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101. 发明授权

US09395082B2 Combustor resonator section with an internal thermal barrier coating and method of fabricating the same 有权
标题翻译：具有内部热障涂层的燃烧器谐振器部分及其制造方法
公开(公告)号：US09395082B2
公开(公告)日：2016-07-19
申请号：US13622452
申请日：2012-09-19
申请人： Siemens Energy, Inc.
发明人： Abhijeet Tiwary , Stephen A. Ramier , Timothy A. Fox , James Bertoncello , Steven Williams
IPC分类号： F02C7/24 , F23R3/00 , F23R3/06 , F23M5/00 , F01N1/02 , F23R3/42 , F23M20/00
CPC分类号： F23M5/00 , F01N1/023 , F02C7/24 , F05D2260/963 , F23M20/005 , F23M2900/05004 , F23R3/002 , F23R3/06 , F23R3/42 , F23R2900/00014 , F23R2900/00017 , F23R2900/00018 , F23R2900/03042 , F23R2900/03044 , Y10T29/49323
摘要： A combustor (100) for a gas turbine engine (30) has a circumferentially extending liner (109) defining at least a portion of an interior combustion chamber (107) and a hot gas path (115). The liner includes a resonator section (112) including at least one resonator (116A, 116B) having a resonator chamber (125A, 125B) formed on an exterior of the liner. A thermal barrier coating (118) is disposed along an inner surface of the liner including an inner surface (130) of the resonator section. The resonator further includes a plurality of apertures (117) and each aperture extends through the liner and the thermal barrier coating at the resonator section and there is fluid flow communication between the combustion chamber and the resonator chamber.
摘要翻译：用于燃气涡轮发动机（30）的燃烧器（100）具有限定内部燃烧室（107）和热气体路径（115）的至少一部分的周向延伸的衬套（109）。衬套包括谐振器部分（112），该谐振器部分包括至少一个谐振器（116A，116B），该谐振器具有形成在衬套的外部上的谐振腔（125A，125B）。隔热层涂层（118）沿着衬套的内表面设置，包括谐振器部分的内表面（130）。谐振器还包括多个孔（117），并且每个孔在谐振器段处延伸穿过衬垫和热障涂层，并且在燃烧室和谐振腔之间存在流体流动连通。

102. 发明申请

US20160146464A1 COMBUSTOR WITH ANNULAR BLUFF BODY 审中-公开
公开(公告)号：US20160146464A1
公开(公告)日：2016-05-26
申请号：US14950601
申请日：2015-11-24
申请人： General Electric Technology GmbH
发明人： Ennio PASQUALOTTO , Douglas Anthony PENNELL , Michael DÜSING
IPC分类号： F23M20/00 , F23R3/34 , F23R3/28 , F23R3/00 , F23R3/14
CPC分类号： F23M20/005 , F23R3/002 , F23R3/14 , F23R3/286 , F23R3/343 , F23R3/54 , F23R2900/00014
摘要： The present invention relates to a gas turbine combustor comprising: a flow sleeve; a combustion liner located at least partially within the flow sleeve thereby creating a main passage between the flow sleeve and the combustor liner; a dome located forward of the flow sleeve and encompassing at least a part of the combustion liner, the dome having a substantially rounded head end thereby forming a turning passage between the liner and the head end; and a swirler wall aligned along a centerline of the combustor, the swirler wall projecting into the liner, wherein the swirler wall and the rounded head end are connected, wherein the connection forms an annular end face.
摘要翻译：本发明涉及一种燃气轮机燃烧器，包括：流动套管; 至少部分地位于流动套筒内的燃烧衬套，从而在流动套筒和燃烧器衬套之间形成主通道; 位于所述流动套筒前方的圆顶并且包围所述燃烧衬套的至少一部分，所述圆顶具有基本上圆形的头端，从而在所述衬套和所述头端之间形成转动通道; 以及沿着燃烧器的中心线对准的旋流器壁，所述旋流器壁突出到衬套中，其中旋流器壁和圆形头部端部被连接，其中连接件形成环形端面。

103. 发明授权

US09310079B2 Combustion liner with open cell foam and acoustic damping layers 有权
标题翻译：具有开孔泡沫和声阻尼层的燃烧衬里
公开(公告)号：US09310079B2
公开(公告)日：2016-04-12
申请号：US13162103
申请日：2011-06-16
申请人： Richard Christopher Uskert
发明人： Richard Christopher Uskert
IPC分类号： F23R3/06 , F23R3/00 , F23M20/00 , F23M5/02
CPC分类号： F23R3/06 , F23M5/02 , F23M20/005 , F23M2900/05004 , F23R3/002 , F23R3/007 , F23R2900/00014 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
摘要： The disclosure is directed to a gas turbine engine combustion liner and a gas turbine engine. The gas turbine engine combustion liner may include a thermally cooled wall section, an acoustically damped wall section, or a thermally cooled and acoustically damped wall section. Open cell foam or honeycomb may be disposed between inner and outer combustion liner walls. The walls, open cell foam, or honeycomb may be made of a composite material.
摘要翻译：本发明涉及燃气涡轮发动机燃烧衬套和燃气涡轮发动机。燃气涡轮发动机燃烧衬套可以包括热冷却壁部分，声阻挡壁部分或热冷却和声阻尼壁部分。开孔泡沫或蜂窝体可以设置在内燃烧衬套壁和外燃烧衬套壁之间。壁，开孔泡沫或蜂窝体可以由复合材料制成。

104. 发明授权

US09279586B2 Resonator device for damping the pressure oscillation within a combustion chamber and a method for operating a combustion arrangement 有权
标题翻译：用于抑制燃烧室内的压力振荡的谐振器装置和用于操作燃烧装置的方法
公开(公告)号：US09279586B2
公开(公告)日：2016-03-08
申请号：US13640340
申请日：2011-03-08
申请人： Ghenadie Bulat
发明人： Ghenadie Bulat
IPC分类号： F02C7/24 , F23R3/00 , F23M20/00
CPC分类号： F23R3/002 , F02C7/24 , F05D2260/963 , F23M20/005 , F23R2900/00013 , F23R2900/00014
摘要： A resonator device is provided for damping a pressure oscillation within a combustion chamber. The resonator device may comprise: a container filled with a gas; an opening in the container; and a heating element adapted to generate a flame. The flame is arranged to heat the gas within the container. The resonator device is comprised in a combustion arrangement comprising a combustion chamber for defining a combustion space for burning fuel. The container is connected to the combustion chamber such that an inside of the container is in communication with the combustion space via the opening. The resonator device has a resonance frequency equal to a pressure oscillation frequency within the combustion chamber under normal load conditions.
摘要翻译：提供一种用于阻尼燃烧室内的压力振荡的谐振器装置。谐振器装置可以包括：填充有气体的容器; 集装箱开口; 以及适于产生火焰的加热元件。火焰被布置成加热容器内的气体。谐振器装置包括在燃烧装置中，该燃烧装置包括用于限定用于燃烧燃料的燃烧空间的燃烧室。容器连接到燃烧室，使得容器的内部经由开口与燃烧空间连通。谐振器装置在正常负载条件下具有等于燃烧室内的压力振荡频率的共振频率。

105. 发明申请

US20150362189A1 BURNER SYSTEM WITH RESONATOR 审中-公开
标题翻译：燃烧器系统与谐振器
公开(公告)号：US20150362189A1
公开(公告)日：2015-12-17
申请号：US14303866
申请日：2014-06-13
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Andreas Böttcher , Peter KAUFMANN , Andre KLUGE , Boris Ferdinand KOCK , William R. RYAN , Udo SCHMITZ , Daniel VOGTMANN , Jaap VAN KAMPEN
IPC分类号： F23M20/00 , F23R3/34 , F23R3/00
CPC分类号： F23M20/005 , F23R3/002 , F23R3/286 , F23R3/343 , F23R2900/00014
摘要： The present invention relates to a burner system (1) comprising a pilot burner arrangement (2), a main burner arrangement (3) surrounding the pilot burner arrangement (2), a combustion chamber arranged downstream with respect to the pilot burner arrangement (2) and the main burner arrangement (3), and at least one resonator (17), wherein the main burner arrangement (3) defines a ring-shaped air supply (13) outwardly delimited by a burner cone (14) and provided with radially extending swirl vanes (15), wherein a resonator cavity (18) of the at least one resonator (17) is formed at the outside of the burner cone (14), wherein the resonator cavity (18) is provided with a plurality of resonator openings (20) defining a fluidic connection between the resonator cavity (18) and the combustion chamber.
摘要翻译：本发明涉及一种燃烧器系统（1），其包括引燃燃烧器装置（2），围绕引燃燃烧器装置（2）的主燃烧器装置（3），相对于引燃燃烧器装置（2）布置在下游的燃烧室）和主燃烧器装置（3）以及至少一个谐振器（17），其中主燃烧器装置（3）限定了由燃烧器锥体（14）向外限定并且径向设置的环形空气供应装置（13）延伸的旋流叶片（15），其中所述至少一个谐振器（17）的谐振腔（18）形成在所述燃烧器锥体（14）的外部，其中所述谐振器腔（18）设置有多个谐振器开口（20）限定谐振器腔（18）和燃烧室之间的流体连接。

106. 发明授权

US09200571B2 Fuel nozzle assembly for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的燃油喷嘴组件
公开(公告)号：US09200571B2
公开(公告)日：2015-12-01
申请号：US12498494
申请日：2009-07-07
申请人： Donald Mark Bailey , Scott R. Simmons , Marcus B. Huffman
发明人： Donald Mark Bailey , Scott R. Simmons , Marcus B. Huffman
IPC分类号： F23R3/20 , F02C7/22 , F23R3/14 , F23R3/28 , F23M20/00
CPC分类号： F02C7/22 , F05D2240/128 , F23D2900/00008 , F23M20/005 , F23R3/14 , F23R3/283 , F23R3/286 , F23R2900/00014 , F23R2900/00017 , F23R2900/00018
摘要： A fuel nozzle assembly for a gas turbine engine includes a flange and a pre-mix tube. The flange includes a first end that is configured to couple to an end cover of the combustor, and a second end that is opposite said first end. The pre-mix tube is coupled at a first end to the flange second end. The flange and the pre-mix tube are fabricated to operate at a natural frequency that is different from an operating frequency of the gas turbine engine.
摘要翻译：用于燃气涡轮发动机的燃料喷嘴组件包括凸缘和预混合管。凸缘包括构造成联接到燃烧器的端盖的第一端和与第一端相对的第二端。预混合管在第一端连接到凸缘第二端。法兰和预混合管被制造成以与燃气涡轮发动机的工作频率不同的固有频率工作。

107. 发明授权

US09127839B2 Combustion apparatus 有权
标题翻译：燃烧装置
公开(公告)号：US09127839B2
公开(公告)日：2015-09-08
申请号：US13708105
申请日：2012-12-07
申请人： Rinnai Corporation
发明人： Fumio Tanaka , Kazuyuki Akagi , Hideo Okamoto
IPC分类号： F23C7/00 , F23M20/00 , F23L1/00 , F23M9/02
CPC分类号： F23M20/00 , F23M20/005
摘要： A combustion apparatus has a burner, a combustion box containing therein a heat exchanger, an exhaust passage in fluid communication with the combustion box, a fan for supplying the burner with combustion air, and a predetermined length of air suction duct in fluid communication with a suction opening formed in a fan casing. The air suction duct has: on a downstream end thereof, an outlet cylindrical portion which is smaller in diameter than a diameter of the suction opening in the fan casing and which lies opposite to the suction opening; and a flange portion which overhangs radially outward from a perimeter of the air suction duct adjacent to the outlet cylindrical portion into contact with that peripheral portion of the fan casing which forms the suction opening. The flange portion is provided with an auxiliary suction opening in fluid communication with a space surrounding the outlet cylindrical portion.
摘要翻译：燃烧装置具有燃烧器，燃烧箱，其内装有热交换器，与燃烧箱流体连通的排气通道，用于向燃烧器提供燃烧空气的风扇，以及预定长度的空气吸入管道，其与吸入口形成在风扇壳体中。吸气管在其下游端具有直径小于风扇壳体中的吸入口的直径且与吸入口相对的出口圆筒部; 以及凸缘部，其从邻近出口圆筒部的吸气管的周边径向向外突出，与形成吸入口的风扇壳的周边部接触。凸缘部分设置有与围绕出口圆柱形部分的空间流体连通的辅助抽吸开口。

108. 发明申请

US20150128833A1 Cyclone Burner 审中-公开
标题翻译：旋风燃烧器
公开(公告)号：US20150128833A1
公开(公告)日：2015-05-14
申请号：US14359360
申请日：2011-11-25
申请人： Mads Nielsen , Mads Peter Rasmussen , Karl Emil Andreas Strömberg , Mads Kristian Ullitz , Jagannath Pandian Manohar
发明人： Mads Nielsen , Mads Peter Rasmussen , Karl Emil Andreas Strömberg , Mads Kristian Ullitz , Jagannath Pandian Manohar
IPC分类号： F23D1/02 , F23D1/00 , F23M20/00
CPC分类号： F23D1/02 , F23C3/006
摘要： A description is given of a cyclone burner for converting solid fuel comprising a substantially rotationally-symmetric whirling chamber (1), means for introducing gas and fuel into the whirling chamber (1), means for bringing the gas and fuel into rotation in the whirling chamber (1) and an outlet (4) for the gas and the converted fuel where the outlet (4) is centrally positioned in the outlet end (3) of the whirling chamber (1). The cyclone burner is characterized in that the whirling chamber (1) comprises a conical shaped portion (2) having the smaller diameter furthest from the outlet end (3) and in that the means (5) for introducing gas are connected to the whirling chamber (1) along the length of the conical shaped portion (2).
摘要翻译：描述了用于转换固体燃料的旋风燃烧器，其包括基本上旋转对称的旋转室（1），用于将气体和燃料引入旋转室（1）中的装置，用于使气体和燃料在旋转中旋转的装置室（1）和用于气体和转换燃料的出口（4），其中出口（4）位于旋转室（1）的出口端（3）中心。旋风式燃烧器的特征在于，旋转室（1）包括具有距出口端（3）最远的较小直径的圆锥形部分（2），并且用于引入气体的装置（5）连接到旋转室（1）沿着圆锥形部分（2）的长度。

109. 发明授权

US11686474B2 Damper for swirl-cup combustors 有权
公开(公告)号：US11686474B2
公开(公告)日：2023-06-27
申请号：US17192613
申请日：2021-03-04
申请人： General Electric Company
发明人： Kwanwoo Kim , Clayton Cooper , Steven Vise , Shai Birmaher , Pradeep Naik , Andrew Wickersham
IPC分类号： F23R3/28 , F02C7/22 , F23M20/00
CPC分类号： F23R3/286 , F02C7/22 , F23M20/005 , F05D2240/35 , F05D2260/963 , F23R2900/00014
摘要： A gas turbine engine may include a combustion section having a fuel nozzle, a swirler, and a ferrule configured to mount and center the fuel nozzle with the swirler. The combustion section may further include a damper on a cold side of the combustion section. The damper may have an acoustic cavity, a damper neck, and a cavity feed hole. The damper may operate as Helmholtz cavity to absorb a hydrodynamic or acoustic instability present in a region within the swirler.

110. 发明公开

US20230167975A1 FUEL NOZZLE WITH RESTRICTED CORE AIR PASSAGE 审中-公开
公开(公告)号：US20230167975A1
公开(公告)日：2023-06-01
申请号：US17535852
申请日：2021-11-26
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Tin-Cheung John HU
IPC分类号： F23R3/54 , F02C3/04 , F02C3/14 , F02C7/18 , F02C7/24 , F23C9/00 , F23M20/00 , F23R3/06 , F23R3/14 , F23R3/20 , F23R3/24 , F23R3/28 , F23R3/34 , F23R3/44
CPC分类号： F23R3/54 , F02C3/04 , F02C3/145 , F02C7/18 , F02C7/24 , F23C9/006 , F23M20/005 , F23R3/06 , F23R3/14 , F23R3/20 , F23R3/24 , F23R3/286 , F23R3/343 , F23R3/44 , F05D2220/32 , F23R2900/00014 , F23R2900/00015 , F23R2900/03042
摘要： A fuel nozzle for a combustor of an aircraft engine includes a nozzle body defining an a fuel passage, extending therethrough between a fuel inlet and a fuel outlet located at the outlet end that at least partially defines a nozzle tip, for directing a fuel flow into the combustor via the nozzle tip. A core air passage extends through the nozzle body for directing a core air flow into the combustor via the nozzle tip. At least two flow restrictors are disposed in series within the core air passage, the flow restrictors including an upstream flow restrictor and a downstream flow restrictor each having an orifice therein. The restricted air flow passage having a cross-sectional area smaller than that of the core air passage. The orifice in the upstream flow restrictor being at least partially offset from the orifice in the downstream flow restrictor.

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