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91. 发明授权

EP2395129B1 Ceramic coating arrangement and corresponding manufacturing method 有权转让
标题翻译：陶瓷涂层组件及制造方法
公开(公告)号：EP2395129B1
公开(公告)日：2015-02-11
申请号：EP11250419.6
申请日：2011-04-01
申请人： United Technologies Corporation
发明人： Lutjen, Paul M. , Strock, Christopher W.
IPC分类号： C23C28/04 , C23C4/02 , F01D11/12
CPC分类号： F01D11/122 , B21K23/00 , C23C4/02 , C23C28/3215 , C23C28/3455 , F05D2230/30 , F05D2230/90 , F05D2240/11 , F05D2260/94 , F05D2260/941 , F05D2260/95 , Y10T29/49986 , Y10T428/12389 , Y10T428/12451 , Y10T428/12611 , Y10T428/12618 , Y10T428/2462 , Y10T428/24917 , Y10T428/24926

92. 发明公开

EP2388434A3 Gas turbine engine compressor components comprising thermal barriers and method of using the same 审中-公开
标题翻译：燃气涡轮发动机压缩机部件与热应计及其使用方法
公开(公告)号：EP2388434A3
公开(公告)日：2014-12-24
申请号：EP11166226.8
申请日：2011-05-16
申请人： General Electric Company
发明人： Konitzer, Douglas Gerard , Huron, Eric Scott , Hazel, Brian Thomas
IPC分类号： F01D5/06
CPC分类号： F01D5/06 , F05C2201/0463 , F05C2201/0466 , F05D2230/90 , F05D2260/95 , F05D2300/11 , F05D2300/611 , Y02T50/67
摘要： Gas turbine engine compressor disk (10, 12) having a hot flowpath side (16); a shaft (14) having a first surface (13) positioned in the hot flowpath side (16); and a thermal barrier (20) applied to at least the first surface (13) of the shaft (14) wherein the thermal barrier is operable to maintain the temperature of the shaft below about 700°C (1300°F) when the hot flowpath side experiences a service operating temperature of from about 700°C (1300°F) to about 788°C (1450°F).

93. 发明授权

EP1916388B1 Vane with enhanced heat transfer 有权转让
标题翻译：与增加的传热刀片
公开(公告)号：EP1916388B1
公开(公告)日：2014-12-24
申请号：EP07253212.0
申请日：2007-08-15
申请人： United Technologies Corporation
发明人： Chon, Young H.
IPC分类号： F01D5/18 , F01D5/28 , F01D9/04
CPC分类号： F01D5/185 , F01D5/288 , F01D9/041 , F05D2230/80 , F05D2230/90 , F05D2240/123 , F05D2240/124 , F05D2240/129 , F05D2260/20 , Y02T50/673 , Y02T50/676

94. 发明公开

EP2812538A1 ELECTROFORMED SHEATH 有权转让
标题翻译：电动形表壳
公开(公告)号：EP2812538A1
公开(公告)日：2014-12-17
申请号：EP13746743.7
申请日：2013-02-06
申请人： United Technologies Corporation
发明人： PARKOS, JR., Joseph , HANSEN, James O. , HERTEL, Christopher A. , MURPHY, Andrew J. , PHILLIPS, Ashley P. , ABRAHAM, Jay T.
IPC分类号： F01D5/14 , F01D25/00 , F02C7/00
CPC分类号： C25D1/00 , C25D1/02 , F01D5/147 , F04D29/324 , F05D2230/30 , F05D2230/90 , F05D2240/303 , F05D2300/603
摘要： An electroformed sheath for protecting an airfoil includes a sheath body and a mandrel insert is provided. The sheath body includes a leading edge. The sheath body includes a pressure side wall and an opposed suction side wall, which side walls meet at the leading edge and extend away from the leading edge to define a cavity between the side walls. The sheath body includes a head section between the leading edge and the cavity. The mandrel insert is positioned between the pressure side and suction side walls, and includes a generally wedge-shaped geometry. A method for protecting an airfoil includes: 1) securing a mandrel insert to a mandrel; 2) electroplating a sheath body onto the mandrel and the mandrel insert; 3) removing the mandrel from the sheath body so that a sheath cavity is defined within the sheath body; and 4) securing the airfoil within the sheath cavity.

95. 发明公开

EP2770082A3 Method of protecting a surface 有权
标题翻译：一种用于保护表面的方法
公开(公告)号：EP2770082A3
公开(公告)日：2014-11-26
申请号：EP14156134.0
申请日：2014-02-21
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Saint-Jacques, Philippe
IPC分类号： C23C4/02 , C23C4/18 , F01D5/18 , F01D5/28
CPC分类号： B05D1/322 , C23C4/02 , C23C4/18 , F01D5/288 , F05D2230/90
摘要： A method of masking part of a surface (21) of a wall of a gas turbine component (20) including at least one area (24) having cooling holes (22) defined therein, the method including applying a viscous curable masking compound (28) to the part of the surface (21) over an entirety of each of the at least one area (24), including blocking access to the cooling holes (22) from the surface by applying the masking compound (28) over the cooling holes (22) without completely filling the cooling holes (22) with the masking compound (28), and forming a respective solid masking element completely covering each of the at least one area (24) and the cooling holes (22) defined therein by curing the masking compound (28).

96. 发明授权

EP2024607B1 COATED TURBINE COMPONENT AND METHOD OF COATING A TURBINE COMPONENT 有权转让
标题翻译： COATED涡轮部件和方法涂料此类组件的
公开(公告)号：EP2024607B1
公开(公告)日：2014-10-15
申请号：EP06761985.8
申请日：2006-06-08
申请人： Siemens Aktiengesellschaft
发明人： BOX, Paul , WHITEHURST, Mick
IPC分类号： F01D5/28
CPC分类号： F01D5/288 , C23C4/134 , C23C28/021 , C23C28/022 , F05D2230/90 , F05D2300/611
摘要： Turbine components with different types of coatings on different parts thereof are described. The coatings are chosen such that they are especially adapted to the thermal and corrosive conditions being present on the parts of the component during use. A method to coat a turbine component is also described.

97. 发明公开

EP2775100A2 Turbine blade cooling channel formation 有权转让
标题翻译： Turbinenschaufel-Kühlkanalbildung
公开(公告)号：EP2775100A2
公开(公告)日：2014-09-10
申请号：EP14157384.0
申请日：2014-02-28
申请人： General Electric Company
发明人： Knorr, David Bruce , Morey, Kathleen Blanche
IPC分类号： F01D5/18 , F01D5/28
CPC分类号： F01D5/183 , F01D5/147 , F01D5/186 , F01D5/187 , F01D5/286 , F01D5/288 , F05D2230/11 , F05D2230/31 , F05D2230/90 , F05D2260/204 , F05D2300/514
摘要： Embodiments of the invention relate generally to turbine blades and, more particularly, to the formation of cooling channels on a surface of a turbine blade and turbine blades including such cooling channels. In one embodiment, the invention provides a method of forming a cooling channel along a surface (10) of a turbine blade, the method comprising: applying a first mask material (30) to a first portion (12) of a surface (10) of a turbine blade; forming a first barrier (40) layer atop the first mask material (30) and atop a second portion (14) of the surface (10) of the turbine blade; removing the first mask material (30) and the barrier layer (40) atop the first mask material (30) to expose the first portion (12) of the surface (10) of the turbine blade; and etching the first portion (12) of the surface (10) of the turbine blade to form a cooling channel (20) along the surface (10) of the turbine blade.
摘要翻译：本发明的实施例大体上涉及涡轮机叶片，更具体地涉及在涡轮机叶片的表面上形成冷却通道和包括这种冷却通道的涡轮机叶片。在一个实施例中，本发明提供了一种沿着涡轮叶片的表面（10）形成冷却通道的方法，所述方法包括：将第一掩模材料（30）施加到表面（10）的第一部分（12）的涡轮叶片; 在所述第一掩模材料（30）的顶部和所述涡轮叶片的所述表面（10）的第二部分（14）的顶部上形成第一阻挡层（40）在所述第一掩模材料（30）的顶部移除所述第一掩模材料（30）和所述阻挡层（40）以暴露所述涡轮叶片的所述表面（10）的所述第一部分（12）并且蚀刻涡轮机叶片的表面（10）的第一部分（12）以沿涡轮叶片的表面（10）形成冷却通道（20）。

98. 发明公开

EP2770082A2 Method of protecting a surface 有权
标题翻译：保护表面的方法
公开(公告)号：EP2770082A2
公开(公告)日：2014-08-27
申请号：EP14156134.0
申请日：2014-02-21
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Saint-Jacques, Philippe
IPC分类号： C23C4/02 , C23C4/18 , F01D5/18 , F01D5/28
CPC分类号： B05D1/322 , C23C4/02 , C23C4/18 , F01D5/288 , F05D2230/90
摘要： A method of masking part of a surface (21) of a wall of a gas turbine component (20) including at least one area (24) having cooling holes (22) defined therein, the method including applying a viscous curable masking compound (28) to the part of the surface (21) over an entirety of each of the at least one area (24), including blocking access to the cooling holes (22) from the surface by applying the masking compound (28) over the cooling holes (22) without completely filling the cooling holes (22) with the masking compound (28), and forming a respective solid masking element completely covering each of the at least one area (24) and the cooling holes (22) defined therein by curing the masking compound (28).
摘要翻译：一种掩蔽包括至少一个区域（24）的燃气涡轮机部件（20）的壁的表面（21）的一部分的方法，所述区域具有限定在其中的冷却孔（22），所述方法包括将粘性可固化掩蔽化合物）在所述至少一个区域（24）中的每一个的整个区域上施加到所述表面（21）的所述部分上，包括通过将所述掩蔽化合物（28）施加到所述冷却孔（22）中，而不用掩模化合物（28）完全填充冷却孔（22），并且通过固化完全覆盖在其中限定的至少一个区域（24）和冷却孔（22）中的每一个来形成相应的固体掩模元件掩蔽化合物（28）。

99. 发明公开

EP1757786A3 Variable-throat exhaust turbocharger and method for manufacturing constituent members of variable throat mechanism 有权
标题翻译：涡轮增压器具有可调节的入口和用于制造零件，其调节机构的方法
公开(公告)号：EP1757786A3
公开(公告)日：2014-08-13
申请号：EP06119587.1
申请日：2006-08-25
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Hayashi, Noriyuki c/o Mitsubishi Heavy Industries, Ltd. , Ibaraki, Seiichi c/o Mitsubishi Heavy Industries, Ltd. , Jinnai, Yasuaki c/o Mitsubishi Heavy Industries, Ltd.
IPC分类号： F02C6/12 , F01D17/16
CPC分类号： F01D17/165 , F05D2220/40 , F05D2230/211 , F05D2230/313 , F05D2230/314 , F05D2230/90 , Y10T29/4932
摘要： A variable-throat exhaust turbocharger can be provided, in which is used a means to reduce wear of the contact surfaces of the connection pin parts (10) which are formed integral with the lever plates (1) or the drive ring (3) and the grooves (3y) into which the connection pin parts (10) are engaged, and which has a means to prevent slipping out of the drive ring (3) from the nozzle mount (5) toward the lever plate (1) to prevent probable occurrence of fail in action of the variable nozzle mechanism (100) caused by the slipping out of the drive ring (3) is provided by the invention. In the invention, the connection pin parts (10) to make connection between the lever plates (1) and drive ring (3) of the variable throat mechanism are formed integral with either the lever plates (1) or the drive ring (3) by extrusion or by precision casting, and at least the connection pin parts (10) or grooves (3y) into each of which each of the connection pin parts (10) is engaged are treated with surface hardening including diffusion coating.

100. 发明授权

EP2537635B1 Component with cooling channels and method of manufacture 有权转让
标题翻译：部件具有冷却通道和制造过程
公开(公告)号：EP2537635B1
公开(公告)日：2014-04-30
申请号：EP12172765.5
申请日：2012-06-20
申请人： GENERAL ELECTRIC COMPANY
发明人： Bunker, Ronald Scott
IPC分类号： B24C1/04 , B23P15/04 , C23C4/00 , F01D5/18
CPC分类号： B24C1/045 , B23K26/364 , B23K26/389 , B23K2201/001 , F01D5/186 , F05D2230/14 , F05D2230/90 , Y02T50/672 , Y02T50/676

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