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公开(公告)号：US11255545B1
公开(公告)日：2022-02-22
申请号：US17079847
申请日：2020-10-26
摘要： Integrated combustion nozzles and turbomachines are provided. An integrated combustion nozzle includes a unified head end coupled to a combustion liner. The unified head end includes a first fuel nozzle and a second fuel nozzle disposed at a forward end portion of the combustion liner. A fuel plenum is defined between the first fuel nozzle and the second fuel nozzle. A first liner portion extends from the first fuel nozzle and into an opening of a first wall of the combustion liner such that the first liner portion forms a continuous surface with the first wall. The unified head end further includes a second liner portion that extends from the second fuel nozzle and into an opening of a second wall of the combustion liner such that the second liner portion forms a continuous surface with the second wall.
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公开(公告)号：US11248794B2
公开(公告)日：2022-02-15
申请号：US16731306
申请日：2019-12-31
摘要： A fluid mixing apparatus includes mixing conduits that extend through a fluid plenum. The fluid plenum, which surrounds a first wall defining a main passage fluidly coupled to a low-pressure fluid source, is surrounded itself by a second wall defining a high-pressure plenum fluidly coupled to a high-pressure fluid source. An insulated tube disposed at the inlet of the first wall delivers a third fluid. The mixing conduits fluidly couple the high-pressure plenum to the main passage, where the high-pressure fluid is mixed with low-pressure fluid and the third fluid. Optionally, the fluid plenum may house a fourth fluid that is injected through injection holes in the mixing conduits. The fluid mixing apparatus may be used to mix one or more fuels with high- and low-pressure air in a gas turbine combustor. Alternately, the fluid mixing apparatus may mix a fluid with high- and low-pressure water streams.
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公开(公告)号：US11236908B2
公开(公告)日：2022-02-01
申请号：US16169645
申请日：2018-10-24
摘要： A combustion system includes an annular tube disposed between an inner wall and an outer wall, the annular tube extending from an inlet end to an outlet end; at least one fluid inlet disposed in the annular tube proximate the inlet end, the fluid inlet providing a conduit through which fluid flows into the annular tube; at least one outlet disposed in the annular tube proximate the outlet end; at least one primary fuel injector, the primary fuel injector dispersing fuel into a fluid stream entering the annular tube via the fluid inlet; and at least one secondary fuel injector, the secondary fuel injector disposed in the annular tube.
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公开(公告)号：US11204168B2
公开(公告)日：2021-12-21
申请号：US16011865
申请日：2018-06-19
申请人： ROLLS-ROYCE PLC
发明人： Martin K. Yates , Daniel J. Bickley
IPC分类号： F23R3/34 , F23R3/28 , F23K5/14 , F23K5/06 , F02C9/34 , F02C7/228 , F02C7/232 , F02C9/26 , F02C7/14 , F02C7/22 , F02C7/236
摘要： A combustion staging system has: a splitter; pilot and mains fuel manifolds; mains flow control valves; and fuel servo line. Each mains flow control valve has a chamber containing a piston, the chamber to a piston mains side fed by the mains fuel manifold, and the chamber to a piston servo side fed by the servo line. The piston has an open pilot-and-mains position allowing flow from the chamber mains side to the respective injector mains discharge orifice. The piston prevents flow from the chamber mains side. The piston is movable under a pressure change in the servo line relative to the mains fuel manifold. The system has a servo pump and a hydraulic motor driving it. The servo pump changes fuel pressure. Motive power for the hydraulic motor is fuel diverted from a fuel pump high pressure output, the motor returning the diverted fuel to a low pressure input.
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公开(公告)号：US11199818B2
公开(公告)日：2021-12-14
申请号：US16691057
申请日：2019-11-21
发明人： Christopher Chandler
IPC分类号： G05B13/00 , F23N1/00 , F23N5/00 , F23N5/24 , F23R3/34 , F23R3/36 , F02C9/40 , F02C9/28 , G05B19/05
摘要： Provided herein is a method for automated control of the gas turbine fuel composition through automated modification of the ratio of fuel gas from multiple sources. The method includes providing first and second fuel sources. The method further includes sensing the operational parameters of a turbine and determining whether the operational parameters are within preset operational limits. The method also adjusting the ration of the first fuel source to the second fuel source, based on whether the operational parameters are within the preset operational limits.
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公开(公告)号：US11181273B2
公开(公告)日：2021-11-23
申请号：US16317715
申请日：2016-09-27
IPC分类号： F23R3/34
摘要： A turbine engine has two combustion zones so as to operate in conditions where water scarcity is an issue. The secondary combustion zone is located downstream of the primary combustion zone. Fuel can be fed into an air scoop having air from a shell surrounding the primary and secondary combustion zone. The feeding of the fuel through the air scoop allows atomization of the fuel. The mixture can then enter the secondary combustion zone and mix with the products from the first combustion zone.
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公开(公告)号：US20210348764A1
公开(公告)日：2021-11-11
申请号：US17383966
申请日：2021-07-23
发明人： Eduardo Hawie , Nigel Davenport
摘要： A combustor for a gas turbine engine comprises an inner annular liner wall and an outer annular liner wall cooperating to form a combustion chamber of the combustor. A first dome wall has a circumferential array of first fuel injection bores. A second dome has a circumferential array of second fuel injection bores. An intermediate wall extends between the first dome wall and the second dome wall. A first combustion stage is defined by the inner liner wall forward end, the first dome wall and the intermediate wall. A second combustion stage is defined at least by the outer liner wall forward end, the second dome wall and the intermediate wall, the first combustion stage communicating with the first fuel injection bores, the second combustion stage communicating with the second fuel injection bores.
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公开(公告)号：US20210348763A1
公开(公告)日：2021-11-11
申请号：US16998247
申请日：2020-08-20
发明人： U Jin ROH , Mu Hwan CHON
摘要： A combustor and a gas turbine capable of uniformly supplying air into a burner are provided. The combustor may include a burner including a tubular nozzle casing, a head plate coupled to an end of the nozzle casing, and a plurality of nozzles to inject fuel and air, and a duct assembly coupled to the burner, a mixture of the fuel and the air being burned in the duct assembly to produce combustion gas. Each of the nozzles may include outer nozzles and an inner nozzle installed inside the outer nozzles, each of the outer nozzles may include a nozzle tube configured to provide a channel through which air and fuel flow and a nozzle shroud configured to surround the nozzle tube, and a flow distribution member may be installed between the head plate and the nozzle shroud to distribute a flow rate of air introduced into the outer nozzle.
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公开(公告)号：US11168887B2
公开(公告)日：2021-11-09
申请号：US17003430
申请日：2020-08-26
申请人： ROLLS-ROYCE plc
发明人： Tomasz Stankowski
摘要： Fuel spray nozzle for generating a spray of atomised liquid fuel in a combustor of a gas turbine engine. The nozzle includes a flow circuit that has in flow series: a gallery that receives fuel flow, plural circumferentially-spaced restrictor passages arranged in a row around the nozzle, plural conditioning passages configured to impart a circumferential component to their respective portions of the fuel flow, and an annular spin chamber which forms a swirling fuel flow which is discharged at an exit port. The restrictor passages form flow restrictions which in use produce a pressure differential between the gallery and the spin chamber to evenly circumferentially distribute the fuel flow between the restrictor passages. The conditioning passages have increased flow cross-sectional areas relative to the flow cross-sectional areas of the restrictor passages, such that the restrictor passages produce substantially all of the pressure differential between the gallery and the spin chamber.
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公开(公告)号：US11149941B2
公开(公告)日：2021-10-19
申请号：US16220817
申请日：2018-12-14
申请人： Delavan Inc.
摘要： An injection system includes a radial swirler defining an axis and including a plurality of radial swirl vanes configured to direct a radially inward flow of compressor discharge air entering swirler inlets between the radial swirl vanes in a swirling direction around the axis. The radial swirler includes an outlet oriented in an axial direction to direct swirling compressor discharge air in an axial direction. An injector ring is included radially outward from of the swirler inlets. The fuel injector ring is aligned with the axis and includes a plurality of injection orifices directed towards the swirler inlets for injecting fuel into the radial swirler.
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