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公开(公告)号：US20240102655A1
公开(公告)日：2024-03-28
申请号：US18164491
申请日：2023-02-03
发明人： Justin M Locke , Dennis M Moura , Duane C McCormick , Scott A Liljenberg , Theodore R Strickland , William Proscia
CPC分类号： F23R3/28 , F23D11/38 , F23K5/06 , F23R3/06 , F23R3/12 , F23R3/14 , F23R3/346 , F23R3/50 , F23R2900/00014 , F23R2900/03042
摘要： A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.
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公开(公告)号：US11892167B2
公开(公告)日：2024-02-06
申请号：US17791232
申请日：2021-01-07
申请人： Turbogen Ltd.
发明人： Michael Levitsky
摘要： An atomizer provides a high-quality fuel-air mixture to a gas turbine engine, by combining air input from an engine compressor and fuel input from a single low-pressure fuel supply pump. The atomizer includes an atomizer body, a main vortex chamber, a secondary vortex chamber for improving quality of the fuel-air mixture, and a fuel sleeve providing fuel to the secondary vortex chamber. The main vortex chamber includes a main outlet nozzle in fluid communication with a combustion chamber inlet of the gas turbine engine. The secondary vortex chamber includes a secondary outlet nozzle in fluid communication with the main vortex chamber. The fuel sleeve has a blind channel with a longitudinal axis and a fuel tip. The same atomizer may be used for startup mode and for all operational modes of the gas turbine engine.
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公开(公告)号：US20240027069A1
公开(公告)日：2024-01-25
申请号：US17914694
申请日：2021-03-31
发明人： Shinichi Fukuba , Satoshi Takiguchi , Taiki Kinoshita , Kenta Taniguchi , Sosuke Nakamura , Yoshikazu Matsumura
摘要： A combustor for a gas turbine, includes: a first fuel nozzle group and a second fuel nozzle group each of which includes a fuel nozzle capable of supplying a fuel and has an independently controllable fuel supply system; a cylinder inside which a combustion region allowing a combustion gas produced by combustion of the fuel to flow is formed; and a first contraction portion extending partially along a circumferential direction so as to correspond to one of the first fuel nozzle group or the second fuel nozzle group and protruding radially inward from an inner peripheral surface of the cylinder.
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4.发明公开公开(公告)号：US20230288069A1
公开(公告)日：2023-09-14
申请号：US18320682
申请日：2023-05-19
摘要： A mixer for blending fuel and air in a combustor of a turbine engine. The mixer includes a central body having a central passageway and a central axis. The mixer includes a plurality of tubes positioned radially around the central axis and circumferentially around a periphery of the mixer. Each of the tubes of the mixer includes opposed openings and a tangential opening. Each of the tubes of the mixer includes a cylindrical interior mixing passage configured to receive air flow from the opposed openings and the tangential opening and a fuel flow. The opposed openings are configured to spread the fuel flow laterally and the tangential opening is configured to spread the fuel flow tangentially.
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公开(公告)号：US10072846B2
公开(公告)日：2018-09-11
申请号：US14791684
申请日：2015-07-06
发明人： Sarah Marie Monahan , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Matthieu Marc Masquelet
IPC分类号： F23R3/28 , F23R3/34 , F23C5/08 , F23R3/58 , F23R3/12 , F23R3/04 , F23C5/00 , F23R3/42 , F23C5/32 , F23R3/02 , F23R3/10 , F23C5/24 , F23R3/06
CPC分类号： F23R3/286 , F05D2240/35 , F23C5/00 , F23C5/08 , F23C5/10 , F23C5/24 , F23C5/32 , F23R3/02 , F23R3/04 , F23R3/045 , F23R3/06 , F23R3/10 , F23R3/12 , F23R3/34 , F23R3/346 , F23R3/42 , F23R3/58 , F23R2900/00015 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
摘要： A gas turbine engine and combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two axially spaced apart annular trapped vortex cavities are located on the combustor liner and staged axially and radially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities. A plurality of injectors are configured tangentially relative to circular radially outer wall extending between an aft wall and a forward wall of each cavity to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid.
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公开(公告)号：US20180202655A1
公开(公告)日：2018-07-19
申请号：US15923351
申请日：2018-03-16
申请人： Delavan Inc.
CPC分类号： F23D14/58 , B05B7/10 , F23D11/107 , F23R3/12 , F23R3/28 , Y10T29/49996
摘要： A flow directing apparatus for directing fluid flow includes a flow body defining a bore therethrough configured and adapted to direct fluid flowing therethrough. The bore includes an outlet and an opposed inlet with an enlargement, formed as a countersink and/or a chamfer using a suitable boring device. The enlargement is configured and adapted to reduce sensitivity to entrance-edge conditions for the bore.
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公开(公告)号：US20170292705A1
公开(公告)日：2017-10-12
申请号：US15512753
申请日：2015-10-15
发明人： Yusuke TANAKA , Keijiro SAITO , Shinji AKAMATSU
CPC分类号： F23R3/12 , F02C3/04 , F05D2220/32 , F05D2240/35 , F23R3/16 , F23R3/286
摘要： A combustor according to the present invention is provided with: a pilot burner (15) disposed along an axis (P); a plurality of premixing burners (16), each of which has a premixing swirler cylinder (19) and a premixing nozzle (20) disposed inside the premixing swirler cylinder (19) and that are disposed about the axis (P) in the circumferential direction so as to surround the periphery of the pilot burner (15); a substrate (23) through which the pilot burner (15) and the premixing swirler cylinders (19) are individually inserted so as to be supported therein; and stagnation eliminating blocks (27) that are provided so as to fill spaces between the premixing swirler cylinders (19) on a surface of the substrate (23) on the downstream side, wherein air film supplying ports (38) that form air films A on surfaces of the stagnation eliminating blocks (27) are formed in the stagnation eliminating blocks (27).
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8.发明申请公开(公告)号：US20170089584A1
公开(公告)日：2017-03-30
申请号：US15278773
申请日：2016-09-28
IPC分类号： F23R3/28
摘要： A vortex generator, such as for a fuel injection system of a gas turbine, includes a base area and a vortex generator body extending in a tapering fashion from the base area with a predetermined height. A rapid fuel-air mixing at allowable pressure drops for higher firing temperature gas turbines and within short burner-mixing length or time scales is achieved by the vortex generator body forming at least two partial vortex generators, whereby each of the at least two partial vortex generators has its own trailing edge.
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公开(公告)号：US09518743B2
公开(公告)日：2016-12-13
申请号：US14074292
申请日：2013-11-07
发明人： Adnan Eroglu
IPC分类号： F23R3/34 , F23R3/36 , F23C6/04 , F23D11/10 , F23D11/12 , F23D11/40 , F23D14/58 , F23D14/64 , F23D17/00 , F23R3/12 , F23R3/28
CPC分类号： F23R3/34 , F23C6/047 , F23C2900/07002 , F23C2900/07021 , F23D11/105 , F23D11/12 , F23D11/402 , F23D14/58 , F23D14/64 , F23D17/002 , F23D2900/00015 , F23D2900/11101 , F23R3/12 , F23R3/286 , F23R3/343 , F23R3/346 , F23R3/36 , F23R2900/03341
摘要： Methods are directed to operating a burner of a gas turbine. The burner includes a swirl generator and, downstream of it, a mixing tube. The swirl generator is defined by at least two walls facing one another to define a conical swirl chamber and includes nozzles arranged to inject fuel and apertures arranged to feed an oxidizer into the swirl chamber. The burner includes a lance which extends along a longitudinal axis of the swirl generator and side nozzles for ejecting a fuel within the burner. The side nozzles have their axes inclined with respect to the axis of the lance and can be positioned along the axis of the burner. During operation, an oil fuel or gaseous fuel is injected into to the burner through the lance tip and the lance side nozzles at various percentages depending on an operating mode of the gas turbine.
摘要翻译： 方法涉及操作燃气轮机的燃烧器。 燃烧器包括涡流发生器，并在其下游设有混合管。 漩涡发生器由彼此面对的至少两个壁限定，以限定圆锥形的旋转室，并且包括喷射喷射燃料的喷嘴和布置成将氧化剂进料到涡流室中的孔。 燃烧器包括沿着涡流发生器的纵向轴线延伸的喷枪和用于在燃烧器内喷射燃料的侧喷嘴。 侧喷嘴具有相对于喷枪的轴线倾斜的轴线，并且可以沿着燃烧器的轴线定位。 在操作期间，油燃料或气体燃料根据燃气轮机的操作模式以不同的百分比通过喷枪尖和喷枪侧喷嘴喷射到燃烧器中。
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公开(公告)号：US20160356501A1
公开(公告)日：2016-12-08
申请号：US15239993
申请日：2016-08-18
CPC分类号： F23R3/286 , F02C7/264 , F02C7/266 , F23C99/001 , F23C2900/99005 , F23D2207/00 , F23D2209/20 , F23R3/12 , F23R3/14 , F23R2900/00008 , F23R2900/00009
摘要： An apparatus and method for assisting with the combustion of fuel are described. The apparatus includes a swirler assembly and a fuel nozzle. Fuel is directed into a fuel nozzle mixing chamber and combines with air therein to form a fuel-air mixture. At least one plasma generator, at least partially within the fuel nozzle, generates an at least one of an at least partially ionized air-fuel mixture and an at least partially dissociated air-fuel mixture (“at least partially I/D air-fuel mixture”) via a plasma generator discharge. A combustion chamber inlet admits the at least partially I/D air-fuel mixture from the plasma generator into a combustion chamber internal volume. Combustion air flows through the swirler body and into the combustion chamber internal volume. Combustion of the at least partially I/D air-fuel mixture with the combustion air occurs at least partially within the combustion chamber internal volume to responsively produce products.
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