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91. 发明公开

EP3315787A1 THRUST RING AND ROTOR FAN SYSTEM 无效
标题翻译：推力环和转子风扇系统
公开(公告)号：EP3315787A1
公开(公告)日：2018-05-02
申请号：EP17194522.3
申请日：2017-10-03
申请人： Rolls-Royce Corporation
发明人： Power, Bronwyn , Rivers, Jonathan
IPC分类号： F04D29/32 , B64C11/00 , F01D5/14 , F01D5/22 , F02K3/04 , F02K3/072 , F02C9/58 , B64D27/00
CPC分类号： F04D29/282 , B23K2101/001 , B63H1/16 , B64C11/001 , B64C11/06 , B64C2201/162 , B64C2201/165 , B64D2027/005 , F01D5/143 , F01D5/225 , F02C9/58 , F02K3/04 , F02K3/072 , F04D29/326 , F04D29/329 , F04D29/34 , F05D2220/323 , F05D2220/326 , F05D2220/327 , F05D2220/36
摘要： A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about -5 degrees and about 45 degrees, more preferably between about 5 degrees and about 30 degrees. Optionally, an outlet guide vane may be mounted rearward of the one or more rotors having a ring airfoil.
摘要翻译：风扇系统包括具有多个叶片和环翼型件的转子，所述多个叶片可旋转地连接到轮毂和环翼型件。该风扇系统可以包括具有多个叶片和环形翼型的第二反向旋转设置的转子。第一和第二环形翼型具有弧形形状和大约-5度和大约45度之间的迎角，更优选地介于大约5度和大约30度之间。可选地，出口导向叶片可以安装在具有环形翼型的一个或多个转子的后方。

92. 发明公开

EP3309366A1 TURBINE SHROUD ASSEMBLY 有权
标题翻译：涡轮罩组件
公开(公告)号：EP3309366A1
公开(公告)日：2018-04-18
申请号：EP17194914.2
申请日：2017-10-05
申请人： Rolls-Royce Corporation
发明人： Thomas, David J. , Walston, Jeffrey A.
IPC分类号： F01D25/24
CPC分类号： F01D11/08 , F01D11/14 , F01D25/005 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2250/75 , F05D2300/6033 , Y02T50/672
摘要： A turbine shroud assembly of a gas turbine engine (10) comprises a carrier (28) and a blade track (30). The carrier (28) is arragned around at least a portion of a central axis, formes a load stage, comprises metallic materials, and includes a forward hanger (68) and an aft hanger (68). The blade track (30) comprises ceramic-containing materials, and includes a runner (36), an attachment flange (38) extending from the runner (36) for the engagement with the load stage of the carrier (28), and has an I-beam cross-sectional shape when viewed in the circumferential direction.The runner extends at least partway about a cental axis and has a flow surface (34) arranged to define a gas flow path
摘要翻译：燃气涡轮发动机（10）的涡轮护罩组件包括载架（28）和叶片轨道（30）。载体（28）绕中心轴线的至少一部分拱起，形成载荷台，包括金属材料，并且包括前部吊架（68）和后部吊架（68）。叶片轨道（30）包括含陶瓷的材料，并且包括流道（36），从流道（36）延伸的用于与载体（28）的载荷台接合的附接凸缘（38），并且具有当沿圆周方向观察时，工字梁的横截面形状。转轮至少绕中心轴线部分地延伸并且具有流动表面（34），该流动表面（34）被布置成限定气体流动路径

93. 发明授权

EP3061557B1 REPAIR OF DUAL WALLED METALLIC COMPONENTS USING DIRECTED ENERGY DEPOSITION MATERIAL ADDITION 有权
标题翻译：使用定向能量沉积材料补充修复双壁金属组件
公开(公告)号：EP3061557B1
公开(公告)日：2018-04-18
申请号：EP16157452.0
申请日：2016-02-25
申请人： Rolls-Royce Corporation
发明人： HENDERKOTT, Joseph Peter , SHUCK, Quinlan Yee
IPC分类号： B23K1/00 , B23P6/00 , F01D5/14
CPC分类号： F01D5/147 , B23K1/0018 , B23K26/342 , B23K26/38 , B23K2101/001 , B23P6/007 , F01D5/005 , F01D5/186 , F01D5/288 , F05D2220/32 , F05D2230/232 , F05D2230/233 , F05D2230/234 , F05D2230/30 , F05D2240/35 , F05D2260/202 , F05D2300/17 , F23R3/002 , F23R3/04
摘要： A technique for repairing a dual walled component comprising a spar comprising a plurality of pedestals and a coversheet attached to the plurality of pedestals may include removing a damaged portion of the coversheet from the dual walled component to expose a plurality of exposed pedestals and define a repair location and an adjacent coversheet portion. The technique also may include attaching a material to the plurality of exposed pedestals and adjacent coversheet portion using directed energy deposition material addition to form a repaired coversheet portion.

94. 发明公开

EP3296510A3 ADDITIVELY DEPOSITED GAS TURBINE ENGINE COOLING COMPONENT 审中-公开
标题翻译：附加燃气涡轮发动机冷却组件
公开(公告)号：EP3296510A3
公开(公告)日：2018-04-11
申请号：EP17186119.8
申请日：2017-08-14
申请人： Rolls-Royce Corporation
发明人： Varney, Bruce
IPC分类号： F01D5/18 , F23R3/00
CPC分类号： F01D25/12 , B23P15/04 , F01D5/182 , F01D5/186 , F01D9/041 , F05D2220/32 , F05D2230/20 , F05D2230/31 , F05D2240/12 , F05D2240/30 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/203 , F05D2260/94 , F23R3/002 , F23R3/005 , F23R3/06
摘要： An example gas turbine engine (212) component (10A,10B,10,112,12) includes a component (10A,10B,10,112,12) configured to separate a cooling air plenum (100,12,14,74) from a heated gas environment (16,76,96). The component (10A,10B,10,112,12) includes a substrate (122,130, 30B,30) defining a surface (31), and a unitary structure (112,12B,12). The unitary structure (112,12B,12) includes a cooling region (22) and a cover layer (18B,18). The cover layer (18B,18) defines a hot wall surface (20,34) configured to face the heated gas environment (16,76,96). The cooling region (22) is disposed between the cover surface (31) and the substrate (122,130,30B,30) and includes a plurality of support structures (24) extending between the cover layer (18B,18) and the surface (31) of the substrate (122,130,30B,30). At least some of the support structures (24) define a respective bond surface (32) bonded to the substrate (122,130,30B,30) at the surface (31) of the substrate (122,130,30B,30). An example technique for fabricating the gas turbine engine (212) component (10A,10B,10,112,12) includes additively depositing the unitary structure (112,12B,12) on the surface (31) of the substrate (122,130, 30B,30).
摘要翻译：示例性燃气涡轮发动机（212）部件（10A，10B，10,112,12）包括构造成将冷却空气室（100,12,14,74）与加热气体环境（16,76,96）。部件（10A，10B，10,112,12）包括限定表面（31）的基板（122,130,30B，30）和整体结构（112,12B，12）。整体结构（112,12B，12）包括冷却区域（22）和覆盖层（18B，18）。覆盖层（18B，18）限定配置成面对加热气体环境（16,76,96）的热壁表面（20,34）。冷却区域（22）设置在覆盖表面（31）和基底（122,130,30B，30）之间并且包括在覆盖层（18B，18）和表面（31）之间延伸的多个支撑结构）的衬底（122,130,30B，30）。至少一些支撑结构（24）限定了在衬底（122,130,30B，30）的表面（31）处结合到衬底（122,130,30B，30）的相应结合表面（32）。用于制造燃气涡轮发动机（212）部件（10A，10B，10,112,12）的示例性技术包括在基板（122,130,30B，30）的表面（31）上累加地沉积整体结构）。

95. 发明授权

EP2971515B1 AERODYNAMIC FAIRINGS SECONDARILY ATTACHED TO NOSECONE 有权
标题翻译：空气动力学第二次附着在NOSECONE上
公开(公告)号：EP2971515B1
公开(公告)日：2018-04-11
申请号：EP13786386.6
申请日：2013-10-24
申请人： Rolls-Royce Corporation
发明人： TOTTEN, Trevor, John , RIVERS, Jonathan, Michael , ENGEBRETSEN, Eric, William
IPC分类号： F02K3/06
CPC分类号： B64C11/14 , F01D5/066 , F02C7/04 , F02K3/06 , F05D2300/603 , Y10T29/49336 , Y10T156/10
摘要： An aerodynamic fan nosecone for a gas turbine engine is provided and includes a fan nosecone that may be made of composite material. To improve airflow transition to the blade members, aerodynamic fairings are provided and are secured to an exterior surface of the nosecone which enhances fuel economy. The fairings may be secured to the nosecone by various methods, including providing for the fairings to be changed out and replaced with other fairings on the same nosecone assembly.

96. 发明公开

EP3296510A2 ADDITIVELY DEPOSITED GAS TURBINE ENGINE COOLING COMPONENT 审中-公开
公开(公告)号：EP3296510A2
公开(公告)日：2018-03-21
申请号：EP17186119.8
申请日：2017-08-14
申请人： Rolls-Royce Corporation
发明人： Varney, Bruce
IPC分类号： F01D5/18 , F23R3/00
CPC分类号： F01D25/12 , B23P15/04 , F01D5/182 , F01D5/186 , F01D9/041 , F05D2220/32 , F05D2230/20 , F05D2230/31 , F05D2240/12 , F05D2240/30 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/203 , F05D2260/94 , F23R3/002 , F23R3/005 , F23R3/06
摘要： An example gas turbine engine (212) component (10A,10B,10,112,12) includes a component (10A,10B,10,112,12) configured to separate a cooling air plenum (100,12,14,74) from a heated gas environment (16,76,96). The component (10A,10B,10,112,12) includes a substrate (122,130, 30B,30) defining a surface (31), and a unitary structure (112,12B,12). The unitary structure (112,12B,12) includes a cooling region (22) and a cover layer (18B,18). The cover layer (18B,18) defines a hot wall surface (20,34) configured to face the heated gas environment (16,76,96). The cooling region (22) is disposed between the cover surface (31) and the substrate (122,130,30B,30) and includes a plurality of support structures (24) extending between the cover layer (18B,18) and the surface (31) of the substrate (122,130,30B,30). At least some of the support structures (24) define a respective bond surface (32) bonded to the substrate (122,130,30B,30) at the surface (31) of the substrate (122,130,30B,30). An example technique for fabricating the gas turbine engine (212) component (10A,10B,10,112,12) includes additively depositing the unitary structure (112,12B,12) on the surface (31) of the substrate (122,130, 30B,30).

97. 发明授权

EP2985366B1 COMPOSITE FAN ANNULUS FILLER WITH NANOCRYSTALLINE COATING 有权
标题翻译：具有纳米晶涂层的复合风扇环状充填物
公开(公告)号：EP2985366B1
公开(公告)日：2018-01-17
申请号：EP15180607.2
申请日：2015-08-11
申请人： Rolls-Royce Corporation
发明人： Wade, A. Vest
IPC分类号： C25D1/02 , C25D1/08 , C25D5/56 , F01D5/28 , F01D11/00
CPC分类号： F01D11/008 , C25D1/02 , C25D1/08 , C25D5/56 , F01D5/288 , F01D25/28 , F05D2220/30 , F05D2220/32 , F05D2220/3212 , F05D2220/323 , F05D2220/36 , F05D2230/20 , F05D2230/30 , F05D2230/31 , F05D2230/90 , F05D2240/24 , F05D2250/191 , F05D2300/177 , F05D2300/43 , F05D2300/611 , Y02T50/671
摘要： According to the present disclosure, an fan annulus filler for use in a fan assembly of a gas turbine engine may include an annulus filler body formed of a polymer. The annulus filler body may include a surface coated with a nanocrystalline coating to form a flow surface.

98. 发明公开

EP3263837A1 PRESSURE RECOVERY AXIAL-COMPRESSOR BLADING 有权
标题翻译：压力恢复轴向压缩机叶片
公开(公告)号：EP3263837A1
公开(公告)日：2018-01-03
申请号：EP17175176.1
申请日：2017-06-09
申请人： Rolls-Royce Corporation
发明人： Power, Bronwyn
IPC分类号： F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , F01D5/145 , F04D29/544 , F05D2250/713 , Y02T50/671 , Y02T50/673
摘要： In accordance with some embodiments of the present disclosure, a pressure recovery axial compressor blade is provided. The blade may comprise a high pressure surface and a low pressure surface connected at a leading edge and a trailing edge of the blade. Both the high and low pressure surfaces extend span wise from a first end to a second end. At least one of the high and low pressure surfaces has a finite discontinuity in curvature at an intermediate position along the chord of the blade.
摘要翻译：根据本公开的一些实施例，提供了压力恢复轴向压缩机叶片。叶片可以包括连接在叶片的前缘和后缘处的高压表面和低压表面。高压表面和低压表面都从第一端部延伸到第二端部。高压表面和低压表面中的至少一个在沿叶片翼弦的中间位置处具有有限的曲率不连续性。

99. 发明公开

EP3241753A1 OPTIONALLY HYBRID POWER SYSTEM 有权
标题翻译：可选混合动力系统
公开(公告)号：EP3241753A1
公开(公告)日：2017-11-08
申请号：EP17165977.4
申请日：2017-04-11
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc.
发明人： Armstrong, Michael , Keller, Richard
IPC分类号： B64D27/24 , B64D31/06
CPC分类号： B64D31/00 , B64D27/10 , B64D27/24 , B64D31/06 , B64D2027/026 , F02C7/32 , Y02T50/44 , Y02T50/64 , Y10S903/905 , Y10S903/93
摘要： The disclosure is directed to an "optionally hybrid power system" that may operate either as a traditional power system, deriving power from a single power source, or as a hybrid power system, deriving power from multiple types of power sources. An example optionally hybrid power system may include a gas turbine engine and one or more electric motors. When configured as a traditional power system the optionally hybrid power system may derive all power from the gas turbine engine. However, when configured as a hybrid power system, the one or more motors may be coupled to the optionally hybrid power system to supplement the power produced by the gas turbine engine. Additionally, an operator interface that may control the optionally hybrid power system may select from a plurality of operating modes that depend on the configuration of the optionally hybrid power system.
摘要翻译：本公开内容针对“可选混合动力系统”，其可以作为传统动力系统运行，从单个动力源获得动力，或作为混合动力系统从多种类型的动力源获得动力。示例性的可选混合动力系统可以包括燃气涡轮发动机和一个或多个电动机。当被配置为传统动力系统时，可选的混合动力系统可以从燃气涡轮发动机获得所有动力。然而，当被配置为混合动力系统时，一个或多个马达可以联接到可选混合动力系统以补充由燃气涡轮发动机产生的动力。另外，可以控制可选混合动力系统的操作者界面可以从取决于可选混合动力系统的配置的多个操作模式中进行选择。

100. 发明公开

EP3238913A1 ADDITIVELY MANUFACTURED COMPONENTS INCLUDING CHANNELS 有权转让
标题翻译：包括通道在内的附加制造组件
公开(公告)号：EP3238913A1
公开(公告)日：2017-11-01
申请号：EP17165567.3
申请日：2017-04-07
申请人： Rolls-Royce Corporation , Rolls-Royce plc
发明人： Sauer, Kevin , Holdcraft, John , Stapleton, David
IPC分类号： B29C64/00
摘要： An example system (10) may include a computing device (12) and an additive manufacturing tool (14). The computing device (12) may define a digital representation (16d) of an inclined channel (18a, 18d, 18f) at least partially within a component (36a), including an angle θ based on a formula θ = 2 tan -1 [tan(λ/2)/sin(α)]. The inclined channel (18a, 18d, 18f) may define a longitudinal axis (15d, 15f) inclined at the angle α relative to a build direction (13d, 13f), and may include a gabled roof (19b, 19d, 19f) configured to collapse into an arched roof (39e, 39g). The angle λ is a predetermined interior angle of the gabled roof (19b, 19d, 19f) measured in a plane substantially parallel to the build direction (13d, 13f). The angle θ is an interior angle of the gabled roof (19b, 19d, 19f) in a plane substantially normal to the inclined longitudinal axis (15d, 15f). The computing device (12) may control, based on the digital representation (16d), the additive manufacturing tool (14) to deposit a material (20, 26) along the build direction (13d, 13f) to fabricate the component (36a) including the inclined channel (38b).
摘要翻译：示例系统（10）可以包括计算设备（12）和增材制造工具（14）。计算设备（12）可以至少部分地在部件（36a）内限定倾斜通道（18a，18d，18f）的数字表示（16d），包括基于公式θ= 2tan-1 [ 黄褐色（λ/ 2）/ SIN（α）]。倾斜通道（18a，18d，18f）可以限定相对于构建方向（13d，13f）以角度α倾斜的纵向轴线（15d，15f），并且可以包括构造成屋顶的屋顶（19b，19d，19f）坍塌成拱形屋顶（39e，39g）。角度λ是在基本平行于构建方向（13d，13f）的平面中测量的人字形屋顶（19b，19d，19f）的预定内角。角度θ是在基本垂直于倾斜纵向轴线（15d，15f）的平面中的人字形屋顶（19b，19d，19f）的内角。计算设备（12）可以基于数字表示（16d）控制增材制造工具（14）沿着构建方向（13d，13f）沉积材料（20,26）以制造组件（36a）包括倾斜通道（38b）。

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