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公开(公告)号：US10001281B2
公开(公告)日：2018-06-19
申请号：US14689765
申请日：2015-04-17
摘要： A fuel nozzle apparatus for a gas turbine engine includes: an annular outer body extending parallel to a centerline axis and having an exterior surface, and having a ring of forward openings passing through the exterior surface, and a ring of aft openings passing through the exterior surface, the aft openings positioned axially aft of the forward openings; an annular main injection ring disposed inside the outer body and including: a forward main fuel gallery extending in a circumferential direction; an aft main fuel gallery extending in a circumferential direction; a ring of forward main fuel orifices communicating with the forward main fuel gallery and each aligned with one of the forward openings; a ring of aft main fuel orifices, communicating with the aft main fuel gallery and each aligned with one of the aft openings; and a pilot fuel injector disposed along the centerline axis.
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32.发明授权公开(公告)号：US09995220B2
公开(公告)日：2018-06-12
申请号：US14135655
申请日：2013-12-20
CPC分类号： F02C7/222 , F23D17/002 , F23R3/36
摘要： The described gas turbine engine fuel manifold includes one or more fuel conduits defined within a ring-shaped manifold body, each of the fuel conduits being fluidly connected to a respective separate group of fuel injection nozzles. Each of the fuel conduits, which extend from a conduit inlet to a conduit end, include a first portion extending continuously between the conduit inlet and an inflexion of the conduit, and a second portion downstream of the first portion and connected thereto in serial flow communication, the second portion extending between the inflexion and the conduit end. The inflexion being a single exit of the first portion such that fuel flows uninterrupted between the conduit inlet and the inflexion. The respective separate group of fuel injection nozzles of the fuel conduit fluidly communicating exclusively with the second portion of the fuel conduit.
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公开(公告)号：US09989256B2
公开(公告)日：2018-06-05
申请号：US14750347
申请日：2015-06-25
申请人： SNECMA
CPC分类号： F23R3/14 , F02C7/22 , F05D2220/323 , F05D2220/36 , F05D2240/35 , F23C7/004 , F23R3/286 , F23R3/343 , F23R3/36 , Y02T50/675
摘要： An injection system for a turbine engine combustion chamber is provided. The injection system includes a first annular deflector surrounded by the bowl of the injection system and extending in the downstream direction from the downstream transverse surface that delimits the downstream side of the swirler. The first deflector has a free downstream end offset in the upstream direction from a downstream end of the bowl, so as to guide an air film output from the first orifices formed through the bowl. The internal radius of the cross section of the first annular deflector increases from the downstream transverse surface as far as the downstream end of the first annular deflector.
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34.发明申请公开(公告)号：US20170363291A1
公开(公告)日：2017-12-21
申请号：US15540405
申请日：2015-01-29
申请人： Siemens Energy, Inc.
摘要： A fuel injector for injecting alternate fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) may be fluidly coupled to a radial passage (22) in a plurality of vanes (20) that branches into passages (24) (e.g., axial passages) to inject a first fuel without jet in cross-flow injection. This may be effective to reduce flashback in fuels having a relatively high flame speed. A mixer (30) with lobes (32) for injection of a second fuel may be arranged at the downstream end of a fuel delivery tube (12). A fuel-routing structure (38) may be configured to route the second fuel within a respective lobe so that fuel injection of the second fuel takes place radially outwardly relative to a central region of the mixer. This may be conducive to an improved (e.g., a relatively more uniform) mixing of air and fuel.
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公开(公告)号：US20170356656A1
公开(公告)日：2017-12-14
申请号：US15539314
申请日：2015-12-25
发明人： Masahiro OGATA , Takeo ODA , Yasuhiro KINOSHITA , Kohshi HIRANO , Takahiro UTO
CPC分类号： F23R3/286 , F02C7/22 , F02C9/40 , F23C1/00 , F23C99/00 , F23D17/00 , F23R3/28 , F23R3/30 , F23R3/34 , F23R3/346 , F23R3/36 , F23R2900/00002
摘要： The present invention provides a burner, a combustor equipped with the burner, and a gas turbine, with which it is possible to premix a first hydrocarbon-based fuel (for example, natural gas), a second fuel (for example, hydrogen gas), and combustion air, and to spray into the combustion chamber of the combustor a thin and uniform concentration distribution of the premixed air, and with which it is possible to suppress the amount of NOx discharged. On the upstream side of the premix flow path, hydrogen gas is sprayed from second fuel spray nozzles, which project into the premix flow path, into the flow of the combustion air flowing toward the center from the outer edge of an outer cylinder, whereby a primary air-fuel mixture having a uniform concentration distribution is generated without affecting a low-speed region of the combustion air. Natural gas is then sprayed from first fuel spray nozzles into the primary air-fuel mixture, whereby the natural gas, which has a high specific gravity, and the primary air-fuel mixture are adequately mixed in a stirring fashion, and a secondary air-fuel mixture (premixed air) is generated that is lean and has a more uniform concentration distribution than the first air-fuel mixture. By combusting this type of premixed air in the combustion chamber, NOx in the combustion exhaust gas can be suppressed.
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公开(公告)号：US20170299190A1
公开(公告)日：2017-10-19
申请号：US15130037
申请日：2016-04-15
发明人： Rajeshriben Patel , James Scott Piper , Raymond Alvarez , Rasoul Paydar , Ram Srinivasan , Edouard Bahous
CPC分类号： F23R3/36 , F02C7/22 , F05D2220/32 , F05D2220/75 , F05D2240/35 , F05D2240/60 , F23C2900/07001 , F23R3/14 , F23R3/286 , F23R2900/00002 , Y02E50/12 , Y02T50/675
摘要： A fuel injector for a combustion engine includes an injector head including a nozzle, a premixer, and a distributor structured to distribute a plurality of different fuels to different sets of fueling orifices in the premixer. A pilot assembly of the fuel injector is coupled to the premixer and includes a first fueling passage for a first fuel and a second fueling passage for a second fuel. Multiple sets of fueling orifices are positioned within the fuel injector, the fueling orifice sets being selectively connectable to a plurality of different fuel supplies, and both located and sized so as to accommodate a wide range of flow rates to enable a combustion engine coupled with the fuel injector to operate on fuels having a range of Wobbe numbers and compositions.
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公开(公告)号：US09771869B2
公开(公告)日：2017-09-26
申请号：US14154692
申请日：2014-01-14
发明人： Suhui Li , Joel Meier Haynes , Ping Yu , Wei Chen , David Leach , John Joseph Lipinski , Manuel Moises Cardenas, Jr. , Wenjie Wu , Qingguo Zhang
摘要： A fuel nozzle system for enabling a gas turbine to start and operate on low-Btu fuel includes a primary tip having primary fuel orifices and a primary fuel passage in fluid communication with the primary fuel orifices, and a fuel circuit capable of controlling flow rates of a first and second low-Btu fuel gases flowing into the fuel nozzle. The system is capable of operating at an ignition status, in which at least the first low-Btu fuel gas is fed to the primary fuel orifices and ignited to start the gas turbine, and a baseload status, in which at least the second low-Btu fuel gas is fired at baseload. The low-Btu fuel gas ignited at the ignition status has a content of the first low-Btu fuel gas higher than that of the low-Btu fuel gas fired at the baseload status. Methods for using the system are also provided.
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公开(公告)号：US09695750B2
公开(公告)日：2017-07-04
申请号：US14443468
申请日：2013-11-26
IPC分类号： F02C9/40 , F02C9/28 , F02C7/22 , F02C3/22 , B64D37/30 , F02C7/14 , F02C7/224 , F23R3/36 , F23K5/00
CPC分类号： F02C7/22 , F02C3/22 , F02C7/14 , F02C7/224 , F02C9/40 , F23K5/005 , F23R3/36 , Y02T50/672 , Y02T50/675
摘要： A turbine engine assembly having a turbine core with a compressor section, a combustion section, a turbine section, and a nozzle section and a liquid natural gas (LNG) fuel system having a LNG reservoir, a vaporizer heat exchanger, a first liquid supply line operably coupling the LNG reservoir to an input of the vaporizer heat exchanger, a gas supply line operably coupling an output of the vaporizer heat exchanger to the combustion section, a second liquid supply line operably coupling the LNG reservoir to the gas supply line and a thermostatic expansion valve (TEV) and a dual fuel aircraft control system.
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公开(公告)号：US09650961B2
公开(公告)日：2017-05-16
申请号：US14081609
申请日：2013-11-15
CPC分类号： F02C7/222 , F02C7/28 , F23D14/02 , F23D14/78 , F23D17/002 , F23D2204/10 , F23D2900/00003 , F23R3/02 , F23R3/28 , F23R3/283 , F23R3/286 , F23R3/36 , F23R2900/00018
摘要： A gas turbine combustor includes: multiple gaseous fuel nozzles to inject gaseous fuel; a manifold to distribute gaseous fuel to the multiple gaseous fuel nozzles; a burner flange to secure a burner to an end cover; and a burner body to connect the manifold and the burner flange. Gaseous fuel passages are provided in the end cover, the burner flange, and the burner body. The gaseous fuel passage communicates with the manifold. A second manifold is provided in the burner flange. The gaseous fuel passage is provided in the burner body to make the second manifold communicate with the first mentioned manifold.
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公开(公告)号：US09618209B2
公开(公告)日：2017-04-11
申请号：US14199419
申请日：2014-03-06
发明人： Ramarao Venkat Bandaru , James Scott Piper , Scott Michael Lindner , Anthony Paul Batakis , Peter Joseph Giella
CPC分类号： F23R3/28 , F23R3/36 , F23R2900/00004
摘要： A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a gas outer tube, a gas inner tube, a liquid tube, and a heat shield. The gas outer tube and the gas inner tube form a gas fuel annulus. The gas inner tube and the liquid tube form a liquid fuel annulus. The liquid tube forms an air cavity. The heat shield extends within the liquid tube forming an insulating gap between the heat shield and the liquid tube.
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