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公开(公告)号：US20190032559A1
公开(公告)日：2019-01-31
申请号：US15658464
申请日：2017-07-25
Applicant: United Technologies Corporation
Inventor： Zhongtao Dai , Lance L. Smith , Jeffrey M. Cohen
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：US10054312B2
公开(公告)日：2018-08-21
申请号：US14631499
申请日：2015-02-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Zhongtao Dai , Kristin Kopp-Vaughan
CPC classification number: F23R3/283 , F23R3/14 , F23R3/286 , F23R3/343 , F23R2900/03042 , Y02T50/675
Abstract: A mixer assembly for a gas turbine engine is provided, including a main mixer, and a pilot mixer having an annular housing. The pilot mixer can further include features to cool portions of the annular housing, such as a radial edge of the annular housing.
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Patent Agency Ranking
公开(公告)号：US09920932B2
公开(公告)日：2018-03-20
申请号：US14593877
申请日：2015-01-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Zhongtao Dai , Jeffrey M. Cohen , Catalin G. Fotache , Lance L. Smith , Donald J. Hautman
CPC classification number: F23R3/286 , F23C7/004 , F23R3/14 , F23R2900/03343
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：US20180045415A1
公开(公告)日：2018-02-15
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
CPC classification number: F23R3/286 , F23C7/004 , F23R3/14 , F23R2900/03343
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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25.发明申请DUAL FUEL NOZZLE WITH SWIRLING AXIAL GAS INJECTION FOR A GAS TURBINE ENGINE 审中-公开双燃料喷嘴，用于燃气涡轮发动机的旋转轴向气体注入公开(公告)号：US20160209038A1
公开(公告)日：2016-07-21
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
CPC classification number: F23R3/14 , F23C1/08 , F23D11/106 , F23D11/107 , F23D2900/11101 , F23R3/12 , F23R3/28 , F23R3/36 , Y02T50/675
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.
Abstract translation: 用于燃气涡轮发动机的燃烧器的燃料喷嘴包括沿轴线的外部空气旋流器，外部空气旋流器限定外部环形空气通道。 沿着轴线的内部空气旋流器限定围绕外部空气旋流器和内部空气旋流器之间的轴线的环形燃料气体通道，环形燃料气体通道以多个倾斜槽终止。
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26.发明申请Dual Fuel Nozzle With Liquid Filming Atomization for a Gas Turbine Engine 审中-公开双燃料喷嘴，用于燃气轮机发动机的液体雾化雾化公开(公告)号：US20160209037A1
公开(公告)日：2016-07-21
申请号：US14914825
申请日：2014-08-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Zhongtao Dai , Randolph J Smith , Kristin Kopp-Vaughan , Timothy S. Snyder , Donald J Hautman
Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler.
Abstract translation: 用于燃气涡轮发动机的燃烧器的燃料喷嘴包括沿轴线的外部空气旋流器，所述外部空气旋流器在外壁和内壁之间限定外部环形空气通道，外壁限定会聚发散喷嘴。 沿着轴线的内部空气旋流器限定其间的环形液体通道，环形液体通道终止在会聚发散喷嘴的上游，并且围绕外部空气旋流器和内部空气旋流器之间的轴线的环形燃料气体通道。
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公开(公告)号：US20150121882A1
公开(公告)日：2015-05-07
申请号：US14593877
申请日：2015-01-09
Applicant: United Technologies Corporation
Inventor： Zhongtao Dai , Jeffrey M. Cohen , Catalin G. Fotache , Lance L. Smith , Donald J. Hautman
IPC: F23R3/28
CPC classification number: F23R3/286 , F23C7/004 , F23R3/14 , F23R2900/03343
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.
Abstract translation: 提供了一种用于燃气涡轮发动机的混合器组件，包括具有位于至少一个径向旋流器和至少一个轴向旋流器之间的燃料喷射孔的主混合器，其中喷射到主混合器中的燃料被流过的空气雾化和分散 径向旋流器和轴向旋流器。
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