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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：US20140308175A1
公开(公告)日：2014-10-16
申请号：US14316344
申请日：2014-06-26
发明人： Yasushi DOURA , Masahiro OGATA
IPC分类号： B01D53/94
CPC分类号： B01D53/94 , F23C13/04 , F23C2900/13001 , F23R3/40 , F23R3/60
摘要： A catalytic combustor (2) in a gas turbine engine (GT) includes a casing (54) for accommodating a catalyst carrier (10) therein, a catalyst retaining body (62) interposed between the casing (54) and the catalyst carrier (10) for retaining an outer peripheral surface of the catalyst carrier (10) to an inner peripheral surface of the casing (54) and also for preventing a gas (G2) from leaking in a downstream direction through an outer periphery of the catalyst carrier (10), a support material (64) disposed on a downstream side of the direction of flow of the gas to be treated in the catalyst carrier (10) for holding the catalyst carrier (10), and a downstream side regulating member (72) disposed on the downstream side of the catalyst retaining body (62) for avoiding a movement of the catalyst retaining body (62) in a direction of flow of the gas (G2).
摘要翻译： 燃气涡轮发动机（GT）中的催化燃烧器（2）包括用于在其中容纳催化剂载体（10）的壳体（54），介于壳体（54）和催化剂载体（10）之间的催化剂保持体 ），用于将催化剂载体（10）的外周表面保持到壳体（54）的内周面，并且还用于防止气体（G2）在催化剂载体（10）的外周沿下游方向泄漏 ），设置在用于保持催化剂载体（10）的催化剂载体（10）中待处理气体的流动方向的下游侧的支撑材料（64）和设置在下游侧调节构件（72）的支撑材料 在催化剂保持体（62）的下游侧，用于避免催化剂保持体（62）在气体（G2）的流动方向上移动。
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公开(公告)号：US20150362194A1
公开(公告)日：2015-12-17
申请号：US14620874
申请日：2015-02-12
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.
摘要翻译： 为了提供一种能够在保持由主燃烧器中的预混合燃烧引起的低排放性能的同时以低NOx燃烧高浓度的氢气的多燃气涡轮燃烧器，燃气轮机燃烧器包括主燃烧器（12） ），用于在燃烧室（10）的第一燃烧区域（S1）内供给和燃烧含有第一燃料（F1）的预混合气体（M）和用于供给和燃烧燃料的辅助燃烧器（20） 在第二燃烧区域（S2）内在第一燃烧区域（S1）的下游位于燃烧室（10）内的与第一燃料（F1）不同的组成的第二燃料（F2）。 第一燃料（F1）是烃系统，第二燃料（F2）是含有浓度超过氢的稳定的燃烧极限浓度的氢的气体。
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公开(公告)号：US20150275755A1
公开(公告)日：2015-10-01
申请号：US14736571
申请日：2015-06-11
发明人： Masahiro OGATA , Takeo ODA , Yasuhiro KINOSHITA
CPC分类号： F02C3/22 , F02C3/24 , F02C7/228 , F02C9/40 , F23C2900/9901 , F23R3/286 , F23R3/346 , F23R3/36
摘要： A multi-fuel-capable gas turbine combustor is provided which is able to sufficiently utilize various fuels having a characteristic deviating from a premixing characteristic range suitable for generating a premixed gas, even while maintaining favorable low-emission performance by premixed combustion. The gas turbine combustor includes: a main burner configured to supply a premixed gas containing a first fuel for premixing, to a first combustion region within a combustion chamber to cause premixed combustion; and a supplemental burner configured to supply a second fuel for reheating having a different composition from that of the first fuel, to a second combustion region at a location downstream of the first combustion region within the combustion chamber, to cause diffusion combustion. The first fuel has a premixing characteristic range suitable for generating a premixed gas. The second fuel has a characteristic deviating from the premixing characteristic range.
摘要翻译： 提供一种多燃料燃气轮机燃烧器，其能够充分利用具有偏离适合于产生预混合气体的预混合特性范围的特性的各种燃料，即使在通过预混燃烧保持有利的低排放性能的同时也是如此。 燃气轮机燃烧器包括：主燃烧器，其构造成将包含用于预混合的第一燃料的预混合气体供应到燃烧室内的第一燃烧区域以引起预混燃烧; 以及补充燃烧器，其构造成将具有与第一燃料的组成不同的组成的再加热用的第二燃料供应到燃烧室内的第一燃烧区域下游的第二燃烧区域，以引起扩散燃烧。 第一种燃料具有适于产生预混合气体的预混合特性范围。 第二燃料具有偏离预混合特性范围的特性。
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公开(公告)号：US20140308174A1
公开(公告)日：2014-10-16
申请号：US14316230
申请日：2014-06-26
发明人： Yasushi DOURA , Masahiro OGATA
IPC分类号： B01D53/94
CPC分类号： B01D53/94 , F23C13/04 , F23C2900/13001 , F23R3/40
摘要： A catalytic combustor (2) for use in a gas turbine engine (GT) includes catalyst units (U1, U2, U3) in a multistage. The catalyst unit (U1, U2, U3) in each stage includes a support material (64) for supporting the respective catalyst unit (U1, U2, U3) against the pressure of a gas. The catalyst unit (U1, U2, U3) in each stage is unitized together with the support material (64) and the catalyst units (U1, U2, U3) are removably fitted to a combustor housing (50).
摘要翻译： 用于燃气涡轮发动机（GT）的催化燃烧器（2）包括多级催化剂单元（U1，U2，U3）。 各级中的催化剂单元（U1，U2，U3）包括用于抵抗气体的压力支撑相应的催化剂单元（U1，U2，U3）的支撑材料（64）。 每个级中的催化剂单元（U1，U2，U3）与支撑材料（64）一体化，并且催化剂单元（U1，U2，U3）可拆卸地装配到燃烧器壳体（50）。
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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：US20140305126A1
公开(公告)日：2014-10-16
申请号：US14317777
申请日：2014-06-27
发明人： Yasushi DOURA , Masahiro OGATA , Kousuke TANAKI
IPC分类号： F02C7/22
CPC分类号： F02C7/22 , F23L15/00 , F23R3/04 , F23R3/40 , Y02E20/348
摘要： An apparatus for equalizing flow velocity distribution of a fuel gas supplied into a catalytic combustor includes a rectification vane and a rectification plate in an inlet chamber of the catalyst combustor. The inlet chamber has a round transverse sectional shape and includes an inflow port that allows the fuel gas to inflow radially, and an outflow port for discarding the fuel gas axially. The rectification vane has a front edge oriented towards the inflow port, and a rectifying surface ramified from the front edge so as to extend towards a cylindrical inner wall surface of the inlet chamber such that swirling flow of the fuel gas flown into the inlet chamber, that flows towards the inflow port along the cylindrical inner wall surface, is generated. The rectification plate is located at the outflow port and has openings for allowing the fuel gas to flow therethrough.
摘要翻译： 用于均衡供给到催化燃烧器中的燃料气体的流速分布的装置包括在催化剂燃烧器的入口室中的整流叶片和整流板。 入口室具有圆形横截面形状，并且包括允许燃料气体径向流入的流入口和用于轴向排放燃料气体的流出口。 整流叶片具有朝向流入口的前边缘，以及从前边缘分支的整流表面，以朝向入口室的圆柱形内壁表面延伸，使得燃料气体的旋流流入入口室， 产生沿着圆筒形内壁面向流入口流动的流路。 整流板位于流出口，具有允许燃料气体流过的开口。
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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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