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公开(公告)号：US20150184857A1
公开(公告)日：2015-07-02
申请号：US14644227
申请日：2015-03-11
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Timothy S. Snyder
IPC: F23R3/26
CPC classification number: F23R3/002 , F02C7/12 , F23R3/04 , F23R3/06 , F23R3/12 , F23R3/14 , F23R2900/00018 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
Abstract: A combustor component of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat shield panel. The heat shield panel defines a bend and a microcircuit flow path within a thickness of the heat shield panel. The microcircuit flow path includes an inlet and an outlet radially outward of the inlet. The microcircuit flow path at the bend is positioned radially between the inlet and the outlet, and the microcircuit flow path follows the bend. A method of cooling a combustor of a gas turbine engine is also disclosed.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机的燃烧器部件尤其包括隔热板。 隔热板限定了在隔热板的厚度内的弯曲和微电路流动路径。 微电路流路包括入口径向向外的入口和出口。 弯曲处的微电路流动路径径向位于入口和出口之间，并且微电路流动路径跟随弯曲。 还公开了一种冷却燃气涡轮发动机的燃烧器的方法。
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公开(公告)号：US20140338351A1
公开(公告)日：2014-11-20
申请号：US13725137
申请日：2012-12-21
Applicant: United Technologies Corporation
Inventor： Timothy S. Snyder , Randal G. McKinney , James B. Hoke
CPC classification number: F23R3/002 , F02C7/2365 , F23R3/06 , F23R3/12 , F23R3/26 , F23R3/286 , Y02T50/675
Abstract: A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.
Abstract translation: 用于定制燃气涡轮发动机的燃烧器流的方法包括控制进入旋流器的气流大致均匀并控制进入淬火区域的气流以提供期望的模式因子。
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公开(公告)号：US11725818B2
公开(公告)日：2023-08-15
申请号：US16705644
申请日：2019-12-06
Applicant: United Technologies Corporation
Inventor： Timothy S. Snyder
Abstract: A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. A hood chamber is separated from the combustion chamber by a bulkhead extending between the inner shell and the outer shell. The bulkhead includes at least one opening extending between the hood chamber and the combustion chamber. A fuel injector extends through the at least one opening. The fuel injector includes a primary fuel passage including a primary fuel outlet located within the combustion chamber. The fuel injector further includes a secondary fuel passage including a plurality of secondary fuel outlets located within the hood chamber.
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公开(公告)号：US20210207541A1
公开(公告)日：2021-07-08
申请号：US16736970
申请日：2020-01-08
Applicant: United Technologies Corporation
Inventor： Timothy S. Snyder
Abstract: A fuel delivery system for a combustor of a gas turbine engine including a primary fuel tank configured to store a primary fuel, a secondary fuel tank configured to store a secondary fuel, a swirler configured to produce a main flame within a combustion chamber of the combustor, and a fuel nozzle configured to produce a pilot flame within the combustion chamber of the combustor. The fuel nozzle includes a nozzle outlet that is located proximate to an end of the swirler or at the end of the swirler, the end of the swirler being located at an inlet of the combustor. The fuel delivery system also includes a primary fuel line fluidly connecting the primary fuel tank to the fuel nozzle and a secondary fuel line fluidly connecting the secondary fuel tank to the swirler.
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公开(公告)号：US10730635B1
公开(公告)日：2020-08-04
申请号：US16574424
申请日：2019-09-18
Applicant: United Technologies Corporation
Inventor： Timothy S. Snyder , Steven H. Zysman
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an engine wing. This disclosure also relates to an airplane including an engine wing.
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Patent Agency Ranking
公开(公告)号：US20200025090A1
公开(公告)日：2020-01-23
申请号：US16270226
申请日：2019-02-07
Applicant: United Technologies Corporation
Inventor： James B. Hoke , Timothy S. Snyder , David Kwoka , Robert M. Sonntag
Abstract: A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.
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公开(公告)号：US10240533B2
公开(公告)日：2019-03-26
申请号：US13832507
申请日：2013-03-15
Applicant: United Technologies Corporation
Inventor： James B. Hoke , Timothy S. Snyder , David Kwoka , Robert M. Sonntag
Abstract: A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.
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公开(公告)号：US10094563B2
公开(公告)日：2018-10-09
申请号：US14644227
申请日：2015-03-11
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Timothy S. Snyder
Abstract: A combustor component of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat shield panel. The heat shield panel defines a bend and a microcircuit flow path within a thickness of the heat shield panel. The microcircuit flow path includes an inlet and an outlet radially outward of the inlet. The microcircuit flow path at the bend is positioned radially between the inlet and the outlet, and the microcircuit flow path follows the bend. A method of cooling a combustor of a gas turbine engine is also disclosed.
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公开(公告)号：US09816394B2
公开(公告)日：2017-11-14
申请号：US14221494
申请日：2014-03-21
Applicant: United Technologies Corporation
Inventor： Frank J. Cunha , Timothy S. Snyder
CPC classification number: F01D25/14 , F01D5/187 , F01D9/041 , F05D2220/32 , F05D2220/328 , F05D2220/90 , F05D2240/12 , F05D2240/128 , F05D2260/202 , Y02T50/672 , Y02T50/676
Abstract: A panel for use in a gas turbine engine exhaust case is disclosed. The panel has an airfoil section and a flow diverting structure adjacent a leading edge, wherein the flow diverting structure directs fluid flow into an area of the airfoil that lacks sufficient internal pressure for cooling fluid flow.
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50.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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