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公开(公告)号：US20120006028A1
公开(公告)日：2012-01-12
申请号：US12832116
申请日：2010-07-08
申请人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
发明人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
CPC分类号： F01D9/023 , F02C7/12 , F05D2260/96 , F23R3/06 , F23R2900/00014
摘要： A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.
摘要翻译： 共振室（42）具有外壁（32），其具有冷却剂入口孔（34A-C），具有声孔（38）的内壁（36）和内壁和外壁之间的侧壁（40A-C） 。 外壁上的凹部（33A-C）具有与外壁的顶部（37A-C）相比靠近内壁的底部部分（50）。 冷却剂入口孔可以沿着凹陷的底部部分并且沿着侧壁的底部部分定位，以将冷却剂流（44,41）引向内壁上与声学不对准的冲击位置（43） 孔。 这提高了冲击冷却效率。 外壁的峰（37A-C）在共振室中提供用于目标共振的体积。
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公开(公告)号：US09546558B2
公开(公告)日：2017-01-17
申请号：US12832116
申请日：2010-07-08
申请人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
发明人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
CPC分类号： F01D9/023 , F02C7/12 , F05D2260/96 , F23R3/06 , F23R2900/00014
摘要： A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.
摘要翻译： 共振室（42）具有外壁（32），其具有冷却剂入口孔（34A-C），具有声孔（38）的内壁（36）和内壁和外壁之间的侧壁（40A-C） 。 外壁上的凹部（33A-C）具有与外壁的峰（37A-C）相比靠近内壁的底部部分（50）。 冷却剂入口孔可以沿着凹陷的底部部分并且沿着侧壁的底部部分定位，以将冷却剂流（44,41）引向内壁上与声学不对准的冲击位置（43） 孔。 这提高了冲击冷却效率。 外壁的峰（37A-C）在共振室中提供用于目标共振的体积。
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公开(公告)号：US20150159878A1
公开(公告)日：2015-06-11
申请号：US14102578
申请日：2013-12-11
IPC分类号： F23R3/58
CPC分类号： F23R3/58 , F23R3/06 , F23R3/16 , F23R2900/00014 , F23R2900/03045
摘要： A combustor for a gas turbine engine includes a pilot fuel injector and a plurality of circumferentially located main injectors for injecting fuel and air into a combustion chamber defined by a liner wall of a combustor basket. A combustion zone is located in the combustion chamber where the fuel and air are ignited to produce hot combustion gases. A plurality of vortex generators are located in circumferentially spaced relation on the liner wall and comprise structures extending radially inward into the combustion chamber to create vortices at predetermined circumferential locations downstream from where the fuel and air are ignited to effect a reduction in emissions of the combustion gases.
摘要翻译： 用于燃气涡轮发动机的燃烧器包括引燃燃料喷射器和用于将燃料和空气喷射到由燃烧器筐的衬套壁限定的燃烧室中的多个周向定位的主喷射器。 燃烧区位于燃烧室中，其中燃料和空气被点燃以产生热燃烧气体。 多个涡流发生器位于衬套壁上周向间隔开的关系上，并且包括径向向内延伸进入燃烧室的结构，以在燃料和空气被点燃的燃料和空气的下游的预定圆周位置处产生涡流，以实现燃烧排放的减少 气体。
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公开(公告)号：US20140338332A1
公开(公告)日：2014-11-20
申请号：US13893441
申请日：2013-05-14
IPC分类号： F23M23/20
CPC分类号： F23M20/005 , F23R3/002 , F23R3/60 , F23R2900/00014
摘要： An acoustically dampened gas turbine engine having a gas turbine engine combustor with an acoustic damping resonator system is disclosed. The acoustic damping resonator system may be formed from one or more resonators positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor. The resonator may be positioned in a head region of the combustor basket. In one embodiment, the resonator may be positioned in close proximity to an intersection between the outer housing and an upstream wall defining at least a portion of the combustor. The acoustic damping resonator system may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions.
摘要翻译： 公开了一种具有声阻尼谐振器系统的燃气涡轮发动机燃烧器的声阻尼燃气轮机。 声阻尼谐振器系统可以由位于燃气涡轮发动机燃烧器内的一个或多个谐振器形成，外部壳体形成燃烧器筐并在燃烧器内周向延伸。 谐振器可以定位在燃烧器筐的头部区域中。 在一个实施例中，谐振器可以定位成紧邻外壳体和限定燃烧器的至少一部分的上游壁之间的交叉点。 声阻尼谐振器系统可以减轻纵向模式动力学，从而增加发动机工作范围并减少排放。
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公开(公告)号：US09400108B2
公开(公告)日：2016-07-26
申请号：US13893441
申请日：2013-05-14
CPC分类号： F23M20/005 , F23R3/002 , F23R3/60 , F23R2900/00014
摘要： An acoustically dampened gas turbine engine having a gas turbine engine combustor with an acoustic damping resonator system is disclosed. The acoustic damping resonator system may be formed from one or more resonators positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor. The resonator may be positioned in a head region of the combustor basket. In one embodiment, the resonator may be positioned in close proximity to an intersection between the outer housing and an upstream wall defining at least a portion of the combustor. The acoustic damping resonator system may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions.
摘要翻译： 公开了一种具有声阻尼谐振器系统的燃气涡轮发动机燃烧器的声阻尼燃气轮机。 声阻尼谐振器系统可以由位于燃气涡轮发动机燃烧器内的一个或多个谐振器形成，外部壳体形成燃烧器筐并在燃烧器内周向延伸。 谐振器可以定位在燃烧器筐的头部区域中。 在一个实施例中，谐振器可以定位成紧邻外壳体和限定燃烧器的至少一部分的上游壁之间的交叉点。 声阻尼谐振器系统可以减轻纵向模式动力学，从而增加发动机工作范围并减少排放。
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公开(公告)号：US09366438B2
公开(公告)日：2016-06-14
申请号：US13767123
申请日：2013-02-14
CPC分类号： F23R3/26 , F23R3/10 , F23R3/46 , F23R3/54 , F23R2900/00014 , F23R2900/03043
摘要： A combustor assembly in a gas turbine engine includes a liner defining a combustion zone, at least one fuel injector for providing fuel, and a flow sleeve. An inner surface of the flow sleeve defines an outer boundary for an air flow passageway. Upon the air reaching a head end of the combustor assembly at an end of the air flow passageway the air turns 180 degrees to flow into the combustion zone where it is burned with the fuel. The combustor assembly further includes an inlet assembly positioned radially between the liner and the flow sleeve. The inlet assembly defines an inlet to the air flow passageway and includes a plurality of overlapping conduits that are arranged such that the air entering the air flow passageway passes through radial spaces between adjacent conduits.
摘要翻译： 燃气涡轮发动机中的燃烧器组件包括限定燃烧区的衬套，用于提供燃料的至少一个燃料喷射器和流动套筒。 流动套管的内表面限定了用于空气流动通道的外部边界。 当空气在空气流动通道的端部到达燃烧器组件的头端时，空气转动180度以流入燃烧区域，在燃烧区域中燃烧燃料。 燃烧器组件还包括径向位于衬套和流动套筒之间的入口组件。 入口组件限定了空气流动通道的入口，并且包括多个重叠的管道，其布置成使得进入空气流动通道的空气通过相邻导管之间的径向空间。
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公开(公告)号：US20140223914A1
公开(公告)日：2014-08-14
申请号：US13767123
申请日：2013-02-14
IPC分类号： F23R3/26
CPC分类号： F23R3/26 , F23R3/10 , F23R3/46 , F23R3/54 , F23R2900/00014 , F23R2900/03043
摘要： A combustor assembly in a gas turbine engine includes a liner defining a combustion zone, at least one fuel injector for providing fuel, and a flow sleeve. An inner surface of the flow sleeve defines an outer boundary for an air flow passageway. Upon the air reaching a head end of the combustor assembly at an end of the air flow passageway the air turns 180 degrees to flow into the combustion zone where it is burned with the fuel. The combustor assembly further includes an inlet assembly positioned radially between the liner and the flow sleeve. The inlet assembly defines an inlet to the air flow passageway and includes a plurality of overlapping conduits that are arranged such that the air entering the air flow passageway passes through radial spaces between adjacent conduits.
摘要翻译： 燃气涡轮发动机中的燃烧器组件包括限定燃烧区的衬套，用于提供燃料的至少一个燃料喷射器和流动套筒。 流动套管的内表面限定了用于空气流动通道的外部边界。 当空气在空气流动通道的端部到达燃烧器组件的头端时，空气转动180度以流入燃烧区域，在燃烧区域中燃烧燃料。 燃烧器组件还包括径向位于衬套和流动套筒之间的入口组件。 入口组件限定了空气流动通道的入口，并且包括多个重叠的管道，其布置成使得进入空气流动通道的空气通过相邻导管之间的径向空间。
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