射器。 隔板形成具有第一和第二壁的燃烧室。 燃料喷射器以唯一的和/或波动的图案配置有第一壁。
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Patent Agency Ranking
公开(公告)号：US10954859B2
公开(公告)日：2021-03-23
申请号：US15658464
申请日：2017-07-25
Applicant: United Technologies Corporation
Inventor： Zhongtao Dai , Lance L. Smith , Jeffrey M. Cohen
IPC: F02C7/22 , F02C3/04 , F02C9/26 , F23R3/26 , F23R3/28 , F23D11/38 , F23R3/34 , F23R3/14 , F23C7/00 , F02K3/06
Abstract: A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector.
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公开(公告)号：US20200348023A1
公开(公告)日：2020-11-05
申请号：US16402707
申请日：2019-05-03
Applicant: United Technologies Corporation
Inventor： Corneil S. Paauwe , Eva Wong , San Quach , Jeremy Styborski , Caroline Karanian , Lauryn M. Curtis , Steven D. Porter , Zhongtao Dai
Abstract: A gas turbine engine component assembly including: a first component having a first surface and a second surface opposite the first surface; a second component having a first surface and a second surface opposite the first surface of the second component; and a cooling circuit formed in the second component, the cooling circuit including an inlet at the second surface of the second component, an outlet at the first surface of the second component, an inward surface, and an outward surface, the inward surface and the outward surface being in a facing spaced relationship extending from the inlet to the outlet defining an airflow passageway therebetween, wherein the airflow passageway includes a parallel portion that is oriented about parallel to at least one of the first surface of the second component and the second surface of the second component.
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公开(公告)号：US10718524B2
公开(公告)日：2020-07-21
申请号：US15722634
申请日：2017-10-02
Applicant: United Technologies Corporation
Inventor： Zhongtao Dai , Jeffrey M. Cohen , Catalin G. Fotache , Lance L. Smith , Donald J. Hautman
Abstract: A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.
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公开(公告)号：US10228137B2
公开(公告)日：2019-03-12
申请号：US14914802
申请日：2014-08-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Kristin Kopp-Vaughan , Timothy S Snyder , Randolph J Smith , Zhongtao Dai
Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, the outer air swirler defines an outer annular air passage. An inner air swirler along the axis defines an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler, the annular fuel gas passage terminates with a multiple of skewed slots.
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公开(公告)号：US10907833B2
公开(公告)日：2021-02-02
申请号：US15109158
申请日：2015-01-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Zhongtao Dai , Adam Takashi Holley , Randal G. McKinney
Abstract: A combustor for a gas turbine engine comprises a combustion chamber having a pilot injector at one end and at least one main injector spaced radially from the pilot injector. The main injector includes a fluid flow path with a plug that restricts flow at least at an interior portion of the flow path. A gas turbine engine is also disclosed.
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