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公开(公告)号：US20110067379A1
公开(公告)日：2011-03-24
申请号：US12563491
申请日：2009-09-21
CPC分类号： F23R3/36 , F23R2900/00002
摘要： A dual fuel combustor nozzle includes a body member including a first end portion that extends to a second end portion through an intermediate portion. The intermediate portion includes an outer wall portion and an inner wall portion with the inner wall portion defining a first fuel plenum. The dual fuel nozzle also includes an inner nozzle member arranged within the first fuel plenum. The inner nozzle member includes a first end section that extends to a second end section through an intermediate section. The intermediate section defines a second fuel plenum. The second end section being spaced from the second end portion of the body member so as to define a pre-emergence zone.
摘要翻译： 双燃料燃烧器喷嘴包括主体构件，其包括通过中间部分延伸到第二端部的第一端部。 中间部分包括外壁部分和内壁部分，其中内壁部分限定第一燃料增压室。 双燃料喷嘴还包括布置在第一燃料增压室内的内喷嘴构件。 内部喷嘴构件包括通过中间部分延伸到第二端部的第一端部。 中间部分限定第二燃料增压室。 第二端部与本体构件的第二端部分隔开，以限定出苗前区域。
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32.发明申请公开(公告)号：US20100170255A1
公开(公告)日：2010-07-08
申请号：US12350134
申请日：2009-01-07
CPC分类号： F23R3/14 , F23R3/286 , Y10T29/49348
摘要： A fuel nozzle including a swirler assembly that includes a shroud, a hub, and a plurality of vanes extending between the shroud and the hub. Each vane includes a pressure sidewall and an opposite suction sidewall coupled to the pressure sidewall at a leading edge and at a trailing edge. At least one suction side fuel injection orifice is formed adjacent to the leading edge and extends from a first fuel supply passage to the suction sidewall. A fuel injection angle is oriented with respect to the suction sidewall. The suction side fuel injection orifice is configured to discharge fuel outward from the suction sidewall. At least one pressure side fuel injection orifice extends from a second fuel supply passage to the pressure sidewall and is substantially parallel to the trailing edge. The pressure side fuel injection orifice is configured to discharge fuel tangentially from the trailing edge.
摘要翻译： 一种燃料喷嘴，其包括旋流器组件，该旋流器组件包括护罩，轮毂和在护罩和轮毂之间延伸的多个叶片。 每个叶片包括压力侧壁和在前缘和后缘处连接到压力侧壁的相对的抽吸侧壁。 至少一个吸入侧燃料喷射孔邻近前缘形成并从第一燃料供给通道延伸到吸力侧壁。 燃料喷射角度相对于吸力侧壁定向。 吸入侧燃料喷射孔构造成从吸力侧壁向外排出燃料。 至少一个压力侧燃料喷射孔从第二燃料供应通道延伸到压力侧壁并且基本上平行于后缘。 压力侧燃料喷射孔构造成从后缘切向地排放燃料。
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公开(公告)号：US08677760B2
公开(公告)日：2014-03-25
申请号：US12652858
申请日：2010-01-06
CPC分类号： F23R3/286 , F23R3/343 , F23R2900/03343
摘要： Disclosed is a method of operating a secondary fuel nozzle for a turbomachine combustor including delivering a flow of pilot fuel through a pilot fuel channel toward a combustion zone and delivering a flow of air through a plurality of transfer passages arranged around the pilot fuel channel toward the combustion zone. The flow of pilot fuel and the flow of air are combusted in the combustion zone, and a flow of transfer fuel is delivered through the plurality of transfer passages for combustion. A secondary fuel nozzle includes a pilot fuel channel extending along the fuel nozzle to deliver a flow of pilot fuel to a combustion zone. A plurality of transfer passages are arranged around the pilot fuel channel and are configured to deliver a flow of air for combustion with the flow of pilot fuel and to deliver a flow of transfer fuel to the combustion zone.
摘要翻译： 公开了一种操作用于涡轮机燃烧器的二次燃料喷嘴的方法，包括将先导燃料流通过引导燃料通道朝向燃烧区输送，并且将空气流通过布置在引燃燃料通道周围的多个输送通道朝向 燃烧区。 先导燃料的流动和空气的流动在燃烧区燃烧，并且传输燃料的流动通过多个传送通道被输送用于燃烧。 辅助燃料喷嘴包括沿着燃料喷嘴延伸的导向燃料通道，以将引导燃料流输送到燃烧区。 多个传送通道布置在引燃燃料通道周围，并被构造成输送用于与引燃燃料流一起燃烧的空气流并将传输燃料流传送到燃烧区。
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公开(公告)号：US08464537B2
公开(公告)日：2013-06-18
申请号：US12909092
申请日：2010-10-21
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23R3/343 , F23R2900/03343
摘要： A nozzle for a combustor is disclosed. The nozzle includes a center body, a burner tube provided around the center body and defining a fuel-air mixing passage therebetween, and an outer peripheral wall provided around the burner tube and defining an air flow passage therebetween. The nozzle further includes a nozzle tip connected to the center body. The nozzle tip includes a pilot fuel passage configured to deliver a flow of pilot fuel to a combustion zone, and a plurality of transfer passages. The plurality of transfer passages are configured to deliver a flow of air for combustion with the flow of pilot fuel in the combustion zone and further configured to deliver a flow of transfer fuel to the combustion zone.
摘要翻译： 公开了一种用于燃烧器的喷嘴。 喷嘴包括中心体，燃烧器管设置在中心体周围并在其间限定燃料 - 空气混合通道，外周壁设置在燃烧器管周围并且在其间限定空气流动通道。 喷嘴还包括连接到中心体的喷嘴尖端。 喷嘴尖端包括引导燃料通道，其构造成将先导燃料流输送到燃烧区域，以及多个输送通道。 所述多个传送通道构造成输送用于燃烧的空气流与所述燃烧区域中的引燃燃料流，并且进一步构造成将传输燃料流输送到所述燃烧区。
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公开(公告)号：US08365536B2
公开(公告)日：2013-02-05
申请号：US12563491
申请日：2009-09-21
IPC分类号： F02C1/00
CPC分类号： F23R3/36 , F23R2900/00002
摘要： A dual fuel combustor nozzle includes a body member including a first end portion that extends to a second end portion through an intermediate portion. The intermediate portion includes an outer wall portion and an inner wall portion with the inner wall portion defining a first fuel plenum. The dual fuel nozzle also includes an inner nozzle member arranged within the first fuel plenum. The inner nozzle member includes a first end section that extends to a second end section through an intermediate section. The intermediate section defines a second fuel plenum. The second end section being spaced from the second end portion of the body member so as to define a pre-emergence zone.
摘要翻译： 双燃料燃烧器喷嘴包括主体构件，其包括通过中间部分延伸到第二端部的第一端部。 中间部分包括外壁部分和内壁部分，其中内壁部分限定第一燃料增压室。 双燃料喷嘴还包括布置在第一燃料增压室内的内喷嘴构件。 内部喷嘴构件包括通过中间部分延伸到第二端部的第一端部。 中间部分限定第二燃料增压室。 第二端部与本体构件的第二端部分隔开，以限定出苗前区域。
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36.发明授权公开(公告)号：US08104286B2
公开(公告)日：2012-01-31
申请号：US12350134
申请日：2009-01-07
CPC分类号： F23R3/14 , F23R3/286 , Y10T29/49348
摘要： A fuel nozzle including a swirler assembly that includes a shroud, a hub, and a plurality of vanes extending between the shroud and the hub. Each vane includes a pressure sidewall and an opposite suction sidewall coupled to the pressure sidewall at a leading edge and at a trailing edge. At least one suction side fuel injection orifice is formed adjacent to the leading edge and extends from a first fuel supply passage to the suction sidewall. A fuel injection angle is oriented with respect to the suction sidewall. The suction side fuel injection orifice is configured to discharge fuel outward from the suction sidewall. At least one pressure side fuel injection orifice extends from a second fuel supply passage to the pressure sidewall and is substantially parallel to the trailing edge. The pressure side fuel injection orifice is configured to discharge fuel tangentially from the trailing edge.
摘要翻译： 一种燃料喷嘴，其包括旋流器组件，该旋流器组件包括护罩，轮毂和在护罩和轮毂之间延伸的多个叶片。 每个叶片包括压力侧壁和在前缘和后缘处连接到压力侧壁的相对的抽吸侧壁。 至少一个吸入侧燃料喷射孔邻近前缘形成并从第一燃料供给通道延伸到吸力侧壁。 燃料喷射角度相对于吸力侧壁定向。 吸入侧燃料喷射孔构造成从吸力侧壁向外排出燃料。 至少一个压力侧燃料喷射孔从第二燃料供应通道延伸到压力侧壁并且基本上平行于后缘。 压力侧燃料喷射孔构造成从后缘切向地排放燃料。
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公开(公告)号：US20120011854A1
公开(公告)日：2012-01-19
申请号：US12835227
申请日：2010-07-13
申请人： Abdul Rafey KHAN , Willy Steve Ziminsky , Chunyang Wu , Baifang Zuo , Christian Xavier Stevenson
发明人： Abdul Rafey KHAN , Willy Steve Ziminsky , Chunyang Wu , Baifang Zuo , Christian Xavier Stevenson
CPC分类号： F23R3/283 , F23D2214/00 , F23R3/04 , F23R3/14 , F23R3/286 , F23R3/34 , F23R2900/03044
摘要： A combustor for a gas turbine engine includes a plurality of primary nozzles configured to diffuse or premix fuel into an air flow through the combustor; and a secondary nozzle configured to premix fuel with the air flow. Each premixing nozzle includes a center body, at least one vane, a burner tube provided around the center body, at least two cooling passages, a fuel cooling passage to cool surfaces of the center body and the at least one vane, and an air cooling passage to cool a wall of the burner tube. The cooling passages prevent the walls of the center body, the vane(s), and the burner tube from overheating during flame holding events.
摘要翻译： 用于燃气涡轮发动机的燃烧器包括多个主喷嘴，其被配置为将燃料扩散或预混入通过燃烧器的空气流中; 以及辅助喷嘴，其构造成与空气流预混合燃料。 每个预混合喷嘴包括中心体，至少一个叶片，围绕中心体设置的燃烧器管，至少两个冷却通道，用于冷却中心体和至少一个叶片表面的燃料冷却通道，以及空气冷却 通道以冷却燃烧器管的壁。 在火焰保持事件期间，冷却通道防止中心体的壁，叶片和燃烧器管过热。
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公开(公告)号：US08256226B2
公开(公告)日：2012-09-04
申请号：US12428690
申请日：2009-04-23
IPC分类号： F02C1/00
CPC分类号： F23D14/24 , F23C2900/9901
摘要： A burner for use in a gas turbine engine includes a burner tube having an inlet end and an outlet end; a plurality of air passages extending axially in the burner tube configured to convey air flows from the inlet end to the outlet end; a plurality of fuel passages extending axially along the burner tube and spaced around the plurality of air passage configured to convey fuel from the inlet end to the outlet end; and a radial air swirler provided at the outlet end configured to direct the air flows radially toward the outlet end and impart swirl to the air flows. The radial air swirler includes a plurality of vanes to direct and swirl the air flows and an end plate. The end plate includes a plurality of fuel injection holes to inject the fuel radially into the swirling air flows. A method of mixing air and fuel in a burner of a gas turbine is also provided. The burner includes a burner tube including an inlet end, an outlet end, a plurality of axial air passages, and a plurality of axial fuel passages. The method includes introducing an air flow into the air passages at the inlet end; introducing a fuel into fuel passages; swirling the air flow at the outlet end; and radially injecting the fuel into the swirling air flow.
摘要翻译： 用于燃气涡轮发动机的燃烧器包括具有入口端和出口端的燃烧器管; 在燃烧器管中轴向延伸的多个空气通道，其构造成将空气流从入口端输送到出口端; 沿着燃烧器管轴向延伸并围绕多个空气通道间隔开的多个燃料通道，其构造成将燃料从入口端输送到出口端; 并且设置在出口端处的径向空气旋流器，其构造成引导空气沿着出口端径向流动，并向空气流提供涡流。 径向空气旋流器包括多个叶片以引导和旋转空气流和端板。 端板包括多个燃料喷射孔，以将燃料径向喷射到涡流空气流中。 还提供了在燃气轮机的燃烧器中混合空气和燃料的方法。 燃烧器包括燃烧器管，其包括入口端，出口端，多个轴向空气通道和多个轴向燃料通道。 该方法包括将空气流引入入口端的空气通道; 将燃料引入燃料通道; 在出口端旋转气流; 并将燃料径向喷射到旋转空气流中。
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公开(公告)号：US20120096866A1
公开(公告)日：2012-04-26
申请号：US12909092
申请日：2010-10-21
IPC分类号： F02C7/22
CPC分类号： F23R3/286 , F23R3/343 , F23R2900/03343
摘要： A nozzle for a combustor is disclosed. The nozzle includes a center body, a burner tube provided around the center body and defining a fuel-air mixing passage therebetween, and an outer peripheral wall provided around the burner tube and defining an air flow passage therebetween. The nozzle further includes a nozzle tip connected to the center body. The nozzle tip includes a pilot fuel passage configured to deliver a flow of pilot fuel to a combustion zone, and a plurality of transfer passages. The plurality of transfer passages are configured to deliver a flow of air for combustion with the flow of pilot fuel in the combustion zone and further configured to deliver a flow of transfer fuel to the combustion zone.
摘要翻译： 公开了一种用于燃烧器的喷嘴。 喷嘴包括中心体，燃烧器管设置在中心体周围并在其间限定燃料 - 空气混合通道，外周壁设置在燃烧器管周围并且在其间限定空气流动通道。 喷嘴还包括连接到中心体的喷嘴尖端。 喷嘴尖端包括引导燃料通道，其构造成将先导燃料流输送到燃烧区域，以及多个输送通道。 所述多个传送通道构造成输送用于燃烧的空气流与所述燃烧区域中的引燃燃料流，并且进一步构造成将传输燃料流输送到所述燃烧区。
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公开(公告)号：US20100186412A1
公开(公告)日：2010-07-29
申请号：US12360449
申请日：2009-01-27
IPC分类号： F02C7/08
摘要： Disclosed is a premixer for a combustor including an annular outer shell and an annular inner shell. The inner shell defines an inner flow channel inside of the inner shell and is located to define an outer flow channel between the outer shell and the inner shell. A fuel discharge annulus is located between the outer flow channel and the inner flow channel and is configured to inject a fuel flow into a mixing area in a direction substantially parallel to an outer airflow through the outer flow channel and an inner flow through the inner flow channel. Further disclosed are a combustor including a plurality of premixers and a method of premixing air and fuel in a combustor.
摘要翻译： 公开了一种用于燃烧器的预混合器，其包括环形外壳和环形内壳。 内壳在内壳内部限定内部流动通道，并且定位成在外壳和内壳之间限定外部流动通道。 燃料排出环位于外流动通道和内部流动通道之间，并且构造成将燃料流喷射到基本上平行于外部流动通道的外部气流的方向上的混合区域中，并且内部流动通过内部流动 渠道。 进一步公开的是包括多个预混合器的燃烧器和在燃烧器中预混合空气和燃料的方法。
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