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21. 发明申请

WO2013163032A1 GAS TURBINE ENGINE AIRFOIL GEOMETRIES AND CORES FOR MANUFACTURING PROCESS 审中-公开
标题翻译：气体涡轮发动机气动几何和制造工艺的方法
公开(公告)号：WO2013163032A1
公开(公告)日：2013-10-31
申请号：PCT/US2013/037356
申请日：2013-04-19
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： PROPHETER-HINCKLEY, Tracy A. , ZELESKY, Mark F. , MONGILLO, JR., Dominic J. , DEVORE, Matthew A. , GAUTSCHI, Steven Bruce , FISK, Benjamin T.
IPC分类号： F01D5/12 , F01D5/18 , F01D9/00 , F02C7/12
CPC分类号： F01D5/187 , B22C9/10 , B22C9/101 , B22C9/24 , B22F3/1055 , B22F5/10 , B33Y10/00 , B33Y80/00 , C22C28/00 , F05D2220/32 , F05D2230/21 , F05D2230/31 , F05D2260/20 , F05D2300/131 , Y02P10/292 , Y02P10/295
摘要： A core for an airfoil includes a refractory metal structure having a variable thickness. An airfoil includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness, and the second thickness is less than 0.060 inch (1.52 mm). A method of manufacturing a refractory metal core includes depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of a refractory metal core, and producing the core having a variable thickness.
摘要翻译：用于翼型的芯包括具有可变厚度的难熔金属结构。机翼包括主体，其主体和后缘通过间隔开的压力和抽吸侧面连接，以提供由周边壁限定的外部翼面。内壁布置在周边壁的内部和附近，以在其间提供冷却通道。具有第一和第二部分的冷却通道是锥形的并且分别具有第一和第二厚度。第一厚度大于第二厚度，第二厚度小于0.060英寸（1.52mm）。一种制造难熔金属芯的方法包括将多层粉末金属沉积在彼此上，参考与难熔金属芯的特定横截面相关的CAD数据将层相互连接，并且制造具有可变的厚度。

22. 发明申请

WO2013162900A1 AIRFOIL INCLUDING MEMBER CONNECTED BY ARTICULATED JOINT 审中-公开
标题翻译：包括连接在一起的会员的航空器
公开(公告)号：WO2013162900A1
公开(公告)日：2013-10-31
申请号：PCT/US2013/036103
申请日：2013-04-11
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： PROPHETER-HINCKLEY, Tracy A. , TRACY, Anita L.
IPC分类号： F01D5/00 , F01D9/00 , F01C7/00 , F01K3/00 , F01D25/00
CPC分类号： F01D5/22 , B22F3/1055 , B22F5/04 , B22F7/08 , F01D5/26 , Y02P10/295 , Y10T29/49316
摘要： An airfoil includes a body that has a platform, an airfoil extending outwardly from a side of the platform and a root extending outwardly from another side of the platform. A member is connected in an articulated joint to the body.
摘要翻译：翼型件包括具有平台的主体，从平台侧向外延伸的翼型件和从平台的另一侧向外延伸的根部。一个构件连接在一个铰接的关节到身体。

23. 发明申请

WO2015112891A1 ADDITIVE MANUFACTURING PROCESS GROWN INTEGRATED TORSIONAL DAMPER MECHANISM IN GAS TURBINE ENGINE BLADE 审中-公开
标题翻译：添加剂制造工艺在气体涡轮发动机叶片中形成集成的扭转阻尼器机构
公开(公告)号：WO2015112891A1
公开(公告)日：2015-07-30
申请号：PCT/US2015/012737
申请日：2015-01-23
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： TWELVES, JR., Wendell V. , PROPHETER-HINCKLEY, Tracy A. , CABRILA, Pauline
IPC分类号： F01D5/16 , F01D5/26
CPC分类号： F04D29/668 , B22F3/1055 , B22F5/04 , B22F7/06 , F01D5/16 , F04D29/325 , F04D29/388 , F05B2220/302 , F05B2230/31 , F05B2230/60 , F05D2230/22 , F05D2230/30 , F05D2230/31 , Y02P10/295 , Y02T50/672
摘要： A blade is provided for a gas turbine engine. The blade includes an airfoil portion with at least one internal cavity and a damper located within the internal cavity. The damper includes a cantilever spring arm. A fan blade is provided for a gas turbine engine. The fan blade includes an airfoil portion with at least one internal cavity; and a damper located within the internal cavity. The damper includes a cantilever spring arm that terminates with a rub surface pad adjacent to a friction bridge between a concave pressure side and a convex suction side of the airfoil portion. A method is also provided for damping a blade of a gas turbine engine. The method includes deflecting a cantilever spring arm to contact a rub surface pad with a friction bridge between a concave pressure side and a convex suction side of an airfoil portion of the blade.
摘要翻译：为燃气涡轮发动机提供叶片。叶片包括具有至少一个内部空腔的翼型部分和位于内部空腔内的阻尼器。阻尼器包括悬臂弹簧臂。为燃气涡轮发动机提供风扇叶片。风扇叶片包括具有至少一个内部空腔的翼型部分; 和位于内腔内的阻尼器。阻尼器包括悬臂弹簧臂，该悬臂弹簧臂与邻近翼型部分的凹入压力侧和凸形吸入侧之间的摩擦桥的摩擦表面垫结束。还提供了一种用于阻尼燃气涡轮发动机的叶片的方法。该方法包括使悬臂弹簧臂偏转以使摩擦表面垫与叶片的翼型部分的凹入压力侧和凸形吸入侧之间的摩擦桥接触。

24. 发明申请

WO2015020720A2 GAS TURBINE ENGINE COMPONENT WITH RIB SUPPORT 审中-公开
标题翻译：燃气轮机发动机组件与RIB支持
公开(公告)号：WO2015020720A2
公开(公告)日：2015-02-12
申请号：PCT/US2014/041222
申请日：2014-06-06
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： QUACH, San , PROPHETER-HINCKLEY, Tracy A. , DEVORE, Matthew A.
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/186 , B22C9/103 , F01D5/187 , F01D9/041 , F01D25/12 , F02C3/04 , F04D29/324 , F05D2220/32 , F05D2230/211 , F05D2240/12 , F05D2240/125 , F05D2240/30 , F05D2240/307 , F05D2240/35 , F05D2260/202 , F05D2260/22141
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a first sidewall and a second sidewall joined together at a leading edge and a trailing edge and extending from a base to a tip. A plenum is defined inside the airfoil. A first cooling cavity merges into the plenum and a second cooling cavity merges into the plenum. A rib extends from at least one of the first sidewall and the second sidewall at least partially into the plenum to separate the first cooling cavity from the second cooling cavity.
摘要翻译：除了别的之外，根据本公开的示例性方面的部件包括翼型件，该翼型件包括在前缘和后缘处结合在一起的第一侧壁和第二侧壁并且从第一侧壁和第二侧壁延伸，基地到小费。机翼内部形成一个充气室。第一冷却腔合并入气室并且第二冷却腔合并入气室。肋从第一侧壁和第二侧壁中的至少一个至少部分地延伸到充气室中以将第一冷却腔与第二冷却腔分开。

25. 发明申请

WO2014113039A1 VARIABLE AREA VANE ARRANGEMENT FOR A TURBINE ENGINE 审中-公开
标题翻译：涡轮发动机的可变区域风扇装置
公开(公告)号：WO2014113039A1
公开(公告)日：2014-07-24
申请号：PCT/US2013/022411
申请日：2013-01-21
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： MCCAFFREY, Michael G. , SURACE, Raymond , PROPHETER-HINCKLEY, Tracy A.
IPC分类号： F01D17/16
CPC分类号： F01D17/162 , F01D5/145 , F01D5/187
摘要： An adjustable stator vane for a turbine engine includes a shaft, a flange and a stator vane body that pivots about a variable vane axis. The stator vane body extends axially between a first end and a second end. The stator vane body includes an airfoil, a cavity, and a body surface located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially around the inlet and the shaft, and radially from the stator vane body.
摘要翻译：用于涡轮发动机的可调节定子叶片包括轴，凸缘和绕可变叶片轴线枢转的定子叶片体。定子叶片体在第一端和第二端之间轴向延伸。定子叶片主体包括翼型件，空腔和位于第一端的主体表面。空腔从体表中的入口轴向延伸到翼型中。轴从第一端沿着可变叶片轴线延伸。凸缘围绕入口和轴周向延伸，并且从定子叶片体径向延伸。

26. 发明申请

WO2014112968A1 GAS TURBINE ENGINE COMPONENT HAVING TRANSVERSELY ANGLED IMPINGEMENT RIBS 审中-公开
标题翻译：气动涡轮发动机组件具有横向旋转轴承RIBS
公开(公告)号：WO2014112968A1
公开(公告)日：2014-07-24
申请号：PCT/US2013/021509
申请日：2013-01-15
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： PROPHETER-HINCKLEY, Tracy A. , QUACH, San , DEVORE, Matthew A.
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , B22D30/00 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2230/21 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , F23R3/002
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion that includes a first wall spaced apart from a second wall and disposed about a centerline axis. At least one rib extends between the first wall and the second wall. The at least one rib extends along a rib axis that is transversely angled relative to the centerline axis. At least one impingement hole extends through the at least one rib.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件包括主体部分，其包括与第二壁间隔开并围绕中心线轴线设置的第一壁。至少一个肋在第一壁和第二壁之间延伸。至少一个肋沿着相对于中心线轴线横向成角度的肋轴线延伸。至少一个冲击孔延伸穿过至少一个肋。

27. 发明申请

WO2014018138A3 AIRFOIL COOLING CIRCUITS 审中-公开
标题翻译：机翼冷却回路
公开(公告)号：WO2014018138A3
公开(公告)日：2014-01-30
申请号：PCT/US2013/037302
申请日：2013-04-19
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： HUDSON, Eric A. , PROPHETER-HINCKLEY, Tracy A. , QUACH, San , DEVORE, Matthew A.
IPC分类号： F01D5/18 , F01D5/14 , F02C7/00
摘要： An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.
摘要翻译：
翼型包括前缘和后缘; 第一和第二侧面，从所述前缘延伸到所述后缘，每个侧面具有外表面; 位于第一和第二侧以及前缘和后缘之间的芯部通道; 以及位于核心通道和第一侧的外表面之间的壁结构。壁结构包括多个与芯通道连通的冷却流体入口，用于接收来自芯通道的冷却流体，在第一侧的外表面上的多个冷却流体出口，用于排出冷却流体并沿着外部形成冷却膜所述第一侧的表面以及与所述多个冷却流体入口和所述多个冷却流体出口连通的多个冷却通道。一个冷却通道的至少一部分在相邻冷却流体出口之间延伸。

28. 发明申请

WO2014011289A2 AIRFOIL HAVING MINIMUM DISTANCE RIBS 审中-公开
标题翻译：具有最小距离RIBS的AIRFOIL
公开(公告)号：WO2014011289A2
公开(公告)日：2014-01-16
申请号：PCT/US2013/036510
申请日：2013-04-14
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FISK, Benjamin T. , PROPHETER-HINCKLEY, Tracy A. , DOLANSKY, Gregory M. , TRACY, Anita L. , TAFFET, Steven
CPC分类号： F01D5/147 , B23P15/02 , F01D5/187 , F05D2260/22141 , Y10T29/49336
摘要： An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall to define a camber line there between. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. Multiple ribs extend longitudinally in the cavity and are laterally spaced apart from each other relative to the longitudinal axis. In at least one plane that is perpendicular to the longitudinal axis, each of the ribs connects the first side wall and the second side wall along respective minimum distance directions that are perpendicular to the camber line. At least two of the respective minimum distance directions are non-parallel.
摘要翻译：翼型件包括限定纵向轴线的翼型件。翼型本体包括前缘和后缘以及与第一侧壁间隔开的第一侧壁和第二侧壁，以在其间限定弧形线。第一侧壁和第二侧壁连接前缘和后缘，并且在翼型体中至少部分地限定空腔。多个肋在空腔中纵向延伸并且相对于纵向轴线彼此横向间隔开。在垂直于纵向轴线的至少一个平面中，每个肋条沿垂直于弯度线的相应的最小距离方向连接第一侧壁和第二侧壁。各个最小距离方向中的至少两个是不平行的。

29. 发明申请

WO2013163048A1 AIRFOIL WITH POWDER DAMPER 审中-公开
标题翻译： AIRFOIL与粉末阻尼器
公开(公告)号：WO2013163048A1
公开(公告)日：2013-10-31
申请号：PCT/US2013/037500
申请日：2013-04-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FISK, Benjamin T. , PROPHETER-HINCKLEY, Tracy A. , DOLANSKY, Gregory M. , TREEN, Robert J.
IPC分类号： F01D5/12 , F01D5/18 , F01D9/00 , F02C7/00 , F02C7/12 , F02K3/00
CPC分类号： F01D5/16 , F01D5/26 , F01D25/06 , Y10T29/49316
摘要： An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define at least one longitudinally elongated cavity in the airfoil body. A plurality of loose particles is enclosed in the at least one longitudinally elongated cavity.
摘要翻译：翼型件包括限定纵向轴线的翼型件。翼型体包括前缘和后缘以及与第一侧壁间隔开的第一侧壁和第二侧壁。第一侧壁和第二侧壁连接前缘和后缘，并且至少部分地限定翼型本体中的至少一个纵向细长的空腔。多个松散颗粒被封闭在至少一个纵向细长的空腔中。

30. 发明申请

WO2013163037A1 GAS TURBINE ENGINE AIRFOIL IMPINGEMENT COOLING 审中-公开
标题翻译：气体涡轮发动机空气压缩机冷却
公开(公告)号：WO2013163037A1
公开(公告)日：2013-10-31
申请号：PCT/US2013/037387
申请日：2013-04-19
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： PROPHETER-HINCKLEY, Tracy A. , ZELESKY, Mark F. , MONGILLO, JR., Dominic J. , DEVORE, Matthew A. , GAUTSCHI, Steven Bruce , FISK, Benjamin T.
IPC分类号： F01D5/12 , F01D5/18 , F01D9/00 , F02C7/12
CPC分类号： B22C9/04 , B22C9/10 , B22C9/24 , B22F3/1017 , B22F3/105 , B22F3/1055 , B22F5/04 , B23K15/0086 , B33Y10/00 , B33Y80/00 , C21D9/0068 , F01D5/187 , F05D2240/303 , F05D2260/201 , F05D2260/202 , F05D2260/205 , Y02P10/292 , Y02P10/295
摘要： An airfoil has a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A leading edge wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the leading edge wall to provide an impingement cavity between the leading edge wall and the impingement wall and multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil, and producing the airfoil.
摘要翻译：机翼具有主体，其包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。前缘壁在前缘提供外部翼型表面。冲击壁与前缘壁一体地形成，以在前缘壁和冲击壁之间提供冲击腔，并且多个冲击孔设置在冲击壁中。撞击孔横向穿过冲击壁。一种制造翼型件的方法包括以下步骤：将多层粉末金属沉积到彼此上，参考与翼型的特定横截面相关的CAD数据并将翼片相互连接，并产生翼型件。

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