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公开(公告)号：US09068749B2
公开(公告)日：2015-06-30
申请号：US14155408
申请日：2014-01-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Albert K. Cheung
CPC classification number: F23R3/14 , F23D2900/11101 , F23D2900/14241 , F23R3/28 , F23R3/286
Abstract: A swirler for a gas turbine engine fuel injector comprises a swirler body extending from an upstream end to a downstream end. A fuel injector extends into the body, and has a downstream end for injecting fuel in a downstream direction. A first flow path directs air in a first circumferential direction about a central axis of the swirler body. A second flow path directs air to intermix with the air in the first flow path, and then to mix with fuel injected by the fuel injector. The first and second flow paths are positioned to inject air upstream of the downstream end of the fuel injector where fuel is injected. The first flow path is provided in a greater volume than the volume provided in the second flow path. The second flow path directs air at a location downstream of the first flow path.
Abstract translation: 用于燃气涡轮发动机燃料喷射器的旋流器包括从上游端延伸到下游端的旋流器主体。 燃料喷射器延伸到主体中，并且具有用于沿下游方向喷射燃料的下游端。 第一流路围绕旋流器主体的中心轴在第一圆周方向上引导空气。 第二流路引导空气与第一流路中的空气混合，然后与燃料喷射器喷射的燃料混合。 第一和第二流动路径被定位成在喷射燃料的燃料喷射器的下游端的上游喷射空气。 第一流路设置成比在第二流路中提供的体积更大的体积。 第二流路在第一流路的下游位置引导空气。
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公开(公告)号：US11143407B2
公开(公告)日：2021-10-12
申请号：US14895784
申请日：2014-06-11
Applicant: United Technologies Corporation
Inventor： James B. Hoke , Randal G. McKinney , Albert K. Cheung
Abstract: A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow.
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公开(公告)号：US10677161B2
公开(公告)日：2020-06-09
申请号：US14913922
申请日：2014-07-18
Applicant: United Technologies Corporation
Inventor： Christopher B. Lyons , Albert K. Cheung
Abstract: A diffuser for a gas turbine engine includes a diffuser housing that has a circumferential array of hollow struts that provide a cavity. The diffuser housing includes inlet and outlet apertures that are in fluid communication with the cavity. An opening on a trailing end of the struts is in fluid communication with the cavity. The diffuser housing is configured to introduce a fluid through the inlet aperture and receive a core flow through the opening. The fluid and core flow exit through the outlet aperture.
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公开(公告)号：US10533502B2
公开(公告)日：2020-01-14
申请号：US15478104
申请日：2017-04-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Albert K. Cheung
Abstract: A gas turbine engine may include a fuel manifold extending circumferentially around a diffuser case of the gas turbine engine. The fuel manifold may include a fuel supply inlet interface for receiving fuel into the fuel manifold and a plurality of fuel delivery outlet interfaces for delivering fuel to a combustor of the gas turbine engine. The gas turbine engine may also include a valve coupled to the fuel manifold. The valve may be configured to control fuel distribution in the fuel manifold. The valve may be disposed between two fuel delivery outlet interfaces of the plurality of fuel delivery outlet interfaces. The valve may be configured to at least decrease fuel flow to one of the plurality of fuel delivery outlet interfaces. The valve may be configured to at least decrease fuel flow to half of the plurality of fuel delivery outlet interfaces.
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公开(公告)号：US20190063322A1
公开(公告)日：2019-02-28
申请号：US15682887
申请日：2017-08-22
Applicant: United Technologies Corporation
Inventor： Albert K. Cheung
Abstract: A combustor wall for a turbine engine with an axial centerline comprising a combustor support shell comprising a plurality of impingement apertures; a combustor heat shield comprising a plurality of effusion apertures fluidly coupled with the plurality of impingement apertures; and at least one shaped pad formed in said combustor heat shield, said at least one shaped pad extending through a cutout in said combustor support shell.
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Patent Agency Ranking
16.发明申请GAS TURBINE ENGINE COMBUSTOR LINER PANEL WITH SYNERGISTIC COOLING FEATURES 审中-公开燃气涡轮发动机配备有协同冷却功能的衬板公开(公告)号：US20170003027A1
公开(公告)日：2017-01-05
申请号：US15106032
申请日：2015-01-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Stanislav Kostka , Frank J. Cunha , James B. Hoke , Timothy S. Snyder , Albert K. Cheung , Christos Adamopoulos
CPC classification number: F23R3/005 , F02C7/18 , F02K1/822 , F05D2260/20 , F05D2260/201 , F23R3/007 , F23R3/06 , F23R2900/00017 , F23R2900/03041 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
Abstract: A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a cone shaped pin.
Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括多个传热增强器。 多个传热增强器中的至少一个包括锥形销。
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公开(公告)号：US20160209039A1
公开(公告)日：2016-07-21
申请号：US14601389
申请日：2015-01-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Albert K. Cheung , James B. Hoke , Randal G. McKinney
CPC classification number: F23R3/286 , B01F3/04 , B01F15/0274 , F02C7/22 , F02M61/162 , F23D11/383 , F23R3/34
Abstract: A combustor is provided. The combustor may include an axial fuel injection system, and a radial fuel injection system aft of the axial fuel injection system. The axial fuel injection system includes a mixer having a bluff body at an exit port of the mixer, and a fuel injector disposed within the mixer. A fuel and air mixer is also provided and comprises an outer housing with an exit port and a bluff body. The bluff body extends across the exit port of the outer housing. A fuel injection system is also provided. The systems comprise a mixer having a bluff body at an exit port of the mixer and a fuel injector disposed within the mixer.
Abstract translation: 提供燃烧器。 燃烧器可以包括轴向燃料喷射系统和轴向燃料喷射系统后部的径向燃料喷射系统。 轴向燃料喷射系统包括在混合器的出口处具有非流线体的混合器和设置在混合器内的燃料喷射器。 还提供燃料和空气混合器，并且包括具有出口和非流线体的外壳。 非流线形体延伸穿过外壳的出口。 还提供燃料喷射系统。 该系统包括在混合器的出口处具有非流线体的混合器和设置在混合器内的燃料喷射器。
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公开(公告)号：US20160209036A1
公开(公告)日：2016-07-21
申请号：US14456685
申请日：2014-08-11
Applicant: United Technologies Corporation
Inventor： Albert K. Cheung
Abstract: An air swirler, a fuel and air admission assembly, and a staged combustor are disclosed. The staged combustor may be equipped with the fuel and air admission assemblies incorporating the air swirlers for use in gas turbine engines, such as for example gas turbine engines powering aircraft having supersonic cruise capability.
Abstract translation: 公开了一种空气旋流器，燃料和空气进入组件和分级燃烧器。 分级燃烧器可以配备有燃料和空气进入组件，其包括用于燃气涡轮发动机的空气旋流器，例如为具有超音速巡航能力的飞行器供电的燃气涡轮发动机。
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公开(公告)号：US10816209B2
公开(公告)日：2020-10-27
申请号：US15708892
申请日：2017-09-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Albert K. Cheung , James B. Hoke , Randal G. McKinney
Abstract: A fuel injection system may comprise a mixer and a fuel injector disposed within the mixer. The mixer may comprise an outer housing with an exit port and a bluff body extending across the exit port of the outer housing. A flared surface of the mixer may match a contour of the bluff body.
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公开(公告)号：US10670267B2
公开(公告)日：2020-06-02
申请号：US14826463
申请日：2015-08-14
Applicant: United Technologies Corporation
Inventor： Albert K. Cheung , Christos Adamopoulos
Abstract: A combustor liner for a gas turbine is provided. The combustor liner comprises a wall and a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole.
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