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61. 发明公开

EP2796790A1 GAS TURBINE ENGINE PROVIDED WITH SCROLL 审中-公开
标题翻译： GASTURBINENMOTOR MIT SPIRALE
公开(公告)号：EP2796790A1
公开(公告)日：2014-10-29
申请号：EP12859396.9
申请日：2012-11-29
申请人： Kawasaki Jukogyo Kabushiki Kaisha
发明人： UEMURA, Daisuke , YAMASAKI, Yoshihiro , NAKASUJI, Takahiro
IPC分类号： F23R3/42
CPC分类号： F02C3/08 , F01D9/023 , F05D2260/38 , F05D2260/941 , F23R3/54 , F23R3/60
摘要： A gas turbine engine having high reliability is provided by suppressing occurrence of thermal stress between a scroll and a support member thereof. A gas turbine engine equipped with a combustor of a single-can type includes a scroll to guide a combustion gas fed from a combustor to a turbine while swirling the combustion gas about a rotation axis, a flange member to support the scroll with respect to the gas turbine engine from an inner peripheral side of the scroll, and a coupling member of an annular shape to couple the scroll and the flange member with each other. The scroll and the flange member are connected to the coupling member such that the scroll and the flange member are not in direct contact with each other.
摘要翻译：通过抑制涡卷与支承部件之间的热应力的发生，提供了高可靠性的燃气轮机。配备有单罐式燃烧器的燃气轮机包括：涡旋件，用于将从燃烧器供给的燃烧气体引导至涡轮机，同时围绕旋转轴线旋转燃烧气体;凸缘部件，用于将涡旋件相对于涡轮发动机和涡旋件的内周侧的气体涡轮发动机，以及将涡旋件和凸缘构件彼此连接的环形的联接构件。涡卷和凸缘构件连接到联接构件，使得涡旋件和凸缘构件不彼此直接接触。

62. 发明公开

EP2778532A1 COMBUSTOR LINER 有权
标题翻译： BRENNKAMMERWAND
公开(公告)号：EP2778532A1
公开(公告)日：2014-09-17
申请号：EP12846946.7
申请日：2012-11-06
申请人： IHI Corporation
发明人： OKITA Yoji , NAKAMATA Chiyuki , MATSUMOTO Yuuta , HOSOI Jun , HIROMITSU Nagayoshi
IPC分类号： F23R3/42 , F02C7/18 , F23R3/06
CPC分类号： F23R3/06 , F05D2260/22141 , F23R3/002 , F23R3/005 , F23R3/007 , F23R3/60 , F23R2900/00005 , F23R2900/00017 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
摘要： The invention is a combustor liner (12) of a dual wall cooling structure including an inner wall section (30) configured to surround a combustion region (13) and in which a plurality of effusion cooling holes (31) are formed, and an outer wall section (20) formed to be spaced apart from the inner wall section (30) and in which a plurality of impingement cooling holes (21) are formed, wherein the inner wall section (30) is constituted by a plurality of plate-shaped members (40), and a support guide member (50) is provided which is configured to guide the plurality of plate-shaped members (40) to enable free insertion and extraction and support the plurality of plate-shaped members (40) at intervals such that deformation by thermal expansion is able to be absorbed.
摘要翻译：本发明是一种双壁冷却结构的燃烧器衬套（12），其包括构造成围绕燃烧区域（13）的内壁部分（30），其中形成有多个排出冷却孔（31）壁部（20）形成为与内壁部（30）间隔开，并且形成有多个冲击冷却孔（21），其中，内壁部（30）由多个板状设置有构件（40）和支撑引导构件（50），其构造成引导多个板状构件（40），以能够自由地插入和取出并且间隔地支撑多个板状构件（40）使得能够吸收通过热膨胀的变形。

63. 发明公开

EP2778373A1 SEAL ASSEMBLY AND GAS TURBINE PROVIDED THEREWITH 有权转让
标题翻译： DICHTUNGSANORDNUNG UND GASTURBINE DAMIT
公开(公告)号：EP2778373A1
公开(公告)日：2014-09-17
申请号：EP12846960.8
申请日：2012-11-09
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： FUJIMOTO Kiyoshi , TANIGUCHI Kenta , AOYAMA Yudai
IPC分类号： F02C7/28 , F01D11/00 , F16J15/08 , F23R3/42
CPC分类号： F02C7/28 , F01D9/023 , F01D11/005 , F05D2240/55 , F16J15/0887 , F23R3/46 , F23R3/60 , F23R2900/00005 , F23R2900/00012
摘要： This seal assembly is disposed on each of a plurality of gas burners, and inserted into a space which is demarcated by a pair of depression parts which are disposed on the lateral faces of tailpipe exhaust port flanges that are adjacent at the lateral surfaces. The seal assembly comprises: a seal body in which seal parts are formed on each of the lateral faces that face one another in the pair of depression parts, and which are on down-stream sides of the combustion gas which flows within the tailpipes; and an elastic body which impels the seal body toward the downstream sides. The seal body further comprises seal plates which face the respective downstream side lateral faces of the pair of depressions and on which the seal parts are formed, and lateral plates which extend from respective lateral edges which face one another at the seal plates in the lateral face direction toward upstream sides of the combustion gas along the bottom faces of the depression parts. The elastic body further comprises a seal plate contact part which makes contact with the upstream face of the seal plate and impels the seal plate toward the downstream side, and an elastic part which extends to-ward the upstream side from the seal plate contact part with a portion thereof making contact with each respective upstream lateral face of the pair of depression parts.
摘要翻译：该密封组件设置在多个气体燃烧器中的每一个上，并且插入由一对凹陷部分划分的空间中，所述凹陷部分设置在与侧面相邻的尾管排气口凸缘的侧面上。密封组件包括：密封体，密封件形成在在一对凹陷部分中彼此面对的每个侧面上，并且位于在尾管内流动的燃烧气体的下游侧; 以及将密封体推向下游侧的弹性体。密封体还包括密封板，该密封板面对该对凹部的相应的下游侧面并且形成有密封部分，以及侧板，其从在侧面的密封板处彼此面对的相应侧边缘延伸沿着凹陷部分的底面朝向燃烧气体的上游侧的方向。弹性体还包括密封板接触部，其与密封板的上游面接触并向密封板的下游侧推压密封板，弹性部从密封板接触部朝向上游侧延伸，其一部分与所述一对凹陷部分的每个相应的上游侧面接触。

64. 发明公开

EP2730845A1 GAS TURBINE COMBUSTOR 有权转让
标题翻译：燃气轮机燃烧器
公开(公告)号：EP2730845A1
公开(公告)日：2014-05-14
申请号：EP12807850.8
申请日：2012-06-28
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： AKAMATSU, Shinji , KISHIDA, Hiroaki , SATO, Kenji , TOKUYAMA, Kentaro , MATSUYAMA, Keisuke , TAKASHIMA, Takayoshi
IPC分类号： F23R3/16 , F23R3/42
CPC分类号： F23R3/42 , F02C7/24 , F23M20/005 , F23R3/002 , F23R2900/00014
摘要： A gas turbine combustor comprises: a combustor liner through which a combustion gas flows that is produced by combusting a fuel jetted from nozzles; and a first resonator and a second resonator mounted on the outer surface of the combustor liner. The second resonator is positioned on the downstream side of the flow of the combustion gas to the first resonator and attenuates combustion vibration having a higher frequency than the first resonator does. The first and second resonators are acoustic liners having housings mounted on the outer surface of the combustor liner. The resonant spaces enclosed by the housings and the outer surface of the combustor liner communicate with the inner space of the combustor liner through a plurality of acoustic holes formed on the combustor liner.
摘要翻译：燃气轮机燃烧器包括：燃烧器衬套，燃烧气体流过所述燃烧器衬套，所述燃烧器衬套通过燃烧从喷嘴喷射的燃料而产生; 以及安装在燃烧器衬套的外表面上的第一谐振器和第二谐振器。第二谐振器位于燃烧气体向第一谐振器的流动的下游侧，并衰减具有比第一谐振器高的频率的燃烧振动。第一和第二谐振器是具有安装在燃烧器衬套的外表面上的壳体的声衬。由壳体和燃烧器衬套的外表面包围的谐振空间通过形成在燃烧器衬套上的多个声孔与燃烧器衬套的内部空间连通。

65. 发明公开

EP2693021A1 COMBUSTOR AND GAS TURBINE PROVIDED WITH SAME 有权转让
标题翻译： BRENNKAMMER UND GASTURBINE DAMIT
公开(公告)号：EP2693021A1
公开(公告)日：2014-02-05
申请号：EP12764209.8
申请日：2012-03-14
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： TAKIGUCHI, Satoshi , SAITO, Keijiro , MATSUMOTO, Teruhiro , SATO, Kenji , TAMAI, Hidenobu , MANDAI, Shigemi
IPC分类号： F02C7/18 , F23R3/42
CPC分类号： F02C7/18 , F01D9/023 , F01D25/14 , F23R3/002 , F23R3/286 , F23R3/42 , F23R2900/00012
摘要： A combustor (10) according to the invention includes: a combustor basket (14) in which compressed air and fuel are mixed with each other and the mixture is combusted; a transition piece (17) in which a tip portion of the combustor basket (14) is inserted with a gap (C) therebetween; a spring clip (19) that seals the gap between the combustor basket (14) and the transition piece (17); a throttle section (21) that is provided in an opening portion (Ck) of the gap (C) that is opened to the transition piece (17) on the tip side of the combustor basket (14), and narrows an opening area of the opening portion (Ck), compared to the base end side; and cooling device (22) for cooling the throttle section (21).
摘要翻译：根据本发明的燃烧器（10）包括：燃烧器筐（14），其中压缩空气和燃料彼此混合并且混合物燃烧; 一个过渡件（17），其中燃烧器筐（14）的顶端部分间插入有间隙（C）; 弹簧夹（19），其密封所述燃烧器筐（14）和所述过渡件（17）之间的间隙; 设置在所述间隙（C）的在所述燃烧器筐（14）的前端侧向所述过渡件（17）开口的开口部（Ck）中的节流部（21），并且使所述节流部所述开口部（Ck）与所述基端侧相比较; 和用于冷却节流部（21）的冷却装置（22）。

66. 发明公开

EP2690365A1 ACOUSTIC DAMPER, COMBUSTOR, AND GAS TURBINE 有权转让
标题翻译： SCHALLDÄMPFER，BRENNKAMMER UND GASTURBINE
公开(公告)号：EP2690365A1
公开(公告)日：2014-01-29
申请号：EP12760742.2
申请日：2012-02-20
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： ONO, Masaki , KONISHI, Tetsu
IPC分类号： F23R3/16 , F01D25/00 , F01D25/04 , F02C7/24 , F23R3/42
CPC分类号： F01N13/00 , F02C7/24 , F05D2260/963 , F05D2260/964 , F23M20/005 , F23R3/002 , F23R3/005 , F23R3/06 , F23R2900/00014 , F23R2900/03041
摘要： An acoustic damper is fixed to a vibration source to extend along an outer surface of the vibration source, forms a passage (R) that takes in air vibration (V) generated by the vibration source, and is provided with an acoustic section (N) having a partition member (5b) closing the downstream side of the passage (R) with respect to the propagation of air vibration (V) to serve as resistance against the air vibration (V), wherein the acoustic section (N) allows air vibration (V) to propagate in the reverse direction, and has partition members (5b, 5c) arranged so as to serve as resistance against the air vibration (V) in respective directions. This makes it possible to prevent generation of stress due to pressure fluctuation caused when reducing vibration, and to achieve a relatively compact configuration.
摘要翻译：声阻尼器固定在振动源上，沿着振动源的外表面延伸，形成一个通过振动源产生的空气振动（V）的通道（R），并设有声部（N）具有相对于空气振动（V）的传播而关闭通道（R）的下游侧以用作抵抗空气振动（V）的分隔构件（5b），其中声学部分（N）允许空气振动（V）沿相反方向传播，并且具有布置成用于抵抗各个方向上的空气振动（V）的分隔构件（5b，5c）。这使得可以防止由于在减少振动时引起的压力波动引起的应力产生，并且实现相对紧凑的构造。

67. 发明公开

EP2681438A2 FAULT TOLERANT CONTROL SYSTEM FOR DISTRIBUTED MICRO-THRUSTERS 审中-公开
标题翻译：容错控制系统的分布式微推力JETS
公开(公告)号：EP2681438A2
公开(公告)日：2014-01-08
申请号：EP12751939.5
申请日：2012-03-01
申请人： Game Changers, Llc
发明人： ZONENBERG, Andrew D. , SANCHEZ, Jason D. , GARBUZ, Piotr A.
IPC分类号： F02K3/08 , F02K7/00 , F23R3/42 , F23R3/60
CPC分类号： F03H1/0037 , F02K3/08 , F02K9/46 , F02K9/62 , F02K9/80 , F03H1/0018 , F03H99/00 , F05D2240/40 , F05D2270/09 , F05D2270/62
摘要： A control system for controlling the operation of a plurality of micro thrusters arranged in a plurality of parallel horizontal rows and a plurality of parallel vertical columns, the control system requires a power source, a first plurality of power lines connected to the power source and coupled to at least one micro thruster of the plurality of micro thrusters in a horizontal row of the plurality of parallel horizontal rows, a second plurality of power lines connected to the power source and coupled to at least one micro thruster of the plurality of micro thrusters in a vertical column of the plurality of parallel vertical columns, and a control unit coupled to the power source to control activation of the first plurality of power lines and activation of the second plurality of power lines.

68. 发明公开

EP2251530A4 GAS TURBINE 有权转让
公开(公告)号：EP2251530A4
公开(公告)日：2014-01-01
申请号：EP08872711
申请日：2008-11-20
申请人： MITSUBISHI HEAVY IND LTD
发明人： NAKAMURA SOSUKE , MATSUYAMA KEISUKE , HIYAMA TAKASHI , SAKAMOTO YASURO , SAKATA KAORU
IPC分类号： F01D9/02 , F01D5/14 , F01D9/04 , F23R3/42
CPC分类号： F01D9/023 , F01D5/142 , F01D9/041 , F05D2210/30 , F05D2210/40 , F05D2220/3212

69. 发明公开

EP2538138A3 Combustor assembly for use in a turbine engine and methods of assembling same 审中-公开
标题翻译：一种用于在涡轮发动机组件和方法中使用用于燃烧腔室组件的
公开(公告)号：EP2538138A3
公开(公告)日：2013-12-04
申请号：EP12172491.8
申请日：2012-06-18
申请人： General Electric Company
发明人： McMahan, Kevin Weston , Chila, Ronald James , Johns, David Richard
IPC分类号： F01D9/02 , F23R3/00 , F23R3/42
CPC分类号： F23R3/002 , F01D9/023 , F23R3/425 , F23R2900/03044 , Y10T29/49348
摘要： A combustor assembly (28) for use with a turbine engine (10) that includes a rotor assembly (22). The combustor assembly includes a casing (60) that includes a plenum (66) and a combustor liner (34) that is spaced a distance from the plenum and that defines a combustion chamber (70) therein. A transition nozzle (36) extends between the combustor liner and the rotor assembly for channeling combustion gases from the combustion chamber to the rotor assembly. The transition nozzle includes a transition portion (88) and a nozzle portion (90) integrally formed with the transition portion. An annular flowsleeve (104) is coupled radially outward from the transition nozzle such that an annular flow path (106) is defined between the flowsleeve and the transition nozzle. The flowsleeve includes a plurality of openings (124) extending through an outer surface of the flowsleeve for providing flow communication between the plenum and the annular flow path to facilitate impingement cooling of the flowsleeve.

70. 发明公开

EP2530381A2 Load member for transition duct in turbine system 有权转让
标题翻译： einemüberleitkanal在einem Turbinensystem的StützelementfüreinenÜberleitkanal
公开(公告)号：EP2530381A2
公开(公告)日：2012-12-05
申请号：EP12170067.8
申请日：2012-05-30
申请人： General Electric Company
发明人： Flanagan, James Scott , LeBegue, Jeffrey Scott , McMahan, Kevin Weston , Pentecost, Ronnie Ray
IPC分类号： F23R3/00 , F23R3/42 , F23R3/60
摘要： A loading assembly (102) for a turbine system (10) is disclosed. The loading assembly (102) includes a transition duct (50) and a load member (100). The transition duct (50) extends between a fuel nozzle (40) and a turbine section (18), and has an inlet (52), an outlet (54), and a passage (56) extending between the inlet (52) and the outlet (54) and defining a longitudinal axis (90), a radial axis (94), and a tangential axis (92). The outlet (54) of the transition duct (50) is offset from the inlet (52) along the longitudinal axis (90) and the tangential axis (92). The load member (100) extends from the transition duct (50) and is configured to transfer a load between the transition duct (50) and an adjacent transition duct (50) along at least one of the longitudinal axis (90), the radial axis (94), or the tangential axis (92).
摘要翻译：公开了一种用于涡轮机系统（10）的装载组件（102）。装载组件（102）包括过渡管道（50）和负载构件（100）。过渡管道（50）在燃料喷嘴（40）和涡轮部分（18）之间延伸，并且具有入口（52），出口（54）和在入口（52）和出口（54）并且限定纵向轴线（90），径向轴线（94）和切线轴线（92）。过渡管道（50）的出口（54）沿着纵向轴线（90）和切线轴线（92）偏离入口（52）。负载构件（100）从过渡管道（50）延伸，并且构造成沿着纵向轴线（90），径向（90）中的至少一个，在过渡管道（50）和相邻的过渡管道（50）轴（94）或切线轴（92）。

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