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61. 发明授权

US09909501B2 Acoustic structure for a gas turbine engine 有权
公开(公告)号：US09909501B2
公开(公告)日：2018-03-06
申请号：US14228375
申请日：2014-03-28
申请人： Pratt & Whitney Canada Corp.
发明人： Stephen Caulfeild , Bryan Olver , Kin-Leung Cheung
IPC分类号： F02C7/25 , F02C7/24 , F02K1/82 , F23M20/00
CPC分类号： F02C7/25 , F02C7/24 , F02K1/827 , F05D2220/327 , F05D2240/14 , F05D2240/15 , F05D2250/283 , F05D2260/96 , F05D2300/44 , F05D2300/502 , F23M20/005 , Y02T50/672
摘要： An acoustic structure for a gas turbine engine comprising a noise reduction layer and a fire protector layer connected to the noise reduction layer. The noise reduction includes a perforated inner wall adapted to be in contact with a first fluidic environment, and a noise reduction adjacent to the inner wall. The fire protector layer includes a non-perforated outer wall adapted to be in contact with a second fluidic environment having potentially a fire, a fire protector adjacent to the outer wall, and a pressure resisting wall disposed between the fire protector and the noise reduction. The second fluidic environment is under a pressure lower than a pressure of the first fluidic environment. The inner and outer walls are load-bearing walls of the acoustic structure.

62. 发明申请

US20170276350A1 ACOUSTIC DAMPING SYSTEM FOR A COMBUSTOR OF A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20170276350A1
公开(公告)日：2017-09-28
申请号：US15509286
申请日：2014-09-09
申请人： Siemens Aktiengesellschaft
发明人： Reinhard Schilp , David M. Ritland , Erick J. Deane , Jaishree Sharma , Joseph Scott Markovitz
IPC分类号： F23M20/00 , F23R3/06 , F23R3/00 , F02C7/24
CPC分类号： F23M20/005 , F02C7/24 , F05D2260/96 , F23D2210/00 , F23R3/002 , F23R3/04 , F23R3/06 , F23R2900/00014
摘要： An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system (14) is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators (16) formed from a resonator housing (18) positioned within the gas turbine engine combustor (12) at an outer housing (20) forming a combustor basket (22) and extending circumferentially within the combustor (12). In at least one embodiment, the resonator housing (18) may include resonator chambers (26) that may be welded in place within resonator chamber (26) receivers (24) but easily replaceable without exposing the resonator housing (18) to damage. In another embodiment, an inner surface (32) of the resonator chamber (26) may be offset radially outward from an inner surface (34) of the resonator housing (18), thereby creating a flow-path discontinuity and reducing heating of the resonator chamber (26). The acoustic damping resonator system (14) may mitigate dynamics thereby increasing an engine operating envelope and decreasing emissions.

63. 发明授权

US09677505B2 Method for injecting fuel into a combustion chamber of a gas turbine, and injection system for implementing same 有权
公开(公告)号：US09677505B2
公开(公告)日：2017-06-13
申请号：US14126672
申请日：2012-06-19
申请人： Nicolas Savary , Claude Berat , Hubert Hippolyte Vignau , Christophe Nicolas Henri Viguier
发明人： Nicolas Savary , Claude Berat , Hubert Hippolyte Vignau , Christophe Nicolas Henri Viguier
IPC分类号： F23R3/60 , F02M7/00 , F23R3/28 , F02C7/20 , F23R3/14 , F23M20/00
CPC分类号： F02M7/00 , F02C7/20 , F23M20/005 , F23R3/14 , F23R3/283 , F23R3/286 , F23R3/60 , F23R2900/00013 , F23R2900/00014
摘要： An air/fuel mixer system of a combustion chamber of a gas turbine includes at least one compressed air intake swirler, the swirler having a central axis of symmetry, and a fuel injector including an injection head having an axis of symmetry. Each injector is mounted in the corresponding swirler with aid of a guide mechanism, so that the axis of symmetry of the injection head is off-center with respect to the central axis of symmetry of the swirler. The system can reduce, or even eliminate, combustion instabilities, by injecting the fuel along a particular axis which is off-center relative to the axis of the air/fuel mixer system, inducing a flow of fuel which is no longer perfectly axially symmetrical.

64. 发明授权

US09618206B2 Annular helmholtz damper 有权
公开(公告)号：US09618206B2
公开(公告)日：2017-04-11
申请号：US14488652
申请日：2014-09-17
申请人： ALSTOM Technology Ltd
发明人： Franklin Marie Genin , Naresh Aluri , Mirko Ruben Bothien
IPC分类号： F23R3/00 , F23M20/00
CPC分类号： F23R3/002 , F23M20/005 , F23R2900/00014 , Y10T29/49
摘要： The damper arrangement include two concentric hollow shapes, each having a wall, wherein the walls form an annular volume therebetween. The damper arrangement further includes one or more necks for connecting to a combustion chamber at corresponding one or more contact points. The one or more necks are connected to the annular volume.

65. 发明申请

US20170082287A1 BURNER ARRANGEMENT WITH RESONATOR 审中-公开
公开(公告)号：US20170082287A1
公开(公告)日：2017-03-23
申请号：US15310648
申请日：2015-04-17
申请人： Siemens Aktiengesellschaft
发明人： Christian Beck , Olga Deiss , Patrick Ronald Flohr , Anna Knödler
IPC分类号： F23M20/00
CPC分类号： F23M20/005 , F23R3/10 , F23R3/286 , F23R3/42 , F23R2900/00013 , F23R2900/00014
摘要： A burner arrangement having a combustion chamber, a multiplicity of mixing ducts discharging into the combustion chamber, in which ducts combustion air and fuel introduced during proper operation are mixed, and at least one resonator which has a defined resonator volume and resonator openings. The mixing ducts have mixing tubes which extend axially through an annular space defined between a tubular outer wall, a tubular inner wall arranged with the radial separation from the outer wall, an annular end plate arranged upstream and an annular end plate arranged downstream, wherein the end plates are provided with through openings which receive and/or prolong the mixing tubes. The resonator openings of the at least one resonator are designed as air ducts that extend through the downstream end plate, and the resonator volume of the at least one resonator is formed by at least one part of the annular space.

66. 发明授权

US09389001B2 Boiler, and a silencer for a flue gas duct in a boiler 有权
标题翻译：锅炉和锅炉中的烟气管道的消音器
公开(公告)号：US09389001B2
公开(公告)日：2016-07-12
申请号：US14122518
申请日：2012-05-24
申请人： Vesa Kainu , Juha Ojanpera
发明人： Vesa Kainu , Juha Ojanpera
IPC分类号： F01N1/02 , F24H9/00 , F23L15/04 , F22B37/06 , F23M20/00
CPC分类号： F24H9/0005 , F22B37/06 , F23J2900/13003 , F23L15/04 , F23M20/005 , Y02E20/348
摘要： A boiler includes a flue gas duct and heat exchanger pipes in the flue gas duct. The boiler includes a planar silencer plate, which silencer plate includes sound absorbing material, and said first silencer plate being placed downstream of one of said heat exchanger pipes in the flow direction of flue gases in said flue gas duct. Furthermore, a silencer for a flue gas duct with a rectangular cross-section in a boiler, the silencer including at least a first and a second planar silencer plate substantially parallel to the flow direction of flue gases, the silencer plates including sound absorbing material. The first silencer plate is placed at an angle to the second silencer plate, wherein the width of the resonating area of the flue gas duct becomes narrower in two directions transverse to the flow direction of the flue gases.
摘要翻译：锅炉包括烟气管道和烟气管道中的热交换器管道。该锅炉包括平坦的消音器板，该消声器板包括吸音材料，并且所述第一消声器板在所述烟气管道中的烟道气的流动方向上位于所述热交换器管之一的下游。此外，在锅炉中具有矩形截面的烟气管道的消音器，消音器至少包括基本上平行于烟道气流动方向的第一和第二平面消音器板，所述消音器板包括吸音材料。第一消声器板与第二消声器板成角度放置，其中烟道气道的谐振区域的宽度在横向于烟气流动方向的两个方向上变窄。

67. 发明申请

US20160161118A1 DAMPER FOR A GAS TURBINE 审中-公开
标题翻译：用于燃气涡轮的阻尼器
公开(公告)号：US20160161118A1
公开(公告)日：2016-06-09
申请号：US14958386
申请日：2015-12-03
申请人： General Electric Technology GmbH
发明人： Devis TONON , Mirko Ruben BOTHIEN
IPC分类号： F23M20/00 , F23R3/00
CPC分类号： F23M20/005 , F23R3/002 , F23R2900/00014
摘要： A damper for a gas turbine combustion chamber as shown in FIG. 1 includes a damper volume wall and a main neck. The damper volume wall defines a damper volume inside the damper volume wall. The main neck includes a main neck wall defining a main neck volume inside the main neck wall. The main neck is associated with the damper volume for fluid communication between the damper volume and the gas turbine combustion chamber. In addition, the damper includes a gap between the main neck wall and the damper volume wall. The main neck defines a main neck axis. For example, the gap is a second neck, and in further embodiments, multiple damper volumes are provided.
摘要翻译：用于燃气轮机燃烧室的阻尼器，如图1所示。 1包括减震器体积壁和主颈部。阻尼器体积壁在阻尼器体积壁内限定阻尼器体积。主颈部包括在主颈部壁内限定主颈部容积的主颈部壁。主颈部与阻尼器体积和燃气轮机燃烧室之间的流体连通的阻尼器体积相关联。此外，阻尼器包括主颈部壁和阻尼器体积壁之间的间隙。主颈部定义了主颈部轴。例如，间隙是第二颈部，并且在另外的实施例中，提供多个阻尼器体积。

68. 发明授权

US09334804B2 Acoustic damping device 有权
标题翻译：声阻尼装置
公开(公告)号：US09334804B2
公开(公告)日：2016-05-10
申请号：US14505564
申请日：2014-10-03
申请人： ALSTOM Technology Ltd
发明人： Mirko Ruben Bothien , Devis Tonon , Franklin Marie Genin , Douglas Anthony Pennell
IPC分类号： F02C7/24 , F23M20/00 , F23R3/16
CPC分类号： F02C7/24 , F23M20/005 , F23R3/16 , F23R2900/00014
摘要： An acoustic damper includes a neck and a damping volume. The neck has a mouth being in fluid connection with a chamber. The chamber is limited by an inner surface of at least one wall. The acoustic damper device includes a recess located between the mouth of the neck and the inner surface of the wall.
摘要翻译：声阻尼器包括颈部和阻尼体积。颈部具有与腔室流体连接的口。该室由至少一个壁的内表面限制。声阻尼装置包括位于颈部的口部和壁的内表面之间的凹部。

69. 发明授权

US09222674B2 Multi-stage amplification vortex mixture for gas turbine engine combustor 有权
标题翻译：用于燃气轮机发动机燃烧器的多级放大涡旋混合物
公开(公告)号：US09222674B2
公开(公告)日：2015-12-29
申请号：US13188451
申请日：2011-07-21
申请人： Frank J. Cunha , Torence P. Brogan
发明人： Frank J. Cunha , Torence P. Brogan
IPC分类号： F23R3/26 , F23R3/06 , F23N5/16 , F23M20/00
CPC分类号： F23R3/26 , F23D2900/14482 , F23M20/005 , F23N5/16 , F23N2041/20 , F23R3/06 , F23R2900/00013 , F23R2900/00018 , F23R2900/03042 , F23R2900/03044
摘要： A multi-stage vortex mixer for a combustor of a gas turbine engine includes a vortex amplifier stage in communication with a first stage amplifier, the vortex amplifier stage in communication with a dilution hole.
摘要翻译：用于燃气涡轮发动机的燃烧器的多级涡旋混合器包括与第一级放大器连通的涡流放大器级，与稀释孔连通的涡流放大器级。

70. 发明授权

US09188342B2 Systems and methods for dampening combustor dynamics in a micromixer 有权
标题翻译：用于抑制微混合器中的燃烧室动力学的系统和方法
公开(公告)号：US09188342B2
公开(公告)日：2015-11-17
申请号：US13425950
申请日：2012-03-21
申请人： Patrick Benedict Melton , James Harold Westmoreland
发明人： Patrick Benedict Melton , James Harold Westmoreland
IPC分类号： F23R3/28 , F02C7/24 , F23M20/00 , F23R3/32
CPC分类号： F23R3/286 , F02C7/24 , F05D2260/963 , F23M20/005 , F23R3/32 , F23R2900/00014 , F23R2900/03044
摘要： Embodiments of the present application can provide systems and methods for dampening combustor dynamics. According to one embodiment, the system may include a micromixer. The system may also include at least one annular resonator disposed within the micromixer adjacent to a cap face plate or an impingement plate of the micromixer. The at least one annular resonator may include a first side including a number of holes forming a cold side hole pattern, a second side including a number of holes forming a hot side hole pattern, and a cavity substantially defined by the first side and the second side.
摘要翻译：本申请的实施例可以提供用于衰减燃烧室动力学的系统和方法。根据一个实施例，系统可以包括微混合器。该系统还可以包括设置在微型混合器内的至少一个环形谐振器，其邻近盖板或微型混合器的冲击板。所述至少一个环形谐振器可以包括包括形成冷侧孔图案的多个孔的第一侧，包括形成热侧孔图案的多个孔的第二侧和基本上由第一侧和第二侧形成的空腔侧。

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