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71. 发明授权

US09228451B2 Gas turbine engine module adapter to a carrier 有权
标题翻译：燃气轮机发动机模块适配器到载体
公开(公告)号：US09228451B2
公开(公告)日：2016-01-05
申请号：US13099681
申请日：2011-05-03
申请人： Gregory Reinhardt , Joseph Swiderski , Douglas Pollock , Réal Barrette , Stéphane Mongeau
发明人： Gregory Reinhardt , Joseph Swiderski , Douglas Pollock , Réal Barrette , Stéphane Mongeau
IPC分类号： B25B1/24 , F01D25/28
CPC分类号： F01D25/285 , B66C11/04 , F01D25/24 , F01D25/28 , F05D2220/30 , F05D2220/32 , F05D2220/36 , F05D2230/60 , F05D2230/68 , F05D2230/72 , F05D2240/91 , Y02T50/671 , Y10T29/49229 , Y10T29/49826
摘要： An engine mounting arrangement is provided for supporting a gas turbine engine. The mounting arrangement comprises a module adaptor mounted to an overhead or a ground based carrier for rotation about a substantially horizontal axis. The module adaptor extends horizontally from a base to an axially-opposed distal end having a first mounting interface configured for attachment to a module of the engine. The module adaptor holds the engine by the module to which it is attached and with the other engine modules projecting in a cantilever fashion from the supported module.
摘要翻译：提供用于支撑燃气涡轮发动机的发动机安装装置。安装装置包括安装到顶部或基于地面的载体上的模块适配器，用于围绕基本上水平的轴线旋转。模块适配器从基座水平延伸到具有构造成附接到发动机的模块的第一安装接口的轴向相对的远端。模块适配器通过其所连接的模块将引擎保持在发动机上，而其它发动机模块以悬臂方式从支撑的模块突出。

72. 发明申请

US20150369063A1 BLADE WHEEL AND METHOD FOR PRODUCING A BLADE THEREFOR 审中-公开
标题翻译：叶片及其制造方法
公开(公告)号：US20150369063A1
公开(公告)日：2015-12-24
申请号：US14766830
申请日：2013-10-23
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Andreas FÖHRIGEN , Enno JUNG , Christian Albrecht KOCH , Udo WEBER
IPC分类号： F01D5/30 , F01D5/12 , F01D5/32 , F01D5/02
CPC分类号： F01D5/3015 , F01D5/02 , F01D5/12 , F01D5/326 , F01D25/285 , F05D2220/30 , F05D2230/10 , F05D2230/50 , F05D2230/80 , F05D2260/821 , Y10T29/49337
摘要： A turbine blade wheel includes a wheel disk with a disk element (2) including an inlet side (3), an opposite outlet-side (4), substantially axial slots (5) distributed over the disk circumference, and vanes (6) in the slots. Each vane includes a vane root (7), an outlet-side vane root end surface (9) and an inlet-side vane root end surface (8). The vane root (7) is at the inlet side (3) of the disk element (2) for mounting in its respective slot (5). A first bearing plate (12) is provided on the outlet side (4) of the disk element. At least one pressure piece shim (13) is provided in the slot (5). A second bearing plate (14) is provided on the inlet side (3). The disk element (2) is connected to the second bearing plate (14) by a radial connecting element (16) that is pressed to act on the shim in the slot to urge the root of the vane base (7) in the slot (5) to an outermost radial position. Further a method for producing a vane using such a blade wheel is disclosed.
摘要翻译：涡轮机叶轮包括具有盘元件（2）的轮盘，盘片元件（2）包括分配在圆盘周边上的入口侧（3），相对的出口侧（4），大致轴向的槽（5）和叶片插槽。每个叶片包括叶根（7），出口侧叶根端面（9）和入口侧叶根端面（8）。叶片根部（7）位于盘元件（2）的入口侧（3），用于安装在其相应的槽（5）中。第一支承板（12）设置在盘元件的出口侧（4）上。至少一个压片垫片（13）设置在槽（5）中。在入口侧（3）上设有第二支承板（14）。盘元件（2）通过径向连接元件（16）连接到第二支承板（14），该径向连接元件（16）被按压以作用在槽中的垫片上，以将叶片基座（7）的根部推压在槽 5）到最外径位置。公开了一种使用这种叶轮制造叶片的方法。

73. 发明申请

US20150361816A1 BRUSH SEAL ASSEMBLY 有权
标题翻译： BRUSH密封组件
公开(公告)号：US20150361816A1
公开(公告)日：2015-12-17
申请号：US14742455
申请日：2015-06-17
申请人： DOOSAN HEAVY INDUSTRIES CONSTRUCTION CO., LTD.
发明人： Mahmut Faruk AKSIT
IPC分类号： F01D11/02 , F01D25/28 , F01D5/02
CPC分类号： F16J15/3288 , F01D11/001 , F05D2220/30 , F05D2220/31 , F05D2240/56
摘要： A brush seal assembly may seal a gap between a diaphragm and a rotor of a turbine. The brush seal assembly includes a brush, one end of which is inserted in a rotor facing surface of a diaphragm while the other end thereof protrudes toward a rotor, and a support strip spaced apart from one side of the brush so that one side end portion of the support strip is fixed and the other side end portion thereof supports one side of the brush.
摘要翻译：刷密封组件可以密封隔膜和涡轮机的转子之间的间隙。刷子密封组件包括刷子，其一端插入隔膜的转子面对表面，而另一端朝向转子突出，并且与刷子的一侧间隔开的支撑条，使得一侧端部的支撑条固定，另一侧端部支撑着刷的一侧。

74. 发明申请

US20150354371A1 TURBINE BLADE MACHINING METHOD, MACHINING TOOL, AND TURBINE BLADE 有权
标题翻译：涡轮叶片加工方法，加工工具和涡轮叶片
公开(公告)号：US20150354371A1
公开(公告)日：2015-12-10
申请号：US14762062
申请日：2014-02-12
申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.
发明人： Tomomi SONOO
IPC分类号： F01D5/18 , F01D5/28 , B24B19/14
CPC分类号： F01D5/186 , B23P6/002 , B23P2700/06 , B24B1/04 , B24B19/14 , C23C4/18 , F01D5/005 , F01D5/288 , F05D2220/30 , F05D2230/10 , F05D2230/311 , F05D2230/90 , F05D2260/202
摘要： Provided are a turbine blade machining method and a machining tool, which allow efficient machining of a through-hole running from the surface of a turbine blade to the interior thereof, and a turbine blade. This turbine blade machining method, whereby a through-hole is machined in a turbine blade with a protective film formed on a surface of a substrate, has: an insertion step of inserting a machining tool, including a grinding region provided at a tip thereof, into the through-hole with such an orientation that the grinding region faces the surface of the through-hole; and a removal step of grinding the protective film laminated in the through-hole with the grinding region of the machining tool inserted into the through-hole, to remove the protective film laminated in the through-hole.
摘要翻译：提供了一种涡轮机叶片加工方法和加工工具，其允许从涡轮叶片的表面到其内部的通孔的高效加工，以及涡轮叶片。这种涡轮机叶片加工方法，其中在涡轮叶片中加工有形成在基板表面上的保护膜的通孔具有：插入步骤，插入包括设置在其顶端的研磨区域的加工工具，以使研磨区域朝向通孔表面的方向进入通孔; 以及通过插入到通孔中的加工工具的研磨区域来研磨层叠在通孔中的保护膜的去除步骤，以去除层压在通孔中的保护膜。

75. 发明申请

US20150345315A1 TURBINE ENGINE GUIDE VANE ATTACHMENT ORIFICE CLOSER 有权
标题翻译：涡轮发动机指南VANE附件ORIFICE关闭
公开(公告)号：US20150345315A1
公开(公告)日：2015-12-03
申请号：US14728108
申请日：2015-06-02
申请人： SNECMA
发明人： Kaëlig Merwen ORIEUX , Thierry Georges Paul PAPIN
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F01D9/042 , F04D29/542 , F04D29/644 , F05D2220/30 , F05D2220/36 , F05D2230/60 , F05D2240/12 , F05D2260/31 , F16B21/04 , F16B37/14 , Y02T50/673
摘要： A closer for an attachment orifice of an OGV in a turbine engine, the vane having a blade fixed to a root provided with attachment orifices, the closer including a cup adapted to be fixed in the attachment orifice of an OGV; a cylindrical shaped plug engaging in the cup, the plug including an upper face inclined relative to the ground plane of the plug; a guide adapted to position the plug on the cup by rotation into a working position, in which the upper face of the plug coincides with the surface level of the vane root; a blocking system to block the plug in the working position.
摘要翻译：更靠近涡轮发动机中的OGV的附接孔，叶片具有固定到设置有附接孔的根部的叶片，更近的包括适于固定在OGV的附接孔中的杯; 接合在所述杯中的圆柱形塞，所述插头包括相对于所述插头的接地平面倾斜的上表面; 引导件，其适于将插头旋转到工作位置中将插头定位在杯子上，其中插头的上表面与叶根的表面水平重合; 阻塞系统阻塞插头的工作位置。

76. 发明申请

US20150330224A1 BALANCED ROTOR DISC, AND BALANCING METHOD 有权
标题翻译：平衡转子盘和平衡方法
公开(公告)号：US20150330224A1
公开(公告)日：2015-11-19
申请号：US14715488
申请日：2015-05-18
申请人： SNECMA
发明人： Pascal Casaliggi , Remi Bourion , Thierry Capolungo
IPC分类号： F01D5/02
CPC分类号： F01D5/027 , F01D5/02 , F04D29/662 , F05D2220/30 , F05D2240/24 , F05D2260/15 , F16F15/32 , Y02T50/671 , Y10T29/49334
摘要： The invention relates to a rotor disc (1) for a turbomachine, comprising a radial flange (2) that has a plurality of fastening holes (3), and a plurality of scallops (4) forming notches in the flange (2), and being separated by inter-scallop flange portions (7), characterized in that the flange alternatively has, in its circumferential direction: a fastening hole (3) and an inter-scallop flange portion (7) arranged in the radial extension of the fastening hole (3), and a scallop (4), in such a way that one or more of the scallops (47, 48, 49; 42, 45-47, 48-411, 414) has a volume greater than the volume of each of the other scallops (41-46, 410-414; 41, 43, 44, 412, 413), and one or more of the inter-scallop flange portions (73) has a volume less than the volume of each of the other inter-scallop flange portions (71, 72, 74), in order to balance said disc (1). The invention also relates to a turbomachine comprising that rotor disc and a method for balancing a turbomachine rotor disc.
摘要翻译：本发明涉及一种用于涡轮机的转子盘（1），其包括具有多个紧固孔（3）的径向凸缘（2）和在凸缘（2）中形成凹口的多个扇贝）由扇形扇形凸缘部分（7）分开，其特征在于，所述凸缘在其圆周方向上交替地具有紧固孔（3）和形成在所述紧固孔的径向延伸部中的扇形扇形凸缘部分（7）（3）和扇贝（4），使得一个或多个扇贝（47,48,49; 42,45-47,48-411,414）的体积大于每个扇贝的其他扇贝（41-46,410-414; 41,43,44,412,413）中的一个或多个扇形扇形凸缘部分（73）的体积小于其他扇形体的体积扇形扇形凸缘部分（71,72,74），以便平衡所述盘（1）。本发明还涉及一种涡轮机，其包括该转子盘和用于平衡涡轮机转子盘的方法。

77. 发明申请

US20150315931A1 DEVICE FOR CONNECTING A FIXED PORTION OF A TURBINE ENGINE AND A DISTRIBUTOR FOOT OF A TURBINE ENGINE TURBINE 审中-公开
标题翻译：用于连接涡轮发动机的固定部分和涡轮发动机涡轮机的分配器的装置
公开(公告)号：US20150315931A1
公开(公告)日：2015-11-05
申请号：US14503743
申请日：2014-10-01
申请人： SNECMA
发明人： Fabien GARNIER , Sebastien PRESTEL , Helene CONDAT , Patrice ROSSET , Arnaud GENILIER
IPC分类号： F01D25/14
CPC分类号： F01D25/145 , F01D9/02 , F01D11/005 , F01D25/08 , F05D2220/30 , F05D2260/231 , Y02T50/672 , Y02T50/675
摘要： A device (1) for connecting a fixed turbine engine portion (2) and a distributor (3) foot (31) of a turbine engine turbine, comprising a ring-shaped flange (111), the flange (111) being adapted so as to be connected and secured to the fixed turbine engine portion (2) and to the foot (31) of the distributor, the device being characterized in that it further comprises a ring-shaped screen (9), the screen (9) being connected and secured to the flange (111) so as to be positioned in an upstream chamber (4) made between the fixed turbine engine portion (2) and the flange (111) so as to at least partly block heat radiation from the fixed turbine engine portion (2) and directed towards the flange (111).
摘要翻译：一种用于连接涡轮发动机涡轮机的固定涡轮发动机部分（2）和分配器（3）脚部（31）的装置（1），包括环形凸缘（111），所述凸缘（111）适于被连接并固定到固定涡轮引擎部分（2）和分配器的脚部（31）上，该装置的特征在于它还包括一个环形屏幕（9），该屏幕（9）被连接并固定在凸缘111上，以便被定位在形成在固定涡轮发动机部分（2）和凸缘（111）之间的上游腔室（4）中，以便至少部分地阻挡来自固定涡轮发动机部分（2）并指向凸缘（111）。

78. 发明申请

US20150315920A1 METHOD FOR MANUFACTURING A TURBINE ENGINE BLADE ROOT OF A COMPOSITE MATERIAL AND BLADE ROOT OBTAINED BY SUCH A METHOD 有权
标题翻译：用于制造复合材料的涡轮发动机叶片的方法和通过这种方法获得的叶片根
公开(公告)号：US20150315920A1
公开(公告)日：2015-11-05
申请号：US14648762
申请日：2013-12-03
申请人： SNECMA
发明人： Hubert ILLAND
IPC分类号： F01D5/28 , F01D5/30 , B29C70/42 , F01D5/14
CPC分类号： B29D99/0025 , B29B11/16 , B29C70/24 , B29C70/42 , B29L2031/082 , D03D25/005 , F01D5/147 , F01D5/282 , F01D5/284 , F01D5/30 , F01D5/3007 , F01D5/3084 , F05D2220/30 , F05D2230/31 , F05D2240/30 , F05D2300/603 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： A method of fabricating a turbine engine blade root out of composite material including fiber reinforcement densified by a matrix, the method including making a central fiber strip and two outer fiber strips from three sets of yarn layers interlinked by three-dimensional weaving, passing the two outer strips through the central strip with the two outer strips crossing each other inside the central strip, eliminating the portions of the two outer strips lying outside the central strip by cutting them off, shaping the fiber blank in order to obtain a preform having a main portion forming a blade-root preform integral with two secondary portions forming bearing-plate preforms, and densifying the preform densified by the matrix.
摘要翻译：一种制造由包括由基体致密化的纤维增强材料的复合材料制成的涡轮发动机叶片根部的方法，该方法包括由三组织纱相互连接的三组纱线层组成中心纤维条和两条外部纤维条，外部条带穿过中央条带，其中两个外部条带在中心条带内部彼此交叉，通过切除它们而将两个外部条带的部分位于中央条带的外侧，使纤维坯料成形以获得具有主体的预成型件形成与形成支承板预成型件的两个二次部分成一体的叶根根部预成型件的部分，并且致密化由基体致密化的预制件。

79. 发明申请

US20150308279A1 ROTATING ASSEMBLY FOR A TURBOMACHINE 有权
标题翻译：旋转组件用于涡轮机
公开(公告)号：US20150308279A1
公开(公告)日：2015-10-29
申请号：US14694424
申请日：2015-04-23
申请人： SNECMA
发明人： Stephane Pierre Guillaume BLANCHARD , Youki Olivier ITO-LARDEAU
IPC分类号： F01D11/00 , F01D5/22 , F01D5/30 , F01D5/02
CPC分类号： F01D11/006 , F01D5/02 , F01D5/225 , F01D5/3015 , F01D5/3084 , F01D11/003 , F05D2220/30 , F05D2240/55 , F05D2260/231 , F05D2260/30 , Y02T50/672
摘要： A rotating assembly for a turbomachine, including a disc having an external periphery with alternating recesses and teeth, blades extending radially from the disc and the feet of which are axially engaged and radially retained in the recesses of the disc, platforms extending on the circumference from the blades and being arranged end to end on the circumference, with respect to each other, axial sealing device upstream and/or downstream of an annular zone extending radially from the platforms up to the disc. The sealing device radially includes an internal annular portion and an external annular portion structurally distinct from each other, and the external annular portion of which is elastically constrained radially inwards by the internal annular portion.
摘要翻译：一种用于涡轮机的旋转组件，包括具有交替的凹槽和齿的具有外周边的圆盘，从盘的径向延伸的叶片和其轴被轴向接合并径向地保持在盘的凹部中，在圆周上从圆周延伸的平台叶片并且在圆周上相对于彼此端对端设置在从平台径向延伸到盘的环形区域的上游和/或下游的轴向密封装置。密封装置径向地包括内部环形部分和外部环形部分，其在结构上彼此不同，并且其外部环形部分通过内部环形部分径向向内弹性地约束。

80. 发明申请

US20150292352A1 AIRCRAFT PROPULSION ASSEMBLY COMPRISING AN AIR FLOW VALVE WITH A VARIABLE FLOW RATE 有权
标题翻译：包括具有可变流量的空气流量阀的飞机推进组件
公开(公告)号：US20150292352A1
公开(公告)日：2015-10-15
申请号：US14634212
申请日：2015-02-27
申请人： Airbus Operations (S.A.S.)
发明人： Jacques Hervé Marche
IPC分类号： F01D25/12 , B64D33/08 , F01D15/02 , F01D17/00 , F01D1/02 , F01D9/02
CPC分类号： F01D25/12 , B64D33/08 , F01D1/02 , F01D9/02 , F01D15/02 , F01D17/00 , F01D17/148 , F02C6/08 , F02C7/143 , F02C7/185 , F02K3/06 , F02K3/115 , F05D2220/30 , F05D2260/213 , Y02T50/675
摘要： A propulsion assembly having a heat exchanger and a system for supplying cold air including an air inlet in a stream of air, an air duct connecting the air inlet fluidly to the exchanger, and an air flow valve with a variable flow rate inside the duct, the valve including a hub having blades projecting radially from the hub forming a helix, each blade having a root mounted rotatably on the hub, the valve comprising an electric motor to drive the hub by a motor shaft, and structure for varying pitch angle of the blades, the extremity of each blade being flush with a wall of the duct, the valve controllable to a closed configuration where pitch angle of the blades is 0° and the valve prevents passage of air, an open configuration where pitch angle is 90°, and/or a charge configuration where pitch angle is between 0° and 90°.
摘要翻译：具有热交换器和用于供应冷空气的系统的推进组件，所述冷空气包括空气流中的空气入口，将空气入口流体连接到交换器的空气管道和在管道内具有可变流量的空气流量阀，所述阀包括具有从所述毂径向突出形成螺旋形的叶片的毂，每个叶片具有可旋转地安装在所述轮毂上的根部，所述阀包括用于通过马达轴驱动所述轮毂的电动马达，以及用于改变所述桨叶角度的结构叶片的每个叶片的末端与管道的壁齐平，该阀可控制到关闭构造，其中叶片的俯仰角为0°，并且阀阻止空气通过，俯仰角为90°的打开构造，和/或俯仰角在0°和90°之间的电荷构型。

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