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41. 发明授权

US09482112B2 Gas turbine comprising a heat shield and method of operation 有权
标题翻译：包括隔热罩和操作方法的燃气轮机
公开(公告)号：US09482112B2
公开(公告)日：2016-11-01
申请号：US14009590
申请日：2012-03-23
申请人： Andrew Down
发明人： Andrew Down
IPC分类号： F01D25/12 , F02C7/18 , F01D25/14 , F01D9/04 , F01D11/08
CPC分类号： F01D25/14 , F01D9/042 , F01D11/08 , F01D25/12 , F02C7/18 , F05D2240/15
摘要： A turbine has a first and second inner wall, an inner casing and a shield element. The first and second inner walls are mounted to the inner casing such that an inner volume for working fluid is separated from an outer volume for cooling fluid. The first and second inner walls and inner casing are arranged to form a cavity in outer volume. The shield element is arranged inside cavity to separate cavity in an inner and outer region in a radially outer position to the inner region. A gap is formed between the first and second inner walls for working fluid between the inner volume and inner region. The shield element is arranged in cavity to form a fluid inlet for injecting cooling fluid from outer region to inner region for generating a predefined recirculation of working fluid and cooling fluid inside inner region.
摘要翻译：涡轮机具有第一和第二内壁，内壳和屏蔽元件。第一和第二内壁安装到内壳，使得用于工作流体的内部容积与用于冷却流体的外部容积分离。第一和第二内壁和内壳被布置成在外部体积中形成空腔。屏蔽元件设置在腔体内部，以将内部和外部区域中的空腔分隔成在内部区域的径向外部位置。在第一和第二内壁之间形成用于在内部容积和内部区域之间工作流体的间隙。屏蔽元件布置在空腔中以形成用于将冷却流体从外部区域注入到内部区域的流体入口，用于在内部区域内产生工作流体和冷却流体的预定的再循环。

42. 发明申请

US20160298647A1 COMPRESSOR STATOR ASSEMBLY AND METHOD OF INSTALLING 审中-公开
标题翻译：压缩机定子组件和安装方法
公开(公告)号：US20160298647A1
公开(公告)日：2016-10-13
申请号：US15188124
申请日：2016-06-21
申请人： General Electric Company
发明人： Michael Thomas Hudson , Ryan Wesley Murphy
IPC分类号： F04D29/54 , F04D29/64
CPC分类号： F04D29/542 , F01D5/3007 , F01D9/042 , F01D25/246 , F04D29/644 , F05D2230/60
摘要： A compressor stator assembly includes a stator casing having a plurality of stator casing slots and a set of stator portions insertable into the stator casing slots. The stator casing and the set of stator portions are configured such that the set of stator portions only assembles to the stator casing in a single stage of the stator casing, or in a single configuration. The set of stator portions includes a plurality of stator vanes, and the stator vanes have a stator vane characteristic that varies for each stage in the stator casing. The stator vane characteristic is at least one of, a radial height of a forward sidewall, a radial height of an aft sidewall or an axial length.
摘要翻译：压缩机定子组件包括具有多个定子壳体狭槽的定子壳体和可插入到定子壳体槽中的一组定子部分。定子壳体和一组定子部分被构造成使得该组定子部分仅在定子壳体的单个级中或在单个配置中组装到定子壳体。该组定子部分包括多个定子叶片，并且定子叶片具有定子叶片特性，该定子叶片特性对于定子壳体中的每个阶段而变化。定子叶片特性是前侧壁的径向高度，后侧壁的径向高度或轴向长度中的至少一个。

43. 发明申请

US20160290146A1 MULTI-AIRFOIL GUIDE VANE UNIT 审中-公开
标题翻译：多空气导轨风扇单元
公开(公告)号：US20160290146A1
公开(公告)日：2016-10-06
申请号：US15084145
申请日：2016-03-29
申请人： ANSALDO ENERGIA IP UK LIMITED
发明人： Herbert BRANDL
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D9/042
摘要： A multi-airfoil guide vane unit includes a first platform member, a second platform member, and at least two airfoil members, the airfoil members having a longitudinal extent along an airfoil span width and two longitudinal ends, wherein all airfoil members are rigidly affixed to a platform member at a first longitudinal end and at least one airfoil member is rigidly affixed to both platform members at both longitudinal ends. At least one of the airfoil members is floatingly connected to one of the platform members at a second longitudinal end. A longitudinally floating joint arrangement is thus provided between the second longitudinal end of the airfoil member and the platform member, such as to allow displacement of the airfoil member relative to said platform member along the longitudinal extent of said airfoil member.
摘要翻译：多翼型导叶单元包括第一平台构件，第二平台构件和至少两个翼型构件，所述翼型构件具有沿着翼型跨度宽度的纵向长度和两个纵向端部，其中所有翼型构件刚性地固定到在第一纵向端部处的平台构件和至少一个翼型构件在两个纵向端部处刚性地固定到两个平台构件。至少一个翼型件在第二纵向端部浮动地连接到一个平台构件。因此，在翼型构件的第二纵向端部和平台构件之间设置纵向浮动接头装置，以允许翼型件相对于所述平台构件沿所述翼型构件的纵向尺寸移位。

44. 发明申请

US20160281522A1 SEALING ARRANGEMENTS IN GAS TURBINES 审中-公开
标题翻译：密封在涡轮机中的安排
公开(公告)号：US20160281522A1
公开(公告)日：2016-09-29
申请号：US15081101
申请日：2016-03-25
申请人： ANSALDO ENERGIA SWITZERLAND AG
发明人： Frank GRAF , Hans-Christian MATHEWS , Urs BENZ , Fabien FLEURIOT
IPC分类号： F01D11/00 , F01D25/24 , F01D25/12 , F01D9/02
CPC分类号： F01D11/005 , F01D9/00 , F01D9/02 , F01D9/042 , F01D11/00 , F01D25/12 , F01D25/24 , F01D25/246 , F02C7/28 , F05D2220/32 , F05D2240/12 , F05D2240/55 , F05D2260/20 , F16J15/00
摘要： The invention concerns a gas turbine having a picture frame, a first vane, and a sealing arrangement to seal a gap between the picture frame and the first vane, the sealing arrangement including two seals arranged in series between the picture frame and the first vane. In exemplary embodiments, one of the seals is a honeycomb seal, a dogbone seal, a hula seal or a piston seal and the other seal is a honeycomb seal, a dogbone seal, a hula seal or a piston seal. A method of supplying cooling fluid to the gap between the picture frame and the first vane is also disclosed.
摘要翻译：本发明涉及一种具有相框，第一叶片和密封装置的燃气轮机，用于密封相框和第一叶片之间的间隙，密封装置包括串联布置在相框和第一叶片之间的两个密封件。在示例性实施例中，密封件之一是蜂窝密封件，狗骨密封件，呼啦密封件或活塞密封件，另一个密封件是蜂窝密封件，狗骨密封件，呼啦密封件或活塞密封件。还公开了向相框和第一叶片之间的间隙供应冷却流体的方法。

45. 发明申请

US20160273390A1 EXHAUST GAS LINER FOR A GAS TURBINE AND GAS TURBINE WITH SUCH AN EXHAUST GAS LINER 有权
标题翻译：用于气体涡轮机的排气管和具有这种排气气体的气体涡轮机
公开(公告)号：US20160273390A1
公开(公告)日：2016-09-22
申请号：US14741941
申请日：2015-06-17
申请人： ALSTOM Technology Ltd
发明人： Igor MIHALIC , Mirjana MIHELIC , Mladen MATAN , Pedja MILANKOVIC , Juergen PACHOLLECK , Christian Joerg KREUTLE
IPC分类号： F01D25/30 , F02K1/82 , F01D25/14
CPC分类号： F01D25/30 , F01D9/042 , F01D25/145 , F01D25/24 , F01D25/243 , F01D25/246 , F02C7/20 , F02K1/822 , Y02T50/675
摘要： An exhaust gas liner for a gas turbine includes an annular inner shell and an annular outer shell, which are arranged concentrically around a machine axis of the gas turbine to define an annular exhaust gas channel in between. The inner shell and/or said outer shell are composed of a plurality of liner segments, which are attached to a support structure. To compensate thermal expansion and achieving resistance against dynamic loads, the liner segments are fixed to the support structure at certain fixation spots, which are distributed over the area of said liner segments, such that said liner segments are clamped to said support structure through a whole engine thermal cycle without hindering thermal expansion.
摘要翻译：用于燃气轮机的排气衬套包括环形内壳和环形外壳，其围绕燃气轮机的机器轴线同心地布置以在其间限定环形排气通道。内壳和/或所述外壳由多个衬垫段组成，其连接到支撑结构。为了补偿热膨胀并实现抵抗动态载荷的阻力，衬套段在某些固定点处固定到支撑结构上，该固定点分布在所述衬套段的区域上，使得所述衬套段通过整体被夹紧到所述支撑结构发动机热循环，而不会阻碍热膨胀。

46. 发明申请

US20160265374A1 MOUNTING DEVICE AND MOUNTING METHOD 审中-公开
标题翻译：安装设备和安装方法
公开(公告)号：US20160265374A1
公开(公告)日：2016-09-15
申请号：US15033201
申请日：2014-09-18
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Stefan Bentele , Ulrich Beul , Frank Brumbi , Oliver Ceranski , Manuel Ettler , Thomas Helmis , Markus Hofmann , Daniel Lindemann , Adam Maguire , Oliver Ricken , Andreas Stiehm
IPC分类号： F01D9/04
CPC分类号： F01D9/042 , F01D5/28 , F01D5/3007 , F01D5/303 , F01D5/3038 , F05D2220/30 , F05D2230/60 , F05D2230/64 , F05D2230/68 , F05D2240/12
摘要： A mounting device for mounting a guide blade to be mounted in a blade groove of a turbine, where the mounting unit has a clamping unit and a pressing unit. Here, the clamping unit is designed to produce in the blade groove a non-positive connection in a circumferential direction. The pressing unit is arranged behind the clamping unit in the circumferential direction and the pressing unit is supported against the clamping unit in the circumferential direction. The pressing unit is designed to apply a pressing force by means of a pressing piston in an opposite direction to the circumferential direction in a mounting direction and to transmit said force to the guide blade to be mounted.
摘要翻译：一种用于安装安装在涡轮叶片槽中的导向叶片的安装装置，其中安装单元具有夹紧单元和按压单元。这里，夹紧单元被设计成在叶片槽中沿圆周方向产生非正向连接。挤压单元沿圆周方向布置在夹持单元的后面，并且按压单元在圆周方向上被支撑在夹紧单元上。按压单元被设计成通过按压活塞沿与安装方向的圆周方向相反的方向施加按压力，并将所述力传递到待安装的导向叶片。

47. 发明申请

US20160221130A1 TRUNNION HOLE REPAIR UTILIZING INTERFERENCE FIT INSERTS 有权
标题翻译： TRUNNION孔修复利用干涉固定插件
公开(公告)号：US20160221130A1
公开(公告)日：2016-08-04
申请号：US15131235
申请日：2016-04-18
申请人： United Technologies Corporation
发明人： Mark E. Addis , George H. Reynolds
IPC分类号： B23P6/00 , B23P11/02 , F04D29/56 , F01D17/14 , F04D29/54
CPC分类号： B23P6/005 , B23P6/002 , B23P11/02 , B23P11/025 , F01D9/042 , F01D17/14 , F01D17/162 , F04D29/545 , F04D29/563 , F04D29/644 , F05D2220/32 , F05D2230/80 , F05D2240/14 , F05D2260/74 , Y10T29/49318 , Y10T29/49726 , Y10T29/49735 , Y10T29/49737 , Y10T29/49739 , Y10T29/49865
摘要： The present application discloses a method for repairing a damaged counterbore in a variable vane shroud. A layer of base material is removed from the vane shroud adjacent the counterbore such that a damaged portion of the counterbore is removed. A shrink-fit insert having a size slightly larger than that corresponding to the layer of base material removed from the shroud is placed into the area of removed material such that the counterbore is restored to pre-damaged dimensions upon installation of the shrink-fit insert.
摘要翻译：本申请公开了一种在可变叶片护罩中修复损坏的沉孔的方法。从邻近沉孔的叶片护罩中取出一层基底材料，以便去除沉孔的损坏部分。具有略大于从护罩移除的与基材层相对应的尺寸的收缩配合插入物被放置在去除材料的区域中，使得当安装收缩配合插入件时，沉孔恢复到预损坏的尺寸。

48. 发明申请

US20160208630A1 SEALING RING SEGMENT FOR A STATOR OF A TURBINE 审中-公开
标题翻译：用于涡轮定子的密封环段
公开(公告)号：US20160208630A1
公开(公告)日：2016-07-21
申请号：US14898135
申请日：2014-06-25
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Thorsten Barz , Roland Habel , Sebastian Stupariu-Cohan
IPC分类号： F01D9/04 , F01D11/00
CPC分类号： F01D9/042 , F01D11/001 , F05D2240/80 , F05D2260/30
摘要： A sealing ring segment for a stator of a turbine, the sealing ring segment has substantially the shape of a cylinder casing segment and has on its outer side a groove for fixing a plurality of guide vanes. The sealing ring segment has, for each guide vane that is fixable to the sealing ring segment, at least one pressure bolt that acts on the respective guide vane by a restoring force, the pressure bolt being able to be fixed and accordingly oriented by a corresponding opening in the sealing ring segment and being configured as a cylindrical element which can be compressed in the axial direction, and wherein the respective pressure bolt has a disk spring and the restoring force of the respective pressure bolt acts in the radial direction with respect to the rotation axis of the turbine in which the sealing ring segment is placed.
摘要翻译：一种用于涡轮机的定子的密封环段，密封环段具有基本上为气缸壳体段的形状，并且在其外侧上具有用于固定多个导向叶片的凹槽。对于可固定到密封环段的每个导向叶片，密封环段具有通过恢复力作用在相应导向叶片上的至少一个压力螺栓，所述压力螺栓能够被固定并且相应地由相应的在密封环段中开口并且被构造成可以沿轴向压缩的圆柱形元件，并且其中相应的压力螺栓具有盘形弹簧，并且相应的压力螺栓的恢复力相对于径向方向作用在径向方向上设置密封环段的涡轮机的旋转轴线。

49. 发明申请

US20160201512A1 GAS TURBINE ENGINE MID-TURBINE FRAME TIE ROD ARRANGEMENT 审中-公开
标题翻译：气体涡轮发动机中型涡轮机框架结构安装
公开(公告)号：US20160201512A1
公开(公告)日：2016-07-14
申请号：US14593842
申请日：2015-01-09
申请人： United Technologies Corporation
发明人： Steven J. Bauer , Timothy Dale , Christina S. Liebel , Conway Chuong
IPC分类号： F01D25/24 , F01D25/26 , F01D5/02
CPC分类号： F01D25/243 , F01D5/02 , F01D9/042 , F01D9/065 , F01D25/162 , F01D25/26 , F05D2220/32 , F05D2220/3213 , F05D2230/64 , F05D2240/12 , F05D2250/314 , F05D2260/20 , F05D2260/31 , Y02T50/671 , Y02T50/675
摘要： A gas turbine engine mid-turbine frame includes inner and outer cases that are arranged about an engine axis. A radial plane is arranged normal to the engine axis. The inner and outer cases are secured to one another by a tie rod that extends along a longitudinal axis. The longitudinal axis is arranged at an acute angle relative to the radial plane.
摘要翻译：燃气涡轮发动机中涡轮机架包括围绕发动机轴线布置的内壳体和外壳体。径向平面垂直于发动机轴线设置。内壳体和外壳体通过沿着纵向轴线延伸的拉杆彼此固定。纵向轴线相对于径向平面以锐角布置。

50. 发明授权

US09388703B2 Gas turbine engine having a gap between an outlet guide vane and an inner wall surface of a diffuser 有权
标题翻译：燃气涡轮发动机在出口导向叶片和扩散器的内壁表面之间具有间隙
公开(公告)号：US09388703B2
公开(公告)日：2016-07-12
申请号：US13635892
申请日：2011-03-18
申请人： Takuya Ikeguchi , Yusuke Sakai , Koji Terauchi
发明人： Takuya Ikeguchi , Yusuke Sakai , Koji Terauchi
IPC分类号： F01D9/04 , F04D29/54 , F04D29/64 , F01D25/24
CPC分类号： F01D9/042 , F01D25/246 , F04D29/542 , F04D29/644 , F05D2220/3219 , F05D2260/36
摘要： A gas turbine engine is provided, which comprises an outlet guide vane provided downstream of a compressor; an outer casing supporting a radially outward part of the outlet guide vane; and an inner diffuser supporting a radially inward part. The outlet guide vane includes a radially inward inner flange; a projecting part projecting radially inward from the inner flange; and an engagement part protruding to one side in an axial direction of the projecting part. The inner diffuser includes a smaller-diameter part having a smaller outer diameter than the other part located upstream. The inner diffuser is provided with an engagement groove extending to one side in the axial direction from an outer peripheral surface of the smaller-diameter part or a region in the vicinity thereof. The engagement part is inserted into the engagement groove with a gap between the engagement part and groove.
摘要翻译：提供一种燃气涡轮发动机，其包括设置在压缩机下游的出口导向叶片; 外壳，其支撑出口引导叶片的径向向外部分; 以及支撑径向向内部分的内部扩散器。出口导向叶片包括径向向内的内凸缘; 从所述内凸缘径向向内突出的突出部; 以及沿突出部的轴向突出到一侧的接合部。内部扩散器包括具有比位于上游的另一部分更小的外径的较小直径部分。内部扩散器设置有从小直径部分的外周面或其附近的区域沿轴向一侧延伸的接合槽。接合部分在接合部分和槽之间具有间隙地插入到接合槽中。

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