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1.发明授权Combustor connection structure, combustor transition piece, designing method of combustor transition piece and gas turbine 有权燃烧器连接结构，燃烧器过渡件，燃烧器过渡件和燃气轮机的设计方法公开(公告)号：US08955222B2
公开(公告)日：2015-02-17
申请号：US13874883
申请日：2013-05-01
发明人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
CPC分类号： F01D9/023 , F05D2250/50 , F23R3/46 , F23R3/60 , F23R2900/00017 , F23R2900/00018 , Y02E20/16 , Y10T29/49229 , Y10T29/49348
摘要： A cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79£DoutDin£0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in a radial direction between upstream ends of the inner shroud and the outer shroud has a same dimension as a size (a) in a radial direction of the transition piece outlet. In a combustor transition piece that is included in the combustor having a center line (S) arranged with an angle to an axial center (R) of a rotor of a gas turbine and that guides combustion gas to the turbine, a cross-sectional area is monotonously reduced from the transition piece inlet in which the combustion gas flows to the transition piece outlet from which the combustion gas flows out.
摘要翻译： 过渡件出口的横截面面积（Dout）相对于燃烧器的过渡件入口的横截面面积（Din）设定在0.79£DoutDin£0.9的范围内，在第一级涡轮机 连接到过渡件出口的涡轮的喷嘴，在内护罩的上游端和外护罩之间的径向尺寸（Hin）具有与过渡件出口的径向尺寸（a）相同的尺寸 。 在包括在具有与燃气轮机的转子的轴向中心（R）成一角度的中心线（S））并且将燃烧气体引导到涡轮机的燃烧器中的燃烧器过渡件中，横截面积 从燃烧气体流过到燃烧气体流出的过渡件出口的过渡件入口单调地减少。
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2.发明授权公开(公告)号：US09347666B2
公开(公告)日：2016-05-24
申请号：US13727283
申请日：2012-12-26
CPC分类号： F23R3/28 , F02C3/14 , F23R3/10 , F23R3/14 , F23R3/286 , F23R3/34 , F23R3/36 , F23R3/46 , F23R3/54 , F23R2900/00013
摘要： A combustor includes a combustor external cylinder, a tubular combustor basket installed in the combustor external cylinder, a compressed air channel defined between the combustor external cylinder and the combustor basket, and a plurality of fuel nozzles installed in the combustor basket. Compressed air flowing along the compressed air channel is approximately reversed in the flow direction at an end of the combustor basket, and is introduced into the plurality of fuel nozzles. Fuel injection pegs made up of an upstream side fuel injection peg injecting upstream side fuel and a downstream side fuel injection peg injecting downstream side fuel, are installed in the compressed air channel. Concentration fluctuation of the upstream side fuel caused by pressure fluctuation in the combustor is configured so as to reduce a peak of concentration fluctuation of the downstream side fuel at a combustion start position of the combustor.
摘要翻译： 燃烧器包括燃烧器外筒，安装在燃烧器外筒中的管状燃烧器篮，限定在燃烧器外筒和燃烧器筐之间的压缩空气通道，以及安装在燃烧器筐中的多个燃料喷嘴。 沿着压缩空气通道流动的压缩空气在燃烧器筐的端部处的流动方向上大致反转，并被引入到多个燃料喷嘴中。 在压缩空气通道中安装有由注入上游侧燃料的上游侧燃料喷射栓和喷射下游侧燃料的下游侧燃料喷射栓构成的燃料喷射栓。 由燃烧器的压力波动引起的上游侧燃料的浓度波动被构造成能够减小燃烧器的燃烧开始位置处的下游侧燃料的浓度波动的峰值。
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公开(公告)号：US20150226434A1
公开(公告)日：2015-08-13
申请号：US13727283
申请日：2012-12-26
CPC分类号： F23R3/28 , F02C3/14 , F23R3/10 , F23R3/14 , F23R3/286 , F23R3/34 , F23R3/36 , F23R3/46 , F23R3/54 , F23R2900/00013
摘要： A combustor includes a combustor external cylinder, a tubular combustor basket installed in the combustor external cylinder, a compressed air channel defined between the combustor external cylinder and the combustor basket, and a plurality of fuel nozzles installed in the combustor basket. Compressed air flowing along the compressed air channel is approximately reversed in the flow direction at an end of the combustor basket, and is introduced into the plurality of fuel nozzles. Fuel injection pegs made up of an upstream side fuel injection peg injecting upstream side fuel and a downstream side fuel injection peg injecting downstream side fuel, are installed in the compressed air channel. Concentration fluctuation of the upstream side fuel caused by pressure fluctuation in the combustor is configured so as to reduce a peak of concentration fluctuation of the downstream side fuel at a combustion start position of the combustor.
摘要翻译： 燃烧器包括燃烧器外筒，安装在燃烧器外筒中的管状燃烧器篮，限定在燃烧器外筒和燃烧器筐之间的压缩空气通道，以及安装在燃烧器筐中的多个燃料喷嘴。 沿着压缩空气通道流动的压缩空气在燃烧器筐的端部处的流动方向上大致反转，并被引入到多个燃料喷嘴中。 在压缩空气通道中安装有由注入上游侧燃料的上游侧燃料喷射栓和喷射下游侧燃料的下游侧燃料喷射栓构成的燃料喷射栓。 由燃烧器的压力波动引起的上游侧燃料的浓度波动被构造成能够减小燃烧器的燃烧开始位置处的下游侧燃料的浓度波动的峰值。
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公开(公告)号：US20140305094A1
公开(公告)日：2014-10-16
申请号：US14317357
申请日：2014-06-27
发明人： Kei Inoue , Keijiro Saito , Yoshikazu Matsumura , Sosuke Nakamura
IPC分类号： F23D14/70
摘要： Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.
摘要翻译： 提供一种燃气轮机燃烧器，其能够减小在先导火焰和预混合火焰之间形成的先导空气的低温空气层的尺寸，并提高预混火焰的火焰稳定性。 一种燃气轮机燃烧器，其设置有引导式燃烧器，该引燃式燃烧器设置在形成为圆筒状的燃烧器主体的中心部分以形成引燃火焰;以及多个主燃烧器， 形成预混火焰的引燃燃烧器包括作为点燃改善部件的减少先导火焰和预混火焰之间形成的先导空气的低温空气层的尺寸的通道阻挡构件。
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公开(公告)号：US20130219898A1
公开(公告)日：2013-08-29
申请号：US13687587
申请日：2012-11-28
IPC分类号： F02C7/22
CPC分类号： F02C7/22 , F23D11/24 , F23D11/38 , F23D2900/00016 , F23D2900/00018 , F23K2900/05001 , F23K2900/05141 , F23R3/00 , F23R3/28
摘要： A combustor according to the invention includes a combustor basket to which air A is supplied from the outside, a plurality of first nozzles that are annularly provided along the inner periphery of the combustor basket and that supply premixed gas M of the air and fuel to the inside of the combustor basket, and a transition piece in which the combustor basket is connected to a base end thereof and which burns the premixed gas supplied from the first nozzles, thereby forming a flame front spread to the outer periphery side toward the leading end in an axial direction, wherein each first nozzle supplies the premixed gas with fuel concentration changed around the center axis of the first nozzle such that the flame front has a uniform temperature in the axial direction.
摘要翻译： 根据本发明的燃烧器包括从外部供应空气A的燃烧器筐，沿着燃烧器筐的内周环形地设置的多个第一喷嘴，并将空气和燃料的预混合气体M供给到 在燃烧器筐的内部，以及过渡件，其中燃烧器筐连接到其基端，并且燃烧从第一喷嘴供给的预混合气体，从而形成朝向前端的前端的火焰前端扩展 轴向，其中每个第一喷嘴为预混合气供应燃料浓度在第一喷嘴的中心轴线周围改变，使得火焰前沿在轴向具有均匀的温度。
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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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公开(公告)号：US09926845B2
公开(公告)日：2018-03-27
申请号：US13687587
申请日：2012-11-28
CPC分类号： F02C7/22 , F23D11/24 , F23D11/38 , F23D2900/00016 , F23D2900/00018 , F23K2900/05001 , F23K2900/05141 , F23R3/00 , F23R3/28
摘要： A combustor according to the invention includes a combustor basket to which air A is supplied from the outside, a plurality of first nozzles that are annularly provided along the inner periphery of the combustor basket and that supply premixed gas M of the air and fuel to the inside of the combustor basket, and a transition piece in which the combustor basket is connected to a base end thereof and which burns the premixed gas supplied from the first nozzles, thereby forming a flame front spread to the outer periphery side toward the leading end in an axial direction, wherein each first nozzle supplies the premixed gas with fuel concentration changed around the center axis of the first nozzle such that the flame front has a uniform temperature in the axial direction.
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公开(公告)号：US09791149B2
公开(公告)日：2017-10-17
申请号：US14317357
申请日：2014-06-27
发明人： Kei Inoue , Keijiro Saito , Yoshikazu Matsumura , Sosuke Nakamura
摘要： Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.
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公开(公告)号：US09612013B2
公开(公告)日：2017-04-04
申请号：US14317363
申请日：2014-06-27
发明人： Kei Inoue , Keijiro Saito , Yoshikazu Matsumura , Sosuke Nakamura
摘要： Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.
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公开(公告)号：US20140305095A1
公开(公告)日：2014-10-16
申请号：US14317363
申请日：2014-06-27
发明人： Kei Inoue , Keijiro Saito , Yoshikazu Matsumura , Sosuke Nakamura
IPC分类号： F23D14/70
摘要： Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.
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