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1.发明授权Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities 有权燃气轮机发动机燃烧器采用周边声学还原使用火焰温度不均匀性公开(公告)号：US08631656B2
公开(公告)日：2014-01-21
申请号：US12059256
申请日：2008-03-31
CPC分类号： F23R3/50 , F23R2900/00013 , F23R2900/00014
摘要： A gas turbine engine combustor includes an annulus with one or more circular rows of burners and a means for providing a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation. The number of the flame temperature nonuniformities being equal to a circumferential acoustic mode to be attenuated in the combustor (i.e three, five, or seven). Fuel lines and/or water lines in supply communication with the burners and metering orifices in a portion of the fuel lines and/or the water lines may be used to produce the flame temperature nonuniformities. The annulus of the burners may have an equal number of equiangular spaced apart first and second arcuate segments of the burners and a means for operating the burners in the first segments and operating the burners in the second segments at different first and second flame temperatures respectively.
摘要翻译： 燃气涡轮发动机燃烧器包括具有一个或多个圆形排燃烧器的环形空间，以及用于在发动机运行期间在环空周围提供多个等角间隔开的火焰温度不均匀性的装置。 火焰温度不均匀性的数量等于在燃烧器中被衰减的周向声学模式（即三个，五个或七个）。 可以使用与燃料管线和/或水管线的一部分中的燃烧器和计量孔供应连通的燃料管线和/或水管线来产生火焰温度不均匀性。 燃烧器的环带可以具有相等数量的燃烧器的等角度间隔开的第一和第二弧形段，以及用于在第一段中操作燃烧器并分别在不同的第一和第二火焰温度下操作第二段中的燃烧器的装置。
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2.发明申请GAS TURBINE ENGINE COMBUSTOR CIRCUMFERENTIAL ACOUSTIC REDUCTION USING FLAME TEMPERATURE NONUNIFORMITIES 有权气体涡轮发动机燃烧器使用火焰温度非均匀性进行循环减震公开(公告)号：US20090241548A1
公开(公告)日：2009-10-01
申请号：US12059256
申请日：2008-03-31
IPC分类号： F02C1/00
CPC分类号： F23R3/50 , F23R2900/00013 , F23R2900/00014
摘要： A gas turbine engine combustor includes an annulus with one or more circular rows of burners and a means for providing a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation. The number of the flame temperature nonuniformities being equal to a circumferential acoustic mode to be attenuated in the combustor (i.e three, five, or seven). Fuel lines and/or water lines in supply communication with the burners and metering orifices in a portion of the fuel lines and/or the water lines may be used to produce the flame temperature nonuniformities. The annulus of the burners may have an equal number of equiangular spaced apart first and second arcuate segments of the burners and a means for operating the burners in the first segments and operating the burners in the second segments at different first and second flame temperatures respectively.
摘要翻译： 燃气涡轮发动机燃烧器包括具有一个或多个圆形排燃烧器的环形空间，以及用于在发动机运行期间在环空周围提供多个等角间隔开的火焰温度不均匀性的装置。 火焰温度不均匀性的数量等于在燃烧器中被衰减的周向声学模式（即三个，五个或七个）。 可以使用与燃料管线和/或水管线的一部分中的燃烧器和计量孔供应连通的燃料管线和/或水管线来产生火焰温度不均匀性。 燃烧器的环带可以具有相等数量的燃烧器的等角度间隔开的第一和第二弧形段，以及用于在第一段中操作燃烧器并分别在不同的第一和第二火焰温度下操作第二段中的燃烧器的装置。
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公开(公告)号：US07905093B2
公开(公告)日：2011-03-15
申请号：US11689759
申请日：2007-03-22
申请人： Shui-Chi Li , Michael Louis Vermeersch , Zhong-Tao Dai , Timothy James Held , Mark Anthony Mueller
发明人： Shui-Chi Li , Michael Louis Vermeersch , Zhong-Tao Dai , Timothy James Held , Mark Anthony Mueller
IPC分类号： F02C1/00
摘要： A method for operating a gas turbine engine including a compressor and a combustor is provided. The method comprises channeling between about 0% to about 8% of the total airflow discharged from a compressor towards a pilot swirler coupled within the burner, wherein the burner includes a main swirler and an annular centerbody extending between the pilot and main swirlers, injecting a portion of the total fuel flow supplied to the burner through a plurality of apertures defined in a hollow pilot centerbody coupled within the pilot swirler, channeling the remaining airflow discharged from the compressor towards the main swirler, and injecting the remaining fuel flow supplied to the burner through at least one main swirler vane coupled within the main swirler, such that the portion of fuel is pre-mixed with a portion of the total airflow.
摘要翻译： 提供了一种用于操作包括压缩机和燃烧器的燃气涡轮发动机的方法。 该方法包括将从压缩机排出的总气流的约0％至约8％引导至连接在燃烧器内的先导式旋流器，其中燃烧器包括主旋流器和在飞行员和主旋流器之间延伸的环形中心体， 通过被连接在先导式旋流器内的中空先导中心体中限定的多个孔口供应到燃烧器的总燃料流量的一部分，将从压缩机排出的剩余气流引导到主旋流器，以及喷射供应到燃烧器的剩余燃料流 通过联接在主旋流器内的至少一个主旋流器叶片，使得燃料的一部分与总气流的一部分预混合。
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公开(公告)号：US20080229753A1
公开(公告)日：2008-09-25
申请号：US11689759
申请日：2007-03-22
申请人： Shui-Chi Li , Michael Louis Vermeersch , Zhong-Tao Dai , Timothy James Held , Mark Anthony Mueller
发明人： Shui-Chi Li , Michael Louis Vermeersch , Zhong-Tao Dai , Timothy James Held , Mark Anthony Mueller
IPC分类号： F02C3/04
摘要： A method for operating a gas turbine engine including a compressor and a combustor is provided. The method comprises channeling between about 0% to about 8% of the total airflow discharged from a compressor towards a pilot swirler coupled within the burner, wherein the burner includes a main swirler and an annular centerbody extending between the pilot and main swirlers, injecting a portion of the total fuel flow supplied to the burner through a plurality of apertures defined in a hollow pilot centerbody coupled within the pilot swirler, channeling the remaining airflow discharged from the compressor towards the main swirler, and injecting the remaining fuel flow supplied to the burner through at least one main swirler vane coupled within the main swirler, such that the portion of fuel is pre-mixed with a portion of the total airflow.
摘要翻译： 提供了一种用于操作包括压缩机和燃烧器的燃气涡轮发动机的方法。 该方法包括将从压缩机排出的总气流的约0％至约8％引导至连接在燃烧器内的先导式旋流器，其中燃烧器包括主旋流器和在飞行员和主旋流器之间延伸的环形中心体， 通过被连接在先导式旋流器内的中空先导中心体中限定的多个孔口供应到燃烧器的总燃料流量的一部分，将从压缩机排出的剩余气流引导到主旋流器，以及喷射供应到燃烧器的剩余燃料流 通过联接在主旋流器内的至少一个主旋流器叶片，使得燃料的一部分与总气流的一部分预混合。
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公开(公告)号：US08281597B2
公开(公告)日：2012-10-09
申请号：US12347165
申请日：2008-12-31
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23R3/14 , F23R3/20 , F23R3/343 , F23R2900/03044 , Y02T50/675
摘要： A combustor swirl cup includes coaxial inner and outer swirlers separated by a tubular centerbody. The centerbody includes a bypass inlet surrounding the inner swirler and diverges aft along a perforate inner nozzle to terminate at an annular flameholder. An impingement ring is spaced forward from the flameholder in flow communication with the bypass inlet for receiving cooling air therefrom to impingement cool the flameholder.
摘要翻译： 燃烧器旋流杯包括由管状中心体分开的同心的内旋流器和外旋流器。 中心体包括围绕内旋流器的旁路入口，并沿着穿孔内喷嘴向后分叉，以终止于环形火焰稳定器。 冲击环与火焰稳压器间隔开，与旁路入口流动连通，以从其中接收冷却空气，以冲击冷却火焰稳定器。
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公开(公告)号：US20080078181A1
公开(公告)日：2008-04-03
申请号：US11537100
申请日：2006-09-29
IPC分类号： F02C7/26
CPC分类号： F23R3/286 , F23R3/343 , F23R2900/00014 , F23R2900/03343
摘要： A method for operating a combustion system is provided. The method includes coupling the main swirler to the pilot swirler such that the main swirler substantially circumscribes the pilot swirler, supplying fuel to a first fuel circuit defined in the main swirler, and inducing swirling to the supplied fuel via a first set of swirler vanes positioned within the main swirler. The method also includes supplying fuel to a second fuel circuit defined in the main swirler, inducing swirling to the supplied fuel via a second set of swirler vanes positioned within the main swirler, each of the second set of swirler vanes comprising at least one second fuel passage defined therein, and coupling a shroud in flow communication to at least one of the first set of swirler vanes and the second set of swirler vanes, the shroud comprising at least one third fuel passage defined therein.
摘要翻译： 提供了一种操作燃烧系统的方法。 该方法包括将主旋流器连接到先导旋流器，使得主旋流器基本上限制先导旋流器，将燃料供应到在主旋流器中限定的第一燃料回路，并通过定位在第一组旋流器叶片上的所述供应燃料旋转 在主旋流器内。 该方法还包括将燃料供应到在主旋流器中限定的第二燃料回路，通过位于主旋流器内的第二组旋流器叶片引起向供应的燃料的旋转，第二组旋流器叶片中的每一个包括至少一个第二燃料 通道，并且将与流动连通的护罩耦合到第一组旋流器叶片和第二组旋流器叶片中的至少一个，所述护罩包括限定在其中的至少一个第三燃料通道。
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公开(公告)号：US07059135B2
公开(公告)日：2006-06-13
申请号：US11312273
申请日：2005-12-20
申请人： Timothy James Held , Mark Anthony Mueller , Jun Xu
发明人： Timothy James Held , Mark Anthony Mueller , Jun Xu
IPC分类号： F23R3/14
摘要： A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and an annular centerbody extending therebetween. The method comprises injecting at least one of fuel and airflow into the combustor through at least one swirler positioned within the pilot mixer, and injecting fuel into the combustor through at least one swirler positioned within the main mixer, such that the fuel is directed into a combustion chamber downstream from the main mixer.
摘要翻译： 用于操作燃气涡轮发动机的方法有助于减少来自燃烧器的排放量。 燃烧器包括一个混合器组件，该混合器组件包括一个先导式混合器，一个主混合器和一个在其间延伸的环形中心体。 该方法包括通过位于先导混合器内的至少一个旋流器将燃料和气流中的至少一种喷射到燃烧器中，并且通过位于主混合器内的至少一个旋流器将燃料喷射到燃烧器中，使得燃料被引导到 燃烧室主搅拌机下游。
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公开(公告)号：US08596071B2
公开(公告)日：2013-12-03
申请号：US11418613
申请日：2006-05-05
申请人： Mark Anthony Mueller , Zhongtao Dai , Michael Louis Vermeersch , Venkatraman Ananthakrishnanlyer , Timothy James Held , Jun Xu , Keith Robert McManus
发明人： Mark Anthony Mueller , Zhongtao Dai , Michael Louis Vermeersch , Venkatraman Ananthakrishnanlyer , Timothy James Held , Jun Xu , Keith Robert McManus
IPC分类号： F02C3/14
CPC分类号： F23R3/00 , F23R2900/00017
摘要： A method for assembling a gas turbine engine combustor is provided. The method includes providing a heat shield defined by a perimeter. The perimeter includes a radially inner edge, a radially outer edge, an axially inner edge, an axially outer edge, and an opening that extends from an upstream side of the heat shield to a downstream side of the heat shield. The method further includes coupling the heat shield to a domeplate such that the perimeter of the heat shield is positioned a distance downstream from an edge of the heat shield defining the opening. The method additionally includes coupling at least one fuel injector to the domeplate such that a portion of the fuel injector extends through the heat shield opening.
摘要翻译： 提供了一种用于组装燃气涡轮发动机燃烧器的方法。 该方法包括提供由周边限定的热屏蔽。 周边包括径向内边缘，径向外边缘，轴向内边缘，轴向外边缘和从隔热板的上游侧延伸到隔热罩的下游侧的开口。 该方法还包括将隔热罩联接到三脚架，使得隔热罩的周边定位在限定开口的隔热板的边缘的下游的距离处。 该方法另外包括将至少一个燃料喷射器联接到多孔板，使得燃料喷射器的一部分延伸穿过隔热开口。
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公开(公告)号：US20100162713A1
公开(公告)日：2010-07-01
申请号：US12347165
申请日：2008-12-31
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23R3/14 , F23R3/20 , F23R3/343 , F23R2900/03044 , Y02T50/675
摘要： A combustor swirl cup includes coaxial inner and outer swirlers separated by a tubular centerbody. The centerbody includes a bypass inlet surrounding the inner swirler and diverges aft along a perforate inner nozzle to terminate at an annular flameholder. An impingement ring is spaced forward from the flameholder in flow communication with the bypass inlet for receiving cooling air therefrom to impingement cool the flameholder.
摘要翻译： 燃烧器旋流杯包括由管状中心体分开的同心的内旋流器和外旋流器。 中心体包括围绕内旋流器的旁路入口，并沿着穿孔内喷嘴向后分叉，以终止于环形火焰稳定器。 冲击环与火焰稳压器间隔开，与旁路入口流动连通，以从其中接收冷却空气，以冲击冷却火焰稳定器。
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公开(公告)号：US07631500B2
公开(公告)日：2009-12-15
申请号：US11537100
申请日：2006-09-29
CPC分类号： F23R3/286 , F23R3/343 , F23R2900/00014 , F23R2900/03343
摘要： A method for operating a combustion system is provided. The method includes coupling the main swirler to the pilot swirler such that the main swirler substantially circumscribes the pilot swirler, supplying fuel to a first fuel circuit defined in the main swirler, and inducing swirling to the supplied fuel via a first set of swirler vanes positioned within the main swirler. The method also includes supplying fuel to a second fuel circuit defined in the main swirler, inducing swirling to the supplied fuel via a second set of swirler vanes positioned within the main swirler, each of the second set of swirler vanes comprising at least one second fuel passage defined therein, and coupling a shroud in flow communication to at least one of the first set of swirler vanes and the second set of swirler vanes, the shroud comprising at least one third fuel passage defined therein.
摘要翻译： 提供了一种操作燃烧系统的方法。 该方法包括将主旋流器连接到先导旋流器，使得主旋流器基本上限制先导旋流器，将燃料供应到在主旋流器中限定的第一燃料回路，并通过定位在第一组旋流器叶片上的所述供应燃料旋转 在主旋流器内。 该方法还包括将燃料供应到在主旋流器中限定的第二燃料回路，通过位于主旋流器内的第二组旋流器叶片引起向供应的燃料的旋转，第二组旋流器叶片中的每一个包括至少一个第二燃料 通道，并且将与流动连通的护罩耦合到第一组旋流器叶片和第二组旋流器叶片中的至少一个，所述护罩包括限定在其中的至少一个第三燃料通道。
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