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41. 发明申请

US20170176106A1 ROTARY DEGASSERS AND COMPONENTS THEREFOR 审中-公开
公开(公告)号：US20170176106A1
公开(公告)日：2017-06-22
申请号：US15449251
申请日：2017-03-03
申请人： Molten Metal Equipment Innovations, LLC
发明人： Paul V. Cooper
IPC分类号： F27D27/00 , F01D5/18
CPC分类号： F01D5/18 , C21C1/06 , F16C3/02 , F16D1/108 , F27B3/22 , F27D3/16 , F27D27/00 , F27D2027/002 , Y10T403/25
摘要： Disclosed are degassers, couplings, impeller shafts and impellers for use in molten metal. One such coupling transfers gas into an impeller shaft, the coupling having a smooth, tapered internal surface to align with a corresponding surface on the impeller shaft and help prevent gas leakage and to assist in preventing damage to the impeller shaft. Improved impellers for shearing and mixing gas are also disclosed, as is a degasser including one or more of these components.

42. 发明申请

US20170145923A1 SERPENTINE PLATFORM COOLING STRUCTURES 审中-公开
公开(公告)号：US20170145923A1
公开(公告)日：2017-05-25
申请号：US14946279
申请日：2015-11-19
申请人： United Technologies Corporation
发明人： Brandon W. Spangler , Edward F. Pietraszkiewicz
IPC分类号： F02C7/18 , F01D5/18 , F01D5/08
CPC分类号： F02C7/18 , F01D5/08 , F01D5/18 , F01D5/187 , F05D2230/232 , F05D2240/81 , F05D2250/185 , F05D2260/202 , F05D2260/204 , F05D2260/205 , Y02T50/672 , Y02T50/676
摘要： A platform is disclosed. The platform may include an airfoil section with a cooling passage and a platform. The platform may have various cooling features, such as a platform cooling apparatus. The platform cooling apparatus may have a cooling passage forming a channel disposed at least partially through the platform and the platform cooling apparatus may have an inflow channel in fluidic communication with the channel and the cooling passage so that cooling air may travel from the cooling cavity of the blade airfoil section and into the platform cooling apparatus. Moreover, the platform cooling apparatus may have a cooling cover apparatus at least partially fluidically sealing the platform cooling apparatus.

43. 发明申请

US20170144219A1 METHOD FOR FORMING A DIRECTIONALLY SOLIDIFIED REPLACEMENT BODY FOR A COMPONENT USING ADDITIVE MANUFACTURING 有权
公开(公告)号：US20170144219A1
公开(公告)日：2017-05-25
申请号：US15219921
申请日：2016-07-26
申请人： United Technologies Corporation
发明人： JinQuan Xu
IPC分类号： B22D27/04 , B33Y40/00 , B33Y80/00 , B22C9/10 , B22C9/22 , B22D29/00 , B22D25/02 , B22F3/105 , B22F3/24 , B22F5/04 , B23K15/00 , B23K26/342 , B23K26/70 , B23K37/00 , F01D5/00 , F01D5/12 , F01D9/04 , F02C7/22 , F23R3/00 , B33Y10/00
CPC分类号： B22D27/045 , B22C9/02 , B22C9/04 , B22C9/10 , B22C9/108 , B22C9/12 , B22C9/22 , B22D23/06 , B22D25/02 , B22D29/001 , B22F3/1055 , B22F3/24 , B22F5/007 , B22F5/009 , B22F5/04 , B22F2003/248 , B22F2998/10 , B23K1/0018 , B23K9/04 , B23K9/167 , B23K15/0046 , B23K15/0086 , B23K20/00 , B23K26/34 , B23K26/342 , B23K26/70 , B23K31/02 , B23K37/00 , B23K2101/001 , B23P6/005 , B23P6/007 , B23P6/045 , B33Y10/00 , B33Y40/00 , B33Y80/00 , C30B11/00 , C30B11/003 , C30B21/02 , C30B29/52 , F01D5/005 , F01D5/12 , F01D5/18 , F01D5/186 , F01D5/187 , F01D9/04 , F02C7/222 , F05D2220/32 , F05D2230/21 , F05D2230/233 , F05D2230/234 , F05D2230/235 , F05D2230/238 , F05D2230/30 , F05D2230/80 , F05D2240/122 , F05D2240/304 , F05D2260/202 , F05D2260/204 , F05D2300/175 , F05D2300/20 , F05D2300/606 , F05D2300/608 , F23R3/002 , Y02P10/292 , Y02P10/295
摘要： A method of manufacturing a replacement body for a component is provided. The method includes the steps of: a) additively manufacturing a crucible for casting of the replacement body; b) solidifying a metal material within the crucible to form a directionally solidified microstructure within the replacement body; and c) removing the crucible to reveal the directionally solidified replacement body.

44. 发明授权

US09657578B2 Rotary degassers and components therefor 有权
公开(公告)号：US09657578B2
公开(公告)日：2017-05-23
申请号：US14923296
申请日：2015-10-26
申请人： Paul V. Cooper
发明人： Paul V. Cooper
IPC分类号： F27D27/00 , F01D5/18 , C21C1/06 , F16C3/02 , F16D1/108 , F27D3/16
CPC分类号： F01D5/18 , C21C1/06 , F16C3/02 , F16D1/108 , F27B3/22 , F27D3/16 , F27D27/00 , F27D2027/002 , Y10T403/25
摘要： Disclosed are degassers, couplings, impeller shafts and impellers for use in molten metal. One such coupling transfers gas into an impeller shaft, the coupling having a smooth, tapered internal surface to align with a corresponding surface on the impeller shaft and help prevent gas leakage and to assist in preventing damage to the impeller shaft. Improved impellers for shearing and mixing gas are also disclosed, as is a degasser including one or more of these components.

45. 发明申请

US20170136534A1 METHOD FOR MANUFACTURING A TWO-COMPONENT BLADE FOR A GAS TURBINE ENGINE AND BLADE OBTAINED BY SUCH A METHOD 审中-公开
公开(公告)号：US20170136534A1
公开(公告)日：2017-05-18
申请号：US15323766
申请日：2015-06-29
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Francois CASTEILLA , Sebastien DIGARD BROU DE CUISSART , Serge FARGEAS , Vincent HERB
IPC分类号： B22D25/02 , B22C9/10 , B22C9/24 , F01D5/18 , B22D29/00 , B22D30/00 , F01D5/14 , B22C1/00 , B22D21/00
CPC分类号： B22D25/02 , B22C1/00 , B22C9/108 , B22C9/24 , B22D19/00 , B22D19/04 , B22D21/005 , B22D29/001 , B22D30/00 , F01D5/147 , F01D5/18 , F01D5/187 , F01D5/284 , F05D2220/32 , F05D2230/211 , F05D2300/177 , F05D2300/211 , Y02T50/676
摘要： A method of fabricating a two-component blade for a gas turbine engine, the method including in succession: obtaining a blade profile made of ceramic material having a hole passing right through the blade profile in its length direction so as to form a longitudinal channel opening out into a top cavity; positioning and maintaining the blade profile in a mold so as to form a bottom cavity communicating with the channel of the blade profile; casting molten metal into the blade profile so as to fill the top and bottom cavities and the channel interconnecting them; and cooling the metal so that the shrinkage of the metal cooled in the top and bottom cavities leads to the ceramic of the blade profile being subjected to compression prestress.

46. 发明申请

US20170080526A1 ADDITIVE MANUFACTURING USING CAST STRIP SUPERALLOY MATERIAL 审中-公开
公开(公告)号：US20170080526A1
公开(公告)日：2017-03-23
申请号：US14860002
申请日：2015-09-21
申请人： Siemens Energy, Inc.
发明人： Gerald J. Bruck
IPC分类号： B23K26/342 , B23K11/16 , B23K11/02
CPC分类号： B23K26/342 , B23K11/02 , B23K11/16 , B23K31/003 , B23K2101/001 , B23K2103/26 , B33Y10/00 , B33Y80/00 , F01D5/18 , F05D2230/232 , F05D2300/175
摘要： A method of additive manufacturing, including: placing a layer (10) of strip-cast superalloy sheet material over a subcomponent (12) leaving a gap (20) between the layer and the subcomponent; and creating a weldment (14) to the layer. Shrinkage in the layer caused by the weldment is accommodated by a decrease in the gap with reduced shrinkage stress in the weldment. The layer may be formed of more than one piece (16), and the weldment may join the pieces together with or without joining the layer to the subcomponent. The gap may again grow due to differential thermal expansion when the resulting component is placed into service, thereby functioning as a passively regulated cooling channel.

47. 发明申请

US20170058685A1 ADDITIVE LAYER MANUFACTURING 有权
标题翻译：添加剂制造
公开(公告)号：US20170058685A1
公开(公告)日：2017-03-02
申请号：US15227416
申请日：2016-08-03
申请人： ROLLS-ROYCE plc
发明人： Matthew D TUCKER
IPC分类号： F01D9/04 , B33Y70/00 , B33Y10/00 , B33Y80/00 , F01D5/18 , F01D25/12
CPC分类号： F01D9/041 , B22F3/1055 , B22F5/04 , B22F5/10 , B22F2003/1059 , B22F2999/00 , B28B1/001 , B29C64/153 , B33Y10/00 , B33Y70/00 , B33Y80/00 , F01D5/147 , F01D5/18 , F01D5/187 , F01D5/284 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/20 , F05D2230/30 , F05D2230/31 , F05D2240/81 , F05D2250/20 , F05D2250/291 , F05D2260/204 , F05D2260/2212 , F05D2260/22141 , Y02P10/295
摘要： A method for the manufacture of a component having an internal cavity and an array of pedestals extending into the cavity includes; defining external and core geometries of the component; using a powder-bed additive layer manufacturing method, building the component from a plurality of layers laid on a first-plane; and removing excess powder from the core in a first powder extraction direction along the first-plane. The core geometry is adapted for improved powder removal; including a main core passage, an array of pedestals extending into the passage and passage wall extending from the first-plane, one or more pedestals coinciding with the passage wall, having a cross-section in a plane parallel to the first-plane which is altered with respect to the cross-section of non-coinciding pedestals to extend a face of the pedestal which faces away from the powder extraction direction to intersect the passage wall at an obtuse angle.
摘要翻译：一种用于制造具有内腔和延伸到空腔中的基座阵列的部件的方法包括：定义组件的外部和核心几何; 使用粉末添加剂层制造方法，从设置在第一平面上的多个层构建所述部件; 以及沿第一平面在第一粉末提取方向上从芯中去除多余的粉末。核心几何适用于改进粉末去除; 包括主芯通道，延伸到通道中的基座阵列和从第一平面延伸的通道壁，与通道壁重合的一个或多个基座，在平行于第一平面的平面中具有横截面，相对于不重合基座的横截面而改变，以使基座的面向远离粉末取出方向延伸的方向以钝角相交于通道壁。

48. 发明申请

US20170058681A1 REMOVABLY ATTACHABLE SNUBBER ASSEMBLY 有权
标题翻译：可拆卸的可拆卸的SNUBBER总成
公开(公告)号：US20170058681A1
公开(公告)日：2017-03-02
申请号：US14838645
申请日：2015-08-28
申请人： Siemens Energy, Inc.
发明人： Nicholas F. Martin, JR. , David J. Wiebe
IPC分类号： F01D5/22 , F01D5/18
CPC分类号： F01D5/22 , F01D5/18 , F01D5/225 , F05D2220/3215 , F05D2230/60 , F05D2260/20 , F05D2260/96
摘要： A removably attachable snubber assembly for turbine blades includes a turbine blade airfoil including a trailing edge and a leading edge joined by a pressure side and a suction side to provide an outer surface extending in a radial direction to a tip. At least one snubber attachment platform is integrally formed onto the outer surface of the turbine blade airfoil. The at least one snubber attachment platform includes an interlocking mechanism. A snubber is removably attachable to the at least one snubber attachment platform, the snubber including a first end, a second end, a trailing edge, a leading edge, a snubber length, and a snubber width. The snubber also includes a removable attachment mechanism on at least one of the first end and the second end that connects with the interlocking mechanism on the at least one snubber attachment platform.
摘要翻译：用于涡轮机叶片的可拆卸地连接的缓冲组件包括涡轮叶片翼型件，其包括后缘和通过压力侧和吸力侧连接的前缘，以提供沿径向方向延伸到尖端的外表面。至少一个缓冲器附接平台一体地形成在涡轮叶片翼型件的外表面上。所述至少一个缓冲器附接平台包括互锁机构。缓冲器可移除地附接到所述至少一个缓冲器附接平台，所述缓冲器包括第一端，第二端，后缘，前缘，缓冲器长度和缓冲宽度。缓冲器还包括在第一端和第二端中的至少一个上的可拆卸的附接机构，其与至少一个缓冲器附接平台上的互锁机构连接。

49. 发明申请

US20170058680A1 CONFIGURATIONS FOR TURBINE ROTOR BLADE TIPS 审中-公开
标题翻译：涡轮转子叶片的配置
公开(公告)号：US20170058680A1
公开(公告)日：2017-03-02
申请号：US14843069
申请日：2015-09-02
申请人： General Electric Company
发明人： Rohit Chouhan , Shashwat Swami Jaiswal
IPC分类号： F01D5/20 , F01D5/18
CPC分类号： F01D5/20 , F01D5/18 , F05D2220/32 , F05D2240/306 , F05D2240/307 , F05D2260/221 , Y02T50/673
摘要： A rotor blade for a turbine of a gas turbine system. The rotor blade may include: an airfoil that includes a pressure sidewall and a suction sidewall defining an outer periphery, wherein the pressure sidewall and suction sidewall of the airfoil connect along a leading edge and a trailing edge; a tip that defines an outer radial end of the airfoil, wherein the tip included a cap on which an outboard projecting rail defines a tip cavity; and a rail gap formed through an aftward section of the rail.
摘要翻译：一种用于燃气轮机系统的涡轮的转子叶片。转子叶片可以包括：翼型件，其包括压力侧壁和限定外周边的吸力侧壁，其中翼型件的压力侧壁和抽吸侧壁沿着前缘和后缘连接; 限定所述翼型件的外径向端部的尖端，其中所述尖端包括盖，所述外侧突出轨道限定在所述顶盖腔体上; 以及通过轨道的后部形成的轨道间隙。

50. 发明申请

US20170058676A1 System and Method for A Fluidic Barrier on the Low Pressure Side of A Fan Blade 有权
标题翻译：风扇叶片低压侧流动屏障的系统和方法
公开(公告)号：US20170058676A1
公开(公告)日：2017-03-02
申请号：US14837942
申请日：2015-08-27
申请人： Rolls Royce North American Technologies Inc
发明人： Edward C. Rice
IPC分类号： F01D5/14 , F01D25/24 , F01D11/10 , F02K3/06 , F01D5/18
CPC分类号： F01D5/145 , F01D5/18 , F01D11/04 , F01D11/10 , F01D25/24 , F02C3/064 , F02K1/28 , F02K1/386 , F02K3/06 , F02K3/075 , F05D2220/36 , F05D2240/12 , F05D2240/127 , Y02T50/673
摘要： A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A fluid passage is defined between the splitters. The turbofan engine has a plurality of high pressure fluid jets originating from the low pressure side of the fan blades, the jets restricting the migration of the core stream into the bypass stream through the fluid passage.
摘要翻译：涡轮风扇发动机具有与芯流流体连通的风扇部分和在风扇部分的上游和下游设置的分流器分离的旁路空气流。在分流器之间限定流体通道。涡轮风扇发动机具有源自风扇叶片的低压侧的多个高压流体射流，喷射器限制核心流通过流体通道迁移到旁路流中。

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