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公开(公告)号：US20180356095A1
公开(公告)日：2018-12-13
申请号：US15450308
申请日：2017-03-06
摘要： A combustion section for gas turbine engine includes an inner liner, an outer liner, and a dome attached to the inner liner and to the outer liner. A heat shield is attached to the dome, with the dome, the heat shield, or both define an opening. The combustion section also includes a fuel nozzle extending at least partially into the opening, the fuel nozzle defining a fuel nozzle axis and a radial direction relative to the fuel nozzle axis. The fuel nozzle defines an aft end, the aft end of the fuel nozzle positioned forward of the aft surface of the heat shield along the fuel nozzle axis such that the aft end of the fuel nozzle defines a minimum separation from the aft surface of the heat shield along the fuel nozzle axis of at least about 0.15 inches.
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公开(公告)号：US20180306437A1
公开(公告)日：2018-10-25
申请号：US15495043
申请日：2017-04-24
发明人： Peter E. Gunderson
CPC分类号： F23D11/383 , F05D2230/64 , F05D2240/35 , F05D2260/30 , F23D11/105 , F23D11/107 , F23D14/24 , F23D2900/14021 , F23D2900/14241 , F23R3/002 , F23R3/06 , F23R3/12 , F23R3/14 , F23R3/26 , F23R3/28 , F23R3/283 , F23R3/286 , F23R3/60 , F23R2900/00012 , F23R2900/00017 , Y02T50/675
摘要： A fuel swirler with anti-rotation features is provided. A swirler assembly may comprise a swirler, a guide plate, and a retaining ring. The swirler, the guide plate, and/or the retaining ring may comprise recessions configured to receive a retaining element. The retaining element may be configured to interface with the recessions to create an interference in the swirler assembly. The interference may at least partially resist rotation of the guide plate with respect to the swirler.
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公开(公告)号：US20180266691A1
公开(公告)日：2018-09-20
申请号：US15592777
申请日：2017-05-11
CPC分类号： F23R3/283 , F02C3/06 , F02C7/222 , F05D2220/32 , F05D2240/35 , F05D2260/20 , F05D2260/232 , Y02T50/671 , Y02T50/676
摘要： Fuel-air heat exchange system and methods thereof for use in a gas turbine engine. The fuel-air heat exchanger allows heat transfer between a flow of cooling air used to cool components of the engine and a flow of fuel used to drive the engine.
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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
发明人： Wookyung Kim , Zhongtao Dai , Kristin Kopp-Vaughan
摘要： 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：US20180231253A1
公开(公告)日：2018-08-16
申请号：US15434386
申请日：2017-02-16
IPC分类号： F23R3/28
CPC分类号： F23R3/283 , F23D11/38 , F23R2900/00018
摘要： An object includes an annular outer body having an interior surface; and an annular inner body disposed inside the annular outer body, the annular inner body having an exterior surface defining an annular passage with the interior surface of the annular outer body. A plurality of suspension elements connects the interior surface of the annular outer body to the exterior surface of the annular inner body, each suspension element configured to substantially rigidly locate a position of the annular outer body relative to the annular inner body in axial and lateral directions while permitting controlled deflection in a radial direction. Each suspension element has an at least partially tear-shaped cross-section.
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6.发明申请公开(公告)号：US20180230910A1
公开(公告)日：2018-08-16
申请号：US15388133
申请日：2016-12-22
CPC分类号： F02C7/222 , B22D17/24 , B22D25/02 , B22D29/002 , B33Y80/00 , F05D2230/21 , F23R3/283 , F23R2900/00017 , F23R2900/00018
摘要： A fuel manifold (10) configured to form a base support structure (12) to support a plurality of fuel nozzles (14) in a combustor of a gas turbine engine is provided. The fuel manifold includes stage fuel galleries (16, 18), and fuel feed bosses (20, 22) may be configured to connect to respective tubes arranged to deliver gas fuel to the stage fuel galleries (16. 18). Fuel feed bosses (20, 22) are integrally formed with base support structure (12) and this allows the body of fuel manifold (10) to be free of weld joints for affixing the fuel feed boss to the base support structure.
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公开(公告)号：US20180187982A1
公开(公告)日：2018-07-05
申请号：US15905120
申请日：2018-02-26
发明人： Joe Ott , John J. Rup, JR. , Stanley J. Funk , Dennis M. Moura , Lexia Kironn , Roger O. Coffey
CPC分类号： F28F1/00 , F16L9/18 , F16L59/14 , F23D2211/00 , F23D2900/00016 , F23R3/283
摘要： A tube assembly that may be for a fuel nozzle of a fuel system of a gas turbine engine may have a first tube defining a first flowpath along a centerline, a second tube generally spaced radially outward from the first tube with a first void located between and defined by the first and second tubes, and a support structure located in the first void and extending between the first and second tubes. The support structure is constructed and arranged to minimize or eliminate thermal conduction between the tubes. The entire assembly may be additive manufactured as one unitary piece. One example of a method of operation may include designed-for breakage of the structural support due to thermal stresses thereby further minimizing thermal conduction between tubes.
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公开(公告)号：US10001280B2
公开(公告)日：2018-06-19
申请号：US15452345
申请日：2017-03-07
申请人： Delavan Inc.
发明人： Mark Caples
IPC分类号： F23R3/28
CPC分类号： F23R3/283 , F23R2900/00005 , Y10T29/49865 , Y10T29/49945
摘要： One embodiment includes a fuel injector for a gas turbine engine. The fuel injector has an inlet fitting for receiving fuel. The fuel injector also has an outlet fitting for delivering fuel through a nozzle to a combustor of the gas turbine engine. An injector support extends between the inlet fitting and the outlet fitting and has an internal bore therethrough. A fuel tube extends from the inlet fitting through the internal bore of the injector support to the outlet fitting. The injector support has a greater coefficient of thermal expansion than the fuel tube. At room temperature the fuel tube is under compressive stress such that the fuel tube is buckled. As a result of differential thermal expansion of the fuel tube and the injector support during engine operation the fuel tube is relieved of compressive stress.
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公开(公告)号：US20180156462A1
公开(公告)日：2018-06-07
申请号：US15371308
申请日：2016-12-07
发明人： Lucas John Stoia , Richard Martin DiCintio , Timothy James Purcell , Srikanth Chandrudu Kottilingam
IPC分类号： F23R3/28
摘要： A fuel nozzle assembly includes a forward plate and an aft plate which is axially spaced from the forward plate. The aft plate includes a first side surface and a second side surface. A cooling air plenum is defined within the bundled tube fuel nozzle assembly and is at least partially defined by the aft plate. A plurality of tubes extends through the forward plate, the cooling air plenum and the aft plate. A micro-cooling channel is disposed along the second side surface of the aft plate and is in fluid communication with the cooling air plenum and is in fluid communication with an exhaust aperture. A cover plate is connected to the aft plate and covers the micro-cooling channel.
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公开(公告)号：US09982891B2
公开(公告)日：2018-05-29
申请号：US14563532
申请日：2014-12-08
发明人： Axel Widenhorn , Roland Stoll , Dominik Lebküchner , Thilo Kissel , Jan Zanger , Timo Zornek , Thomas Monz
CPC分类号： F23R3/286 , F23R3/283 , F23R3/343 , F23R3/54 , F23R2900/03282
摘要： Burners having a fuel plenum in a base are disclosed. One disclosed example apparatus includes a base of a burner, the base comprising a fuel plenum and coupled to fuel nozzles, where at least one of the fuel nozzles is in fluid communication with the fuel plenum. The disclosed example apparatus also includes a burner head of the burner comprising nozzle passages in fluid communication with an airflow path, where the burner head defines a pilot combustion space that opens towards a flame tube of the burner, and is in fluid communication with the airflow path, and where each nozzle passage is to receive a fuel nozzle to provide fuel to entrain with air from the airflow path.
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