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公开(公告)号：US20140083105A1
公开(公告)日：2014-03-27
申请号：US14091619
申请日：2013-11-27
IPC分类号： F23R3/28
摘要： An annular type gas turbine combustor having a plurality of fuel nozzle assemblies (10) on a circumference includes a pilot nozzle unit (12) for spraying a fuel for diffusive combustion from a pilot outer peripheral nozzle (34) into a combustion chamber (8), a main nozzle unit (14) provided so as to surround the pilot nozzle unit (12) for spraying a fuel for premix combustion, and a flow guide (27) disposed on a downstream side of each of the fuel nozzle assemblies (10) and having a sectional area of a passage for air and air-fuel mixture from each of the fuel nozzle assemblies (10), which gradually increase in a downstream direction.
摘要翻译： 在圆周上具有多个燃料喷嘴组件（10）的环形燃气轮机燃烧器包括用于将用于扩散燃烧的燃料从先导外周喷嘴（34）喷射到燃烧室（8）中的先导喷嘴单元（12） 设置为围绕用于预混燃烧的燃料喷射的先导喷嘴单元（12）设置的主喷嘴单元（14），以及设置在每个燃料喷嘴组件（10）的下游侧的流动引导件（27） 并且具有从下游方向逐渐增加的每个燃料喷嘴组件（10）的空气和空气 - 燃料混合物的通道的截面面积。
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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：US20170321609A1
公开(公告)日：2017-11-09
申请号：US15523824
申请日：2015-11-04
发明人： Masahiro OGATA , Takeo ODA , Yasuhiro KINOSHITA , Kohshi HIRANO , Takahiro UTO
CPC分类号： F02C7/228 , F02C3/04 , F02C7/22 , F02C7/222 , F05D2220/32 , F05D2240/35 , F23R3/28 , F23R3/286 , F23R3/30 , F23R3/34 , F23R3/346 , F23R3/36 , F23R3/44
摘要： A burner injects a mixture of fuel and air from a base end side far from a combustion chamber toward a distal end side close to the combustion chamber. The burner has a fuel passage having a turn-back part turning back and channeling the fuel between the base end side and the distal end side. The burner has a premixed gas passage formed to surround the fuel passage. The burner has a fuel introduction part introducing the fuel channeled through the fuel passage into the premixed gas passage from the base end side to the distal end side. The burner has an air supply part supplying the premixed gas passage with air on the base end side.
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公开(公告)号：US20190162414A1
公开(公告)日：2019-05-30
申请号：US16313661
申请日：2017-06-13
发明人： Masahiro OGATA , Takeo ODA
摘要： A gas turbine combustor includes a casing coupled to a main housing; a liner having formed inside a combustion chamber that extends in an axial direction, an upstream portion including a head portion of the liner accommodated in the casing, and a downstream portion accommodated in the main housing; a main burner provided at the head portion of the liner; a supplemental burner including an injection port located in an air passage formed between the liner and the casing, the supplemental burner configured to inject an air-fuel mixture in which supplemental burning fuel containing hydrogen and the compressed air taken into the supplemental burner through the space formed between the liner and the casing are mixed; and a duct including an entrance connected to the injection port of the supplemental burner and an exit which opens in the combustion chamber, the duct extends in parallel with the axial direction.
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公开(公告)号：US20170211473A1
公开(公告)日：2017-07-27
申请号：US15515113
申请日：2015-09-28
发明人： Kazuhide HAKAMADA , Seiji YAMASHITA , Takeo ODA
CPC分类号： F02C3/30 , F02C3/22 , F02C3/305 , F02C7/16 , F02C7/22 , F23C2900/9901 , F23L7/005 , F23R3/00 , F23R3/28 , F23R2900/00002 , Y02E20/16
摘要： A gas turbine (100) of the present invention is a gas turbine which uses a hydrogen gas as a fuel, and comprises a combustor (20) which includes a fuel injection nozzle (23), and has a combustion chamber (24) in an interior of the combustor; a steam supply unit (40) which supplies steam to the combustor (20) to decrease a combustion temperature; and an air drier (50) which removes the steam from air to be supplied to the combustor (20) to dry the air.
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公开(公告)号：US20190264923A1
公开(公告)日：2019-08-29
申请号：US16407821
申请日：2019-05-09
发明人： Masayoshi KOBAYASHI , Takeo ODA , Takeo NISHIURA , Tomoko TSURU , Takaya HAMAMOTO , Takeshi TAKAGI , Osamu HISAMATSU , Hirotaka KURASHIMA
摘要： A combustor liner used for a gas turbine combustor and forming a combustion chamber includes: an outer side wall made of metal; a panel attached to an inner side of the outer side wall and made of a ceramic matrix composite material, the panel including a panel body facing the combustion chamber, and a connection piece rising from an exterior surface of the panel body at a side portion of the panel body and protruding in a lateral direction; and a connection unit configured to connect the panel to the outer side wall, the connection unit including an elastic member configured to bias at least one of the outer side wall and the connection piece, and a fixation member made of metal and configured to fix at least one of the connection piece and the elastic member to the outer side wall.
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公开(公告)号：US20170307210A1
公开(公告)日：2017-10-26
申请号：US15521314
申请日：2015-11-25
发明人： Kohshi HIRANO , Takahiro UTO , Takeo ODA , Yoshiharu NONAKA
CPC分类号： F23C5/08 , F23C3/002 , F23C7/00 , F23R3/28 , F23R3/286 , F23R3/34 , F23R3/36 , F23R3/38 , F23R2900/00002
摘要： Provided are a gas turbine combustor and a gas turbine, with which the amount of NOx exhaust emissions from a diffuse combustion-type duct burner can be reduced. A duct burner is provided with cylindrical fuel injection nozzles and air holes. The fuel injection nozzles are supported by an outside casing along eight axial centers included within a plane orthogonal to a center axis and arranged at equidistant intervals (45-degree intervals) in the circumferential direction. Sets of eight fuel injection nozzles are respectively constituted as single fuel injection nozzle rows, four fuel injection nozzle rows being arrayed at prescribed spacing along a direction of a center axis. The angular positions of the fuel injection nozzles are arrayed so as to be shifted by a half-pitch angle in opposing rows.
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公开(公告)号：US20170284677A1
公开(公告)日：2017-10-05
申请号：US15508736
申请日：2015-09-28
发明人： Atsushi HORIKAWA , Kunio OKADA , Seiji YAMASHITA , Masahide KAZARI , Takeo ODA
IPC分类号： F23R3/28
摘要： A fuel injection nozzle (31) of the present invention comprises a pre-mixing passage (34) which mixes fuel (103) and air (102) to generate an air-fuel mixture; and an injection port (33) which is located downstream of the pre-mixing passage (34) and injects the air-fuel mixture into a combustion chamber (26). The fuel injection port (33) has a slit shape and a width that is less than a dimension that is twice as large as a quenching distance.
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公开(公告)号：US20160033131A1
公开(公告)日：2016-02-04
申请号：US14421065
申请日：2014-06-12
发明人： Masahiro OGATA , Takeo ODA , Yasuhiro KINOSHITA
CPC分类号： F23R3/286 , F02C3/22 , F02C7/222 , F02C7/232 , F02C9/40 , F23C2900/9901 , F23D2900/00015 , F23R3/34 , F23R3/343 , F23R3/346 , F23R3/36 , F23R3/46 , F23R2900/00002
摘要： To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner (12) for supplying to and combusting a premixed gas (M), containing a first fuel (F1), within a first combustion region (S1) of a combustion chamber (10), and a supplemental burner (20) for supplying to and combusting a second fuel (F2) of a composition different from that of the first fuel (F1) within a second combustion region (S2) defined downstream of the first combustion region (S1) within the combustion chamber (10). The first fuel (F1) is of a hydrocarbon system and the second fuel (F2) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.
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公开(公告)号：US20180372319A1
公开(公告)日：2018-12-27
申请号：US16064599
申请日：2016-12-22
发明人： Ryusuke MATSUYAMA , Takeo ODA , Hitoshi FUJIWARA
摘要： A main fuel injector of a fuel injection device includes: a main outer air passage including an inlet that is open outward in a radial direction, the main outer air passage taking in compressed air through the inlet; a main inner air passage including an inlet that is open inward in the radial direction, the main inner air passage taking in the compressed air through the inlet; a merged air passage, in which the compressed air taken in by the main outer air passage and the compressed air taken in by the main inner air passage merge together; and a main fuel injection port configured to inject a fuel into the compressed air taken in by the main outer air passage or into the compressed air taken in by the main inner air passage.
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