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71. 发明申请

US20160101561A1 DUAL-WALLED CERAMIC MATRIX COMPOSITE (CMC) COMPONENT WITH INTEGRAL COOLING AND METHOD OF MAKING A CMC COMPONENT WITH INTEGRAL COOLING 有权
标题翻译：具有整体冷却的双壁陶瓷基复合材料（CMC）组分和制备具有整体冷却的CMC组分的方法
公开(公告)号：US20160101561A1
公开(公告)日：2016-04-14
申请号：US14881864
申请日：2015-10-13
申请人： Rolls-Royce Corporation
发明人： Jeffrey A. Walston , Sean Landwehr
IPC分类号： B29C53/56 , B28B1/48 , B32B1/08 , F01D11/00 , B32B18/00 , F01D5/14 , F01D9/02 , F23R3/42 , B28B1/24 , B32B3/26
CPC分类号： F01D11/003 , B23K1/0018 , B23K2101/001 , B29L2031/08 , B32B1/00 , B32B1/08 , B32B3/08 , B32B3/266 , B32B5/02 , B32B5/022 , B32B5/024 , B32B5/22 , B32B5/26 , B32B7/045 , B32B18/00 , B32B2255/02 , B32B2255/20 , B32B2260/021 , B32B2260/04 , B32B2260/044 , B32B2262/105 , B32B2307/306 , B32B2307/308 , B32B2307/50 , B32B2307/718 , B32B2581/00 , B32B2603/00 , C04B37/005 , C04B2235/3418 , C04B2235/5244 , C04B2235/5436 , C04B2235/616 , C04B2237/083 , C04B2237/365 , C04B2237/38 , C04B2237/592 , C04B2237/597 , C04B2237/60 , C04B2237/61 , C04B2237/62 , C04B2237/84 , F01D5/147 , F01D5/18 , F01D5/186 , F01D5/189 , F01D5/282 , F01D5/284 , F01D9/02 , F01D9/065 , F05D2240/127 , F05D2260/201 , F05D2260/2212 , F05D2300/6033 , F23R3/002 , F23R3/007 , F23R2900/00018 , F23R2900/03041 , F23R2900/03044
摘要： A dual-walled ceramic matrix composite (CMC) component comprises: a CMC core having a hollow shape enclosing at least one interior channel; and a CMC outer layer overlying and spaced apart from the CMC core by a ceramic slurry-cast architecture positioned therebetween. Each of the CMC core and the CMC outer layer comprises ceramic fibers in a ceramic matrix. The CMC core further includes a plurality of through-thickness inner cooling holes in fluid communication with the at least one interior channel. The ceramic slurry-cast architecture defines a cooling fluid path over an outer surface of the CMC core that connects the interior channel(s) to an external environment of the dual-walled CMC component. The CMC outer layer may also include a plurality of through-thickness outer cooling holes in fluid communication with the cooling fluid path, thereby extending the cooling fluid path through the CMC outer layer.
摘要翻译：双壁陶瓷基复合材料（CMC）组件包括：CMC芯，其具有封闭至少一个内部通道的中空形状; 以及通过位于它们之间的陶瓷浆料铸造结构将CMC外层覆盖并与CMC芯间隔开的CMC外层。 CMC芯和CMC外层中的每一个包括陶瓷基体中的陶瓷纤维。 CMC芯还包括与至少一个内部通道流体连通的多个通过厚度的内部冷却孔。陶瓷浆料浇注结构在CMC芯的外表面上定义了冷却流体路径，其将内部通道连接到双壁CMC部件的外部环境。 CMC外层还可以包括与冷却流体路径流体连通的多个通过厚度的外部冷却孔，从而使冷却流体路径延伸穿过CMC外层。

72. 发明申请

US20160084090A1 METHOD AND ASSEMBLY FOR REDUCING SECONDARY HEAT IN A GAS TURBINE ENGINE 审中-公开
标题翻译：用于减少气体涡轮发动机中二次热的方法和装置
公开(公告)号：US20160084090A1
公开(公告)日：2016-03-24
申请号：US14844082
申请日：2015-09-03
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Brian D. Merry , James D. Hill , Mark F. Zelesky
IPC分类号： F01D5/18 , F02C3/08 , F01D11/00
CPC分类号： F01D5/18 , F01D5/06 , F01D5/185 , F01D5/186 , F01D5/187 , F01D11/001 , F01D11/003 , F01D11/005 , F02C3/08 , F05D2220/32 , F05D2260/20 , Y02T50/676
摘要： A turbine section includes a rotor assembly which includes an internal cooling passage. A segmented seal is adjacent the rotor assembly and includes a fluid passage that is in fluid communication with the internal cooling passage.
摘要翻译：涡轮部分包括包括内部冷却通道的转子组件。分段密封件邻近转子组件并且包括与内部冷却通道流体连通的流体通道。

73. 发明申请

US20160076381A1 SECONDARY FLOWPATH SYSTEM FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机的二次流量系统
公开(公告)号：US20160076381A1
公开(公告)日：2016-03-17
申请号：US14853392
申请日：2015-09-14
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Brian D. Merry , James D. Hill , William K. Ackermann
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/066 , F01D5/084 , F01D5/085 , F04D29/321 , F04D29/584 , F05D2260/205 , F05D2260/221 , Y02T50/671 , Y02T50/676
摘要： A rotor assembly of a gas turbine engine may be spoked and includes a rotor and a shell. The rotor has a rotor disk and a plurality of blades each having a platform attached to the rotor disk and with a first channel defined radially between the platforms and the rotor disk. The shell projects aft of the rotor and includes inner and outer walls with a passage defined therebetween. The passage is in fluid communication with the first channel and, together, form part of a secondary flowpath for cooling of adjacent components. The rotor assembly may further include a structure located radially inward of the rotor disk and shell. The structure defines a supply conduit for flowing air from the passage and into a rotor bore defined at least in part by adjacent rotor disks. The entering air, being pre-heated when flowing through the channel and passage, warms the bore and reduces thermal gradients, thus thermal fatigue, across the rotor disk.
摘要翻译：燃气涡轮发动机的转子组件可以被喷射并且包括转子和壳体。转子具有转子盘和多个叶片，每个叶片具有附接到转子盘的平台，并且在平台和转子盘之间径向地限定第一通道。壳体在转子的后方突出并且包括具有在其间限定的通道的内壁和外壁。通道与第一通道流体连通，并且一起形成用于冷却相邻部件的次级流路的一部分。转子组件还可以包括位于转子盘和壳的径向内侧的结构。该结构限定用于使空气从通道流入并至少部分地由相邻转子盘限定的转子孔的供应管道。进入的空气在流过通道和通道时被预热，加热了孔，并降低了转子盘上的热梯度，从而导致热疲劳。

74. 发明授权

US09273558B2 Saw teeth turbulator for turbine airfoil cooling passage 有权
标题翻译：用于涡轮翼型冷却通道的锯齿紊流器
公开(公告)号：US09273558B2
公开(公告)日：2016-03-01
申请号：US14159817
申请日：2014-01-21
申请人： Siemens Energy, Inc.
发明人： George Liang
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/18 , F01D5/147 , F01D5/187 , F05D2250/11 , F05D2250/182 , F05D2250/183 , F05D2250/21 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A trip strip having a saw-tooth configuration that has application for cooling flow channels in a blade of a gas turbine engine. The saw-tooth configuration is defined by trip strip sections positioned end-to-end, where a leading edge of a trip strip section has a lower height than a trailing end of the trip strip section, and where the next trip strip section having the lower height leading edge disrupts the vortex created by the preceding trip strip section so that its size is reduced.
摘要翻译：具有锯齿结构的跳闸带，其具有用于冷却燃气涡轮发动机的叶片中的流动通道的应用。锯齿配置由端对端定位的跳闸带部分限定，其中跳闸带部分的前缘具有比跳闸带部分的尾端低的高度，并且其中下一跳闸带段具有较低的高度前缘破坏由前一跳闸带部分产生的涡流，使其尺寸减小。

75. 发明授权

US09260972B2 Tip leakage flow directionality control 有权
标题翻译：尖端泄漏流动方向性控制
公开(公告)号：US09260972B2
公开(公告)日：2016-02-16
申请号：US13540752
申请日：2012-07-03
申请人： Mark F. Zelesky , Andrew S. Aggarwala
发明人： Mark F. Zelesky , Andrew S. Aggarwala
IPC分类号： F01D5/20 , F01D5/18 , F01D5/14
CPC分类号： F01D5/18 , F01D5/146 , F01D5/20 , F05D2240/307 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil comprises a suction sidewall, a pressure sidewall, a tip wall, and a tip leakage control channel. Each sidewall extends spanwise from an airfoil base and chordwise between a leading edge and a trailing edge. The tip wall extends chordwise from the leading edge to the trailing edge and joins respective outer spanwise ends of the suction and pressure sidewalls. The tip leakage control channel has an inlet and an outlet recessed into an outer surface of the tip wall. An inlet of the channel begins proximate a junction of the airfoil pressure sidewall and the tip wall. An outlet of the channel terminates at a recessed portion of the junction of the tip wall and the suction sidewall.
摘要翻译：涡轮机翼片包括抽吸侧壁，压力侧壁，尖端壁和尖端泄漏控制通道。每个侧壁从翼型基座向翼展方向延伸，并且在前缘和后缘之间并排。尖端壁从前缘延伸到后缘，并且连接吸力和压力侧壁的相应的外翼展端。尖端泄漏控制通道具有凹入到顶端壁的外表面中的入口和出口。通道的入口在翼型压力侧壁和尖端壁的接合点附近开始。通道的出口终止于尖端壁和抽吸侧壁的接合处的凹陷部分。

76. 发明申请

US20160001354A1 GAS TURBINE ENGINE COMPONENT MANUFACTURING METHOD AND CORE FOR MAKING SAME 审中-公开
标题翻译：气体涡轮发动机组件制造方法和制造方法的核心
公开(公告)号：US20160001354A1
公开(公告)日：2016-01-07
申请号：US14767612
申请日：2014-02-12
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Hector M. Pinero , Richard H. Page
IPC分类号： B22C9/24 , B22C9/10 , F01D5/18 , B22D21/02 , B22D25/02 , F01D9/04 , B22C9/04 , B22C9/12
CPC分类号： B22C9/24 , B22C9/04 , B22C9/10 , B22C9/108 , B22C9/12 , B22C21/14 , B22D21/025 , B22D25/02 , F01D5/18 , F01D5/187 , F01D9/041 , F05D2220/32 , F05D2230/211 , F05D2240/12 , F05D2240/30 , F05D2300/177 , F05D2300/20 , Y02T50/676
摘要： A method of manufacturing a gas turbine engine component includes providing a core having a brittle feature, supporting the feature with a first meltable material, arranging the core with the first meltable material in a first mold, and surrounding the core and the first meltable material with a second meltable material to provide a component shape. The method also includes coating the second meltable material with a refractory material to produce a second mold, removing the first and second meltable material, and casting a component in the second mold.
摘要翻译：一种制造燃气涡轮发动机部件的方法包括提供具有脆性特征的芯部，用第一可熔融材料支撑该特征，将芯体与第一可熔材料一起设置在第一模具中，并且围绕芯部和第一可熔融材料，第二可熔融材料，以提供部件形状。该方法还包括用耐火材料涂覆第二可熔材料以产生第二模具，去除第一和第二可熔融材料，以及将组件浇铸在第二模具中。

77. 发明申请

US20150361801A1 FLUID DAMPER AND METHOD OF MAKING 有权
标题翻译：流体阻尼器及其制造方法
公开(公告)号：US20150361801A1
公开(公告)日：2015-12-17
申请号：US14698284
申请日：2015-04-28
申请人： United Technologies Corporation
发明人： Ken F. Blaney , Richard K. Hayford
IPC分类号： F01D5/26 , F01D25/06 , F01D5/18
CPC分类号： F01D5/26 , F01D5/16 , F01D5/18 , F01D25/06 , F05D2220/32 , F05D2230/211 , F05D2260/96 , F05D2300/1606 , F05D2300/1614 , Y10T29/49341
摘要： An airfoil includes an airfoil structure defining a damping network that includes a first cavity, a second cavity, a flow passage connecting the first and second cavities. The airfoil further includes a damping material configured to flow through the damping network. A method of forming an airfoil includes forming an airfoil body having a damping network that includes a first cavity, a second cavity, and a flow passage connecting the first and second cavities. The method further includes adding a damping material configured to flow through the damping network.
摘要翻译：翼型件包括限定阻尼网络的翼型结构，该阻尼网络包括第一空腔，第二空腔，连接第一和第二空腔的流动通道。翼型件还包括构造成流过阻尼网络的阻尼材料。形成翼型的方法包括形成具有阻尼网络的翼型本体，所述阻尼网络包括第一空腔，第二空腔和连接第一和第二空腔的流动通道。该方法还包括添加被配置成流过阻尼网络的阻尼材料。

78. 发明申请

US20150345304A1 GAS TURBINE ENGINE COMPONENT HAVING VASCULAR ENGINEERED LATTICE STRUCTURE 审中-公开
标题翻译：具有瓦斯工程尺寸结构的气体涡轮发动机部件
公开(公告)号：US20150345304A1
公开(公告)日：2015-12-03
申请号：US14654676
申请日：2013-03-15
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Dominic J. MONGILLO , Tracy A. PROPHETER-HINCKLEY , Mark F. ZELESKY , Joel H. WAGNER , Thomas N. SLAVENS
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , B22F3/1055 , B23P15/26 , B33Y10/00 , B33Y70/00 , B33Y80/00 , F01D5/147 , F01D5/18 , F01D5/183 , F01D5/184 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/08 , F01D25/12 , F01D25/24 , F02C7/18 , F05D2250/185 , F05D2260/204 , F23R3/002 , F23R2900/03043 , Y10T29/49318
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure.
摘要翻译：根据本公开的示例性方面的部件尤其包括形成在壁内部的壁和血管工程格子结构。血管工程格子结构限定了中空血管结构，其构造成使流体通过血管工程化晶格结构。血管工程格子结构具有至少一个入口孔和至少一个出口孔，其将流体与中空血管结构连通。

79. 发明申请

US20150330246A1 TEST BLADE 有权
标题翻译：测试刀片
公开(公告)号：US20150330246A1
公开(公告)日：2015-11-19
申请号：US14693171
申请日：2015-04-22
申请人： ROLLS-ROYCE PLC
发明人： Christopher M WHITEHEAD , Ewan F THOMPSON , Paul J MASON , Jeremy N TURNER
IPC分类号： F01D21/04 , F01D5/18 , F01D5/30
CPC分类号： F01D21/045 , F01D5/18 , F01D5/3007 , F05D2220/30 , F05D2240/30 , F05D2260/83 , Y02T50/672 , Y10T29/49334
摘要： A test blade for use in a blade-release test in which the blade is mounted on a rotatable hub and at least a portion of the blade is released therefrom by the action of a controlled explosion. The blade has a root portion for mounting on said rotatable hub and the root portion comprises a radially inner surface having a channel extending at least partly along or proximal the camber line. The channel is for receiving at least one explosive charge and at least one detonator which may be contained within a charge carrier.
摘要翻译：用于刀片释放测试的测试刀片，其中刀片安装在可旋转轮毂上，并且刀片的至少一部分通过受控爆炸的动作被释放。叶片具有用于安装在所述可旋转轮毂上的根部部分，并且根部部分包括径向内表面，该径向内表面具有至少部分地沿着或靠近弯曲线延伸的通道。该通道用于接收至少一种炸药和至少一个可以包含在电荷载体内的雷管。

80. 发明申请

US20150322799A1 METHOD FOR FORMING COMPONENTS USING ADDITIVE MANUFACTURING AND RE-MELT 有权
标题翻译：使用添加剂制造和再熔融成型组件的方法
公开(公告)号：US20150322799A1
公开(公告)日：2015-11-12
申请号：US14706659
申请日：2015-05-07
申请人： United Technologies Corporation
发明人： JinQuan Xu
IPC分类号： F01D5/18 , C22C19/03 , C22C19/07 , C22C38/00 , C30B11/00 , B22D25/02 , B22D27/04 , B22D29/00 , C30B21/02 , B22C9/02 , B22C9/22
CPC分类号： F01D5/18 , B22C9/02 , B22C9/04 , B22C9/10 , B22C9/12 , B22C9/22 , B22C9/24 , B22D19/10 , B22D21/005 , B22D23/06 , B22D25/02 , B22D27/045 , B22D29/00 , B22F3/1055 , B22F5/007 , B22F5/04 , B22F2003/248 , B23P6/007 , B23P15/02 , B28B1/001 , B28B7/346 , B33Y10/00 , B33Y80/00 , C22C19/03 , C22C19/07 , C22C38/00 , C30B11/00 , C30B11/002 , C30B11/003 , C30B21/02 , C30B29/52 , F01D5/005 , F01D5/14 , F01D5/186 , F01D5/187 , F01D5/28 , F01D5/284 , F01D5/3084 , F01D5/34 , F02M21/0206 , F02M35/10334 , F02M2200/9007 , F04D29/0465 , F04D29/0566 , F05D2220/32 , F05D2230/21 , F05D2230/22 , F05D2230/30 , F05D2240/122 , F05D2240/30 , F05D2240/304 , F05D2260/202 , F05D2300/175 , F05D2300/20 , F05D2300/21 , F05D2300/22 , F05D2300/6033 , F05D2300/606 , F05D2300/607 , F05D2300/609 , Y02P10/292 , Y02P10/295
摘要： A method of manufacturing a component includes additively manufacturing a crucible; directionally solidifying a metal material within the crucible; and removing the crucible to reveal the component. A component for a gas turbine engine includes a directionally solidified metal material component, the directionally solidified metal material component having been additively manufactured of a metal material concurrently with a core, the metal material having been remelted and directionally solidified.
摘要翻译：一种制造组件的方法包括：附加地制造坩埚; 定向凝固坩埚内的金属材料; 并移除坩埚以露出部件。燃气涡轮发动机的部件包括定向凝固的金属材料部件，所述定向凝固的金属材料部件已经与金属材料同时地与金属材料相加地制造，所述金属材料已被再熔化并定向凝固。

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