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121. 发明申请

US20140072448A1 SYSTEM AND METHOD FOR AIRFOIL COVER PLATE 有权
标题翻译：用于气翼盖板的系统和方法
公开(公告)号：US20140072448A1
公开(公告)日：2014-03-13
申请号：US13612769
申请日：2012-09-12
申请人： Christopher Michael Prue , Jesse Blair Butler
发明人： Christopher Michael Prue , Jesse Blair Butler
IPC分类号： F01D5/18 , B23P15/04
CPC分类号： F01D5/20 , F05D2240/307 , F05D2300/514 , F05D2300/612 , Y02T50/673 , Y02T50/676 , Y10T29/49337
摘要： A system includes at least one gas turbine blade that includes at least one recess disposed in a surface of the at least one gas turbine blade. The system also includes a porous insert that includes multiple pores that enable a cooling fluid to flow through the porous insert. The system further includes a cover plate, wherein the porous insert is disposed within the at least one recess, and the cover plate is disposed over the porous insert to enclose the porous insert within the at least one recess.
摘要翻译：一种系统包括至少一个燃气轮机叶片，其包括设置在所述至少一个燃气轮机叶片的表面中的至少一个凹部。该系统还包括多孔插入件，其包括使得冷却流体能够流过多孔插入件的多个孔。所述系统还包括盖板，其中所述多孔插入件设置在所述至少一个凹部内，并且所述盖板设置在所述多孔插入件上方以将所述多孔插入件封闭在所述至少一个凹部内。

122. 发明申请

US20130243601A1 CONNECTING SYSTEM FOR METAL COMPONENTS AND CMC COMPONENTS, A TURBINE BLADE RETAINING SYSTEM AND A ROTATING COMPONENT RETAINING SYSTEM 有权
标题翻译：金属组件和CMC组件的连接系统，涡轮叶片保持系统和旋转组件保持系统
公开(公告)号：US20130243601A1
公开(公告)日：2013-09-19
申请号：US13423658
申请日：2012-03-19
申请人： Donald Earl FLOYD
发明人： Donald Earl FLOYD
IPC分类号： F01D5/32
CPC分类号： F01D5/284 , F01D5/3007 , F01D5/3053 , F01D5/3084 , F05D2260/30 , F05D2300/50212 , F05D2300/6033 , F05D2300/612
摘要： A connecting system for metal component and CMC components, a turbine blade retaining system and rotating component retaining system are provided. The connecting system includes a retaining pin, a metal foam bushing, a first aperture disposed in the metal component, and a second aperture disposed in the ceramic matrix composite component. The first aperture and the second aperture are configured to form a through-hole when the metal component and the ceramic matrix composite component are engaged. The retaining pin and the metal foam bushing are operably arranged within the through-hole to connect the metal component and the ceramic matrix composite component.
摘要翻译：提供了用于金属部件和CMC部件的连接系统，涡轮叶片保持系统和旋转部件保持系统。连接系统包括保持销，金属泡沫衬套，设置在金属部件中的第一孔和设置在陶瓷基体复合部件中的第二孔。当金属部件和陶瓷基体复合部件接合时，第一孔和第二孔构造成形成通孔。保持销和金属泡沫衬套可操作地布置在通孔内，以连接金属部件和陶瓷基体复合部件。

123. 发明申请

US20130039774A1 HYBRID STRUCTURE AIRFOIL 有权
标题翻译：混合结构飞机
公开(公告)号：US20130039774A1
公开(公告)日：2013-02-14
申请号：US13331957
申请日：2011-12-20
申请人： Daniel V. Viens , Vincent C. Nardone , Peter G. Smith , James R. Strife , Foster P. Lamm
发明人： Daniel V. Viens , Vincent C. Nardone , Peter G. Smith , James R. Strife , Foster P. Lamm
IPC分类号： F01D5/12 , F01D5/28 , F01D5/14 , F01D5/18
CPC分类号： F01D5/147 , F01D5/16 , F01D5/282 , F04D29/023 , F04D29/324 , F04D29/388 , F05D2260/96 , F05D2300/603 , F05D2300/612 , F05D2300/615 , Y02T50/672 , Y02T50/673
摘要： A hybrid airfoil for a gas turbine engine is provided that includes a body and a panel. The body has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The body includes a plurality of cavities disposed in the first side of the body, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The panel is a load bearing structure operable to transfer loads to the body and receive loads from the body.
摘要翻译：提供了一种用于燃气涡轮发动机的混合翼型件，其包括主体和面板。主体具有与第一侧相对定向的第一侧和第二侧。第一和第二面在尖端，底座，前缘和后缘之间延伸。主体包括设置在主体的第一侧中的多个空腔，空腔向内朝向第二侧延伸。空腔共同形成开口。至少一个肋设置在空腔之间。一个搁板设置在开口周围。面板连接到搁架第一安装表面和肋上，并且其尺寸被设计成封闭开口。面板是承载结构，可操作以将负载传递到主体并从身体接收负载。

124. 发明申请

US20120266603A1 MULTI-LAYER CERAMIC COMPOSITE POROUS STRUCTURE 有权
标题翻译：多层陶瓷复合多孔结构
公开(公告)号：US20120266603A1
公开(公告)日：2012-10-25
申请号：US13337106
申请日：2011-12-24
申请人： Richard Christopher Uskert , Ted Joseph Freeman , David John Thomas , Jay Lane
发明人： Richard Christopher Uskert , Ted Joseph Freeman , David John Thomas , Jay Lane
IPC分类号： F02C7/141 , B32B38/00 , B32B18/00 , B32B37/02 , B32B5/18 , B32B5/32
CPC分类号： F02C7/18 , B32B5/18 , B32B5/22 , B32B5/24 , B32B5/245 , B32B5/26 , B32B9/005 , B32B9/007 , B32B9/046 , B32B18/00 , B32B2250/03 , B32B2250/20 , B32B2250/40 , B32B2250/42 , B32B2260/04 , B32B2266/04 , B32B2266/06 , B32B2307/306 , B32B2307/724 , B32B2307/726 , B32B2603/00 , C04B37/005 , C04B2237/04 , C04B2237/32 , C04B2237/38 , C04B2237/62 , F01D5/18 , F05D2300/6033 , F05D2300/612 , Y10T156/10 , Y10T428/24331 , Y10T428/24997 , Y10T442/335
摘要： An article of manufacture includes a first ceramic matrix composite (CMC) sheet having a number of flow passages therethrough, and an open-cell foam layer bonded to the first CMC sheet. The open-cell foam layer is an open-cell foam. The article of manufacture includes a second CMC sheet bonded to the open-cell foam layer, the second CMC sheet having a thermal and environmental barrier coating and having a number of flow passages therethrough.
摘要翻译：制品包括具有多个通过其的流动通道的第一陶瓷基质复合材料（CMC）片材和结合到第一CMC片材的开孔泡沫层。开孔泡沫层是开孔泡沫。制品包括结合到开孔泡沫层的第二CMC片，第二CMC片具有热和环境屏障涂层并且具有多个通过其的流动通道。

125. 发明申请

US20110133025A1 ACOUSTIC ATTENUATION PANEL FOR AIRCRAFT FOR ENGINE NACELLE 有权
标题翻译：用于发动机空调的航空器衰减面板
公开(公告)号：US20110133025A1
公开(公告)日：2011-06-09
申请号：US13056822
申请日：2009-07-28
申请人： Guy Bernard Vauchel , Guillaume Ruckert
发明人： Guy Bernard Vauchel , Guillaume Ruckert
IPC分类号： B64C1/40 , B64D33/02 , B64D15/16
CPC分类号： F02C7/045 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , B64D2033/0286 , F02C7/047 , F02C7/24 , F02K1/827 , F05D2300/224 , F05D2300/612 , Y02T50/672
摘要： This acoustic attenuation panel for an aircraft engine nacelle comprises a structuring skin (1) and, by way of acoustic absorption material, a porous material (5) attached to this skin (1).
摘要翻译：用于飞机发动机机舱的声衰减面板包括结构化皮肤（1），并且通过吸声材料，附着到该皮肤（1）上的多孔材料（5）。

126. 发明授权

US07955049B2 Seal between relatively moveable members 有权
标题翻译：相对移动的部件之间的密封
公开(公告)号：US07955049B2
公开(公告)日：2011-06-07
申请号：US11808885
申请日：2007-06-13
申请人： Noel P Hopkins
发明人： Noel P Hopkins
IPC分类号： F01D11/08 , F01D11/12
CPC分类号： F01D11/122 , F01D11/125 , F05D2300/43 , F05D2300/432 , F05D2300/612 , F16J15/445 , Y10T29/49297
摘要： A seal (48) between first and second relatively rotatable members (26,28). The seal comprises an abradable material on at least one of the relatively rotatable members (26,28). The abradable material comprises an open cell metallic foam (60) and polymeric films (64) closing the cells (62) of the metallic foam (60). The seal (48) is used between compressor rotor blades (26) and a stator casing (28) of a gas turbine engine (10). The seal (48) combines the sealing properties of a closed cell metallic foam with the abradability and manufacturing control of open cell metallic foam.
摘要翻译：第一和第二可旋转构件（26,28）之间的密封件（48）。所述密封件包括在所述相对可旋转构件（26,28）中的至少一个上的耐磨材料。耐磨材料包括开孔金属泡沫（60）和封闭金属泡沫（60）的泡孔（62）的聚合膜（64）。密封件（48）用于压缩机转子叶片（26）和燃气涡轮发动机（10）的定子壳体（28）之间。密封件（48）将闭孔金属泡沫的密封性能与开孔金属泡沫的耐磨性和制造控制相结合。

127. 发明申请

US20110085906A1 FAN RETENTION SHAFT 有权
标题翻译：风扇保持轴
公开(公告)号：US20110085906A1
公开(公告)日：2011-04-14
申请号：US12897152
申请日：2010-10-04
申请人： David P. SCOTHERN
发明人： David P. SCOTHERN
IPC分类号： B63H3/00
CPC分类号： F04D29/266 , F01D5/026 , F01D21/045 , F04D29/051 , F05D2260/311 , F05D2300/612 , F16D9/06 , F16F7/125
摘要： A fan retention shaft is provided for retaining a fan within a gas turbine engine in the event of fan shaft failure. The fan retention shaft has a first shaft which in use extends from the engine and a second shaft to which in use the fan is attached, the second shaft being coaxial with the first shaft and the first and second shafts defining an annular passage between them. An energy absorbing medium is disposed within the annular passage. The fan retention shaft has a retaining formation for preventing the first shaft and the second shaft from moving axially with respect to one another. The retaining formation is configured to release the first shaft and the second shaft from their relative axial positions when a threshold axial load is applied to the fan retention shaft. The energy absorbing medium is arranged to absorb kinetic energy from the second shaft as the second shaft moves axially with respect to the first shaft.
摘要翻译：在风扇轴故障的情况下，设置风扇保持轴用于将风扇保持在燃气涡轮发动机内。风扇保持轴具有第一轴，其在使用中从发动机延伸，第二轴在使用中安装有风扇，第二轴与第一轴同轴，第一和第二轴在它们之间形成环形通道。能量吸收介质设置在环形通道内。风扇保持轴具有用于防止第一轴和第二轴相对于彼此轴向移动的保持结构。保持结构构造成当向风扇保持轴施加阈值轴向载荷时，将第一轴和第二轴从其相对的轴向位置释放。能量吸收介质布置成当第二轴相对于第一轴轴向移动时吸收来自第二轴的动能。

128. 发明授权

US07780420B1 Turbine blade with a foam metal leading or trailing edge 有权
标题翻译：涡轮叶片带泡沫金属前缘或后缘
公开(公告)号：US07780420B1
公开(公告)日：2010-08-24
申请号：US11600455
申请日：2006-11-16
申请人： Alfred P. Matheny
发明人： Alfred P. Matheny
IPC分类号： F01D5/14
CPC分类号： F01D5/14 , F01D5/282 , F04D29/324 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2300/603 , F05D2300/612 , Y02T50/672
摘要： A thin compressor blade used in a small aircraft gas turbine engine, in which the blade includes a main blade portion formed from a fiber reinforced resinous composite material to provide a lightweight and strong blade, and in which the leading edge or the trailing edge of the blade is formed from a foam metal reinforced composite material that defines a sharp edge for improved performance of the thin blade. The fibers of the main body extend into the edge region in order that the resin used to bind the foam metal will also bind with the fibers of the laminates to secure the edge to the main blade body. The blade tip can also be formed from the porous foam metal and resin material to make a strong and lightweight rotor blade.
摘要翻译：一种用于小型飞机燃气涡轮发动机中的薄压缩机叶片，其中叶片包括由纤维增强树脂复合材料形成的主叶片部分，以提供轻质且坚固的叶片，并且其中的前缘或后缘叶片由泡沫金属增强复合材料形成，该复合材料限定了锋利的边缘以改善薄叶片的性能。主体的纤维延伸到边缘区域，以便用于结合泡沫金属的树脂也将与层压板的纤维结合，以将边缘固定到主叶片本体。叶片尖端还可以由多孔泡沫金属和树脂材料形成，以制造强而轻的转子叶片。

129. 发明授权

US07775766B2 Gas turbine component 有权
标题翻译：燃气轮机组件
公开(公告)号：US07775766B2
公开(公告)日：2010-08-17
申请号：US10582930
申请日：2004-12-09
申请人： Reinhold Meier , Erich Steinhardt
发明人： Reinhold Meier , Erich Steinhardt
IPC分类号： F01D11/12
CPC分类号： F01D11/127 , B22F2998/00 , F01D11/122 , F01D25/145 , F01D25/24 , F05D2300/612 , Y02T50/672 , Y02T50/675 , B22F7/006 , B22F5/10
摘要： A static gas turbine component, especially for an aircraft engine, is formed at least partially region-wise of metal foam. An abradable shroud lining of metal foam and a carrier allow a radial through-flow of gas.
摘要翻译：特别是用于飞行器发动机的静态燃气涡轮机部件至少部分地形成有金属泡沫的区域。金属泡沫和载体的可磨损护罩衬里允许气体的径向通过。

130. 发明申请

US20080253885A1 Gas turbine engine vane 有权
标题翻译：燃气轮机发动机叶片
公开(公告)号：US20080253885A1
公开(公告)日：2008-10-16
申请号：US11787491
申请日：2007-04-16
申请人： Andrew S. Foose , Jennifer L. Grudnoski
发明人： Andrew S. Foose , Jennifer L. Grudnoski
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D9/02 , F02C7/24 , F02K3/06 , F05D2230/23 , F05D2250/283 , F05D2300/612 , F05D2300/615
摘要： A gas turbine engine vane has first and second members. The first member has a first surface section forming a suction side of an airfoil of the vane. The second surface section forms leading and trailing portions of a pressure side of the airfoil. The third surface section forms a recess between the leading and trailing portions. The second member is secured to the first member and has a first surface section forming an intermediate portion of the pressure side. a leading protrusion of the second member may be captured by a recess below a lip of the first member.
摘要翻译：燃气涡轮发动机叶片具有第一和第二构件。第一构件具有形成叶片的翼型的吸入侧的第一表面部。第二表面部分形成翼型的压力侧的前部和后部。第三表面部分在前部和后部之间形成凹部。第二构件被固定到第一构件并且具有形成压力侧的中间部分的第一表面区段。第二构件的引导突起可以由第一构件的唇缘下方的凹部捕获。

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