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31. 发明授权

EP2673472B1 ENSEMBLE PALE-PLATEFORME POUR ECOULEMENT SUBSONIQUE 有权
标题翻译：刀片平台安排在声音CURRENTS
公开(公告)号：EP2673472B1
公开(公告)日：2015-10-28
申请号：EP12707870.7
申请日：2012-02-06
申请人： SNECMA
发明人： CELLIER, Damien , PERROT, Vincent, Paul, Gabriel , RIOS, Jean-François
IPC分类号： F01D5/14 , F04D29/32
CPC分类号： F01D5/02 , F01D5/143 , F01D5/145 , F04D29/321 , F04D29/329 , F04D29/522 , F05D2240/301 , F05D2240/80 , F05D2250/711 , F05D2250/713 , Y02T50/673

32. 发明公开

EP2880280A1 AIRFOIL DESIGN HAVING LOCALIZED SUCTION SIDE CURVATURES 有权转让
标题翻译：新浪拥有多家地区SIDESAUGKRÜMMUNGEN涡轮叶片造型
公开(公告)号：EP2880280A1
公开(公告)日：2015-06-10
申请号：EP13826145.8
申请日：2013-08-02
申请人： United Technologies Corporation
发明人： AGGARWALA, Andrew S. , ALLEN-BRADLEY, Eunice , GROVER, Eric A. , TRINDADE, Ricardo
IPC分类号： F02C7/00 , F01D5/00
CPC分类号： F01D5/141 , F01D5/145 , F01D5/148 , F01D5/186 , F05D2240/124 , F05D2250/713
摘要： An airfoil for a gas turbine engine comprises a radially extending body having a transverse cross-section. The transverse cross-section comprises a leading edge, a trailing edge, a pressure side and a suction side. The pressure side extends between the leading edge and the trailing edge with a predominantly concave curvature. The suction side extends between the leading edge and the trailing edge with a predominantly convex curvature. The suction side includes an approximately flat portion flanked by forward and aft convex portions. In another embodiment, the suction side includes a series of local curvature changes that produce inflection points in the convex curvature of the suction side spaced from the trailing edge.

33. 发明公开

EP2880277A1 REFLEX ANNULAR VENT NOZZLE 有权转让
标题翻译：反射环形通风喷嘴
公开(公告)号：EP2880277A1
公开(公告)日：2015-06-10
申请号：EP13825191.3
申请日：2013-07-19
申请人： United Technologies Corporation
发明人： KHAN, Wasif
IPC分类号： F02C7/00 , F02C3/00 , F02C9/00
CPC分类号： F02K1/28 , F02K3/075 , F05D2250/323 , F05D2250/713 , F05D2260/4031 , F05D2260/605
摘要： A gas turbine engine includes a core defining an engine central longitudinal axis. An inner-fixed structure is radially outward of the core. A core cowl extends from the inner-fixed structure to a trailing edge. A thrust reverser is spaced radially outward of the core cowl to define a fan flow path. A vent has a core cowl inner surface formed as part of the core cowl and a vent inner surface that is spaced radially inward of the core cowl inner surface to define a vent flow path. A reflex member extends from a trailing edge of the core nacelle to impede mixing of the fan flow path and the vent flow path.
摘要翻译：燃气涡轮发动机包括限定发动机中心纵向轴线的核心。内固定结构在芯的径向外侧。核心整流罩从内部固定结构延伸到后缘。推力反向器在核心罩的径向外侧间隔开以限定风扇流动路径。通风口具有形成为核心罩的一部分的核心罩整体内表面和与核心罩内表面径向向内间隔开以限定排放流动路径的通风口内表面。反射构件从核心机舱的后缘延伸以阻止风扇流路和排气流路径的混合。

34. 发明公开

EP2868894A1 Variable geometry turbo system 审中-公开
标题翻译： Turbosystem mit variabler Geometrie
公开(公告)号：EP2868894A1
公开(公告)日：2015-05-06
申请号：EP14172947.5
申请日：2014-06-18
申请人： Hyundai Motor Company , Hyundai Wia Corporation
发明人： Jung, Kyung-Jae , Lee, Seung Yeon , Kim, Kwang Hwan , Lee, Gil-Beom , Park, Jun Gwan , Yang, Sung-Jin , Park, Ui Yeon , Jin, Kyung-Wook
IPC分类号： F02B37/24 , F01D17/16 , F01D5/14 , F02C6/12 , F04D25/04
CPC分类号： F01D17/165 , F01D5/146 , F02B37/24 , F05D2220/40 , F05D2230/53 , F05D2250/713 , Y02T10/144
摘要： A variable geometry turbo system that controls a flow of exhaust gas introduced into a turbine of a turbo charger may include a vane base ring in which the turbine may be positioned at a center thereof, a fixed vane which may be fixed onto a first surface of the vane base ring to guide the exhaust gas introduced into the turbine, a variable vane which may be pivotally positioned on the first surface of the vane base ring and adjacent to the fixed vane so as to vary a flow path of the exhaust gas introduced into the turbine, a vane cover ring fixed to the vane base ring with the fixed vane and the variable vane interposed therebetween, and an actuating module coupled to the variable vane and selectively actuating the variable vane.
摘要翻译：控制引入到涡轮增压器的涡轮机中的废气流的可变几何涡轮系统可以包括：叶片基座环，其中涡轮机可以位于其中心，固定叶片可固定在第一表面上用于引导引入到涡轮机中的废气的叶片基环，可变叶片，其可以枢转地定位在叶片基座环的第一表面上并且与固定叶片相邻，以便改变引入的废气的流动路径涡轮机，固定到叶片基座环上的叶片盖环，固定叶片和可变叶片插入其间;以及致动模块，其联接到可变叶片并选择性地致动可变叶片。

35. 发明公开

EP2855847A1 AUBE DE SOUFFLANTE POUR TURBOREACTEUR D'AVION A PROFIL CAMBRE EN SECTIONS DE PIED 有权转让
标题翻译： LÜFTERSCHAUFELFÜREIN STRAHLTRIEBWERK EINES FLUGZEUGS MITGEWÖLBTEMPROFIL IN DEN FUSSABSCHNITTEN
公开(公告)号：EP2855847A1
公开(公告)日：2015-04-08
申请号：EP13728469.1
申请日：2013-05-23
申请人： SNECMA
发明人： REISS, Hanna , BISCAY, Adrien , FAYARD, Benoît , JABLONSKI, Laurent , MERLOT, Damien
IPC分类号： F01D5/14 , F04D29/32 , F04D29/66
CPC分类号： F04D29/384 , F01D5/141 , F04D19/002 , F04D29/324 , F04D29/388 , F04D29/666 , F05D2220/36 , F05D2250/713 , F05D2260/961 , Y02T50/671 , Y02T50/673
摘要： The invention concerns a fan blade (4) for a turbojet of an aircraft, comprising a blade (6) that extends axially between a leading edge (18) and a trailing edge (20) and comprising a plurality of blade sections (S) stacked radially between a foot section (S
pied ) and a head section (Stête). All the blade sections comprised between the foot section (Spied) and a blade section (S30) positioned at a radial height corresponding to 30% of the total radial height of the blade have a skeleton curve having an inflection point.
摘要翻译：一种用于飞机涡轮喷气发动机的风扇叶片，所述叶片包括在前缘和后缘之间轴向延伸的翼型件，并且包括径向地堆叠在根部和尖端部分之间的多个翼型段。位于根部和位于对应于翼型件的总径向高度的30％的径向高度处的翼型部分的所有翼型部分具有具有拐点的骨架曲线。

36. 发明授权

EP2245275B1 LEITSCHAUFEL EINER VARIABLEN TURBINENGEOMETRIE EINES TURBOLADERS 有权转让
标题翻译：涡轮增压器的可变几何涡轮的叶片
公开(公告)号：EP2245275B1
公开(公告)日：2015-04-08
申请号：EP08869779.2
申请日：2008-10-28
申请人： Continental Automotive GmbH
发明人： BÖNING, Ralf , DETTMANN, Tobias , FÄTH, Holger , KAUFMANN, Andre
IPC分类号： F01D17/16 , F01D9/02 , F01D5/14
CPC分类号： F01D17/165 , F01D5/141 , F01D9/026 , F01D17/162 , F05D2220/40 , F05D2250/713

37. 发明公开

EP2365187A3 Turbine blade comprising a cooled platform 审中-公开
标题翻译：具有冷却平台的涡轮叶片
公开(公告)号：EP2365187A3
公开(公告)日：2013-05-22
申请号：EP11157347.3
申请日：2011-03-08
申请人： General Electric Company
发明人： Lacy, Benjamin Paul , Itzel, Gary Michael , Wei, Bin
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D5/187 , F05D2230/11 , F05D2230/12 , F05D2240/81 , F05D2250/184 , F05D2250/71 , F05D2250/713 , F05D2260/22141 , Y02T50/67 , Y02T50/676
摘要： The present subject matter discloses a turbine component (10) including a platform (14) and an airfoil (12) extending radially upward from the platform (14). A plurality of curved cooling passages (56) may be defined in the platform (14). Each of the curved cooling passages (56) may have at least one end disposed at an exterior surface of the platform (14). Additionally, each of the cooling passages (56) may be configured to direct a cooling medium through the platform (14).

38. 发明公开

EP2505783A2 Rotor einer Axialverdichterstufe einer Turbomaschine 有权
标题翻译：转子叶轮Axialverdichterstufe einer Turbomaschine
公开(公告)号：EP2505783A2
公开(公告)日：2012-10-03
申请号：EP12161401.0
申请日：2012-03-27
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Heinichen, Frank , Johann, Erik
IPC分类号： F01D5/14 , F01D5/34
CPC分类号： F01D5/143 , F01D5/10 , F01D5/34 , F05D2240/80 , F05D2250/711 , F05D2250/713 , F05D2250/73 , F05D2260/96 , Y02T50/671 , Y02T50/673
摘要： Die Erfindung betrifft einen Rotor einer Axialverdichterstufe einer Turbomaschine, der einen Drehkörper (7) mit einer Drehachse (20), der an seinem Umfang einen Schaufelkranz (1) mit einer radial außen liegenden Kranzoberfläche (10) ausbildet, und mehrere Laufschaufeln (2) aufweist, die an dem Schaufelkranz (1) angeordnet sind. Es ist vorgesehen, dass die Kranzoberfläche (10) zwischen zwei benachbarten Laufschaufeln (2) zumindest in einem Teilbereich sowohl in axialer Richtung (x) als auch in Umfangsrichtung (Φ) einen sich verändernden Radius (r) bezogen auf die Drehachse (20) des Drehkörpers (7) aufweist.
摘要翻译：转子具有旋转体，旋转体形成在具有径向放置的边缘表面（10）的叶片环（1）的周边。多个叶片安装在叶片环上。轮辋表面具有基于旋转体的旋转轴线的半径，其中在轴向方向（x）上的部分和圆周方向上的两个相邻刀片（2）之间的半径发生变化。

39. 发明公开

EP2434094A2 Steam turbine stator vane and steam turbine 审中-公开
标题翻译： LepschaufelfürDampfturbine und Dampfturbine
公开(公告)号：EP2434094A2
公开(公告)日：2012-03-28
申请号：EP11181062.8
申请日：2011-09-13
申请人： Hitachi Ltd.
发明人： Ono, Hideki , Murata, Kenichi , Senoo, Shigeki
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2220/31 , F05D2240/121 , F05D2240/122 , F05D2250/711 , F05D2250/713
摘要： A steam turbine stator vane (1) has a trailing edge curved line (9,10) on which an inflection point is provided when the stator vane (1) is viewed from a downstream side of flow of a working fluid in an axial direction of a steam turbine. The stator vane (1) is formed so that a projecting amount of the curved line (9,10) in a rotational direction of the moving blade (2) of the steam turbine continuously increases from a root portion of the stator vane (1) to a tip portion of the stator vane (1). The tip portion of the stator vane (1) is inclined toward the outer circumferential side of the steam turbine with respect to the flow direction (20) of the working fluid from the upstream side to downstream side of the flow of the working fluid. The root portion is inclined toward the inner circumferential side of the steam turbine with respect to the flow direction of the working fluid from the upstream side to downstream side of the flow of the working fluid.
摘要翻译：蒸汽涡轮机定子叶片（1）具有后缘曲线（9,10），当从工作流体的流动的下游侧观察定子叶片（1）时，沿轴向方向蒸汽轮机定子叶片（1）形成为使得蒸汽轮机的活动叶片（2）的旋转方向上的曲线（9,10）的突出量从定子叶片（1）的根部连续地增大，到定子叶片（1）的尖端部分。定子叶片（1）的前端部相对于工作流体的流动方向（20）从工作流体的流动的上游侧向下游侧朝向蒸汽轮机的外周侧倾斜。根部部分相对于工作流体从工作流体流动的上游侧到下游侧的流动方向朝蒸汽轮机的内周侧倾斜。

40. 发明公开

EP2365187A2 Turbine blade comprising a cooled platform 审中-公开
标题翻译： Turbinenschaufel mit einergekühltenPlattform
公开(公告)号：EP2365187A2
公开(公告)日：2011-09-14
申请号：EP11157347.3
申请日：2011-03-08
申请人： General Electric Company
发明人： Lacy, Benjamin Paul , Itzel, Gary Michael , Wei, Bin
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F01D5/187 , F05D2230/11 , F05D2230/12 , F05D2240/81 , F05D2250/184 , F05D2250/71 , F05D2250/713 , F05D2260/22141 , Y02T50/67 , Y02T50/676
摘要： The present subject matter discloses a turbine component (10) including a platform (14) and an airfoil (12) extending radially upward from the platform (14). A plurality of curved cooling passages (56) may be defined in the platform (14). Each of the curved cooling passages (56) may have at least one end disposed at an exterior surface of the platform (14). Additionally, each of the cooling passages (56) may be configured to direct a cooling medium through the platform (14).
摘要翻译：本主题公开了一种包括平台（14）和从平台（14）径向向上延伸的翼型件（12）的涡轮机部件（10）。多个弯曲的冷却通道（56）可以限定在平台（14）中。每个弯曲的冷却通道（56）可以具有设置在平台（14）的外表面处的至少一个端部。另外，每个冷却通道（56）可构造成引导冷却介质通过平台（14）。

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