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1. 发明申请

US20180216467A1 TURBINE ENGINE WITH AN EXTENSION INTO A BUFFER CAVITY 审中-公开
公开(公告)号：US20180216467A1
公开(公告)日：2018-08-02
申请号：US15422597
申请日：2017-02-02
申请人： General Electric Company
发明人： Brian Kenneth Corsetti , Christopher Michael Ceglio , Robert Francis Manning
IPC分类号： F01D5/08 , F01D25/12 , F01D9/02 , F01D11/02 , F04D19/02 , F04D29/08 , F04D29/32 , F04D29/58 , F02K3/06
CPC分类号： F04D29/582 , F01D11/001 , F01D11/02 , F04D29/083 , F04D29/322 , F05D2250/22 , F05D2250/231 , F05D2250/232 , F05D2250/291 , F05D2250/294 , Y02T50/671
摘要： A turbine engine, such as a gas turbine engine for an aircraft, can include a compressor section, a combustion section, and a turbine section in axial arrangement. The compressor and turbine sections can include a rotating disk having a plurality of blades and a stationary band having a plurality of stationary vanes. The disk and band are spaced axially defining a buffer cavity. One or more extensions extend into the buffer cavity to prevent ingestion of heated gas into the buffer cavity. Recesses on the underside of the extensions can improve the heat transfer coefficient for the extensions.

2. 发明申请

US20180209280A1 BLADED DISC AND METHOD OF MANUFACTURING THE SAME 审中-公开
公开(公告)号：US20180209280A1
公开(公告)日：2018-07-26
申请号：US15877839
申请日：2018-01-23
申请人： ROLLS-ROYCE plc
发明人： John P E FORSDIKE , Simon E. BRAY , Gavin J. BAXTER , Andrew R. WALPOLE
IPC分类号： F01D5/30 , F01D5/02 , B23K20/12
CPC分类号： F01D5/3061 , B23K15/0086 , B23K15/0093 , B23K20/1205 , B23K20/129 , B23K20/16 , B23K20/233 , B23K20/24 , B23K26/0006 , B23K26/34 , B23K2101/001 , B23K2103/08 , B23K2103/26 , B33Y80/00 , F01D5/02 , F01D5/34 , F04D29/321 , F04D29/322 , F05D2220/32 , F05D2230/22 , F05D2230/233 , F05D2230/239 , F05D2230/30 , F05D2300/175 , F05D2300/606
摘要： A method (56) for fabricating an integral assembly (24) is disclosed. The method comprises providing (56) a first workpiece (26) having a first surface and a second workpiece (30) having a second surface (54), performing a first bonding process between the first surface of the first workpiece (26) and the second surface (54) of the second workpiece (30) the bulk material of the first workpiece having a friction weld property that makes it more difficult to weld than a friction weld property at the surface.

3. 发明申请

US20180202458A1 ROTARY ASSEMBLY OF AN AERONAUTICAL TURBOMACHINE COMPRISING AN ADDED-ON FAN BLADE PLATFORM 审中-公开
公开(公告)号：US20180202458A1
公开(公告)日：2018-07-19
申请号：US15741839
申请日：2016-07-06
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Thomas Alain DE GAILLARD , Alexandre Bernard Marie BOISSON , Matthieu Arnaud GIMAT , Audrey LAGUERRE
IPC分类号： F04D29/34 , F04D29/32 , F04D29/64
CPC分类号： F04D29/34 , B64D27/10 , F01D5/066 , F01D5/3015 , F01D11/008 , F04D29/322 , F04D29/329 , F04D29/646 , F05D2220/36 , F05D2300/603
摘要： A rotary assembly of an aviation turbine engine, includes a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk. The tooth of the fan disk includes a tab extending the tooth axially upstream, and the platform includes a locking ring at its upstream end for receiving the tab of the tooth of the fan disk. The assembly further includes a spacer positioned inside the locking ring so as to block the platform on the tab of the tooth of the fan disk.

4. 发明授权

US09970297B2 Composite fan slider with nano-coating 有权
公开(公告)号：US09970297B2
公开(公告)日：2018-05-15
申请号：US14832296
申请日：2015-08-21
申请人： Rolls-Royce Corporation
发明人： Wade A. Vest
IPC分类号： F01D5/30 , F01D5/02 , C25D1/02 , C25D1/08 , C25D5/56 , F04D29/32 , F01D25/00 , F04D29/02 , F01D5/32
CPC分类号： F01D5/02 , C25D1/02 , C25D1/08 , C25D5/56 , F01D5/323 , F01D25/005 , F04D29/023 , F04D29/322 , F05D2220/36 , F05D2230/24 , F05D2230/90 , F05D2250/191 , F05D2300/17 , F05D2300/433 , F05D2300/436 , F05D2300/605 , Y02T50/671 , Y02T50/672
摘要： A fan slider for use in a fan assembly to push a fan blade radially outward of a rotating axis of the gas turbine engine. The fan slider may include a fan slider body coated with a nanocrystalline metallic coating and a slider spring.

5. 发明申请

US20170335865A1 METHOD AND SYSTEM FOR MITIGATING ROTOR BOW 审中-公开
公开(公告)号：US20170335865A1
公开(公告)日：2017-11-23
申请号：US15156751
申请日：2016-05-17
申请人： General Electric Company
发明人： Tod Robert Steen
IPC分类号： F04D29/66 , F01D9/04 , F04D29/54 , F01D5/12 , F04D29/32 , F01D5/26
CPC分类号： F04D29/668 , F01D5/10 , F01D5/12 , F01D5/26 , F01D9/041 , F01D19/00 , F01D25/162 , F01D25/22 , F04D29/322 , F04D29/542 , F05D2220/32 , F05D2240/50 , F05D2260/96 , Y02T50/673
摘要： A method of damping a vibration in a rotatable member and a damping system for a rotatable machine are provided. The damping system includes one or more damping stages. The rotatable machine further comprising a casing at least partially surrounding the rotor. The casing includes inwardly extending vanes that include a radially outer root, a radially inner distal end, and a stationary body extending therebetween. The one or more damping stages includes a damper supportively coupled between one or more roots of the plurality of vanes and the casing, an air bearing fixedly coupled to one or more distal ends of the plurality of vanes and configured to bear against the rotatable body wherein the damping stage is configured to receive vibratory forces from the rotatable body through the air bearing and the vane and ground the received forces to the casing through the damper.

6. 发明授权

US09664058B2 Flowpath boundary and rotor assemblies in gas turbines 有权
公开(公告)号：US09664058B2
公开(公告)日：2017-05-30
申请号：US14587714
申请日：2014-12-31
申请人： General Electric Company
发明人： Michael James Healy , Patrick Daniel Noble , Jeremy Peter Latimer , Brendon James Leary
IPC分类号： F01D5/06 , F01D5/30 , F01D11/00 , F04D29/32 , F04D29/16
CPC分类号： F01D11/008 , F01D5/3007 , F04D29/164 , F04D29/321 , F04D29/322 , F04D29/329 , Y02T50/671 , Y02T50/673
摘要： A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.

7. 发明授权

US09664054B2 Turbomachine rotor with blade roots with adjusting protrusions 有权
公开(公告)号：US09664054B2
公开(公告)日：2017-05-30
申请号：US13878814
申请日：2011-09-07
申请人： Trevor Milne
发明人： Trevor Milne
IPC分类号： B64C11/04 , F03B3/12 , F04D29/34 , F04D29/18 , F01D5/30 , F01D5/00 , F04D19/02 , F04D29/32
CPC分类号： F01D5/30 , F01D5/005 , F01D5/3007 , F04D19/02 , F04D29/322 , F05D2230/60 , F05D2240/80 , F05D2250/70 , Y10T29/49316
摘要： A turbomachine rotor includes a rotor blade mounted to a rotation element. The rotor blade includes a root for mounting the rotor blade to the rotation element. The root has a protrusion structure forming a stop face supporting the mounted root against the rotation element under action of a radially inwardly directed force. The protrusion structure defines a maximum clearance between the stop face and the rotation element. The root is radially moveable to a certain extent where in a radially outermost position the protrusion structure has the maximum radial clearance from the rotation element. The rotation element includes a groove therein. The groove has a groove face bearing the stop face of the rotor blade under action of a radially inwardly directed force. The groove is a circumferential groove extending in a circumferential direction with regard to an axis of rotation of the rotation element.

8. 发明授权

US09523372B2 Fan with overmolded blades 有权
标题翻译：风扇与包覆成型的叶片
公开(公告)号：US09523372B2
公开(公告)日：2016-12-20
申请号：US13696672
申请日：2011-05-06
申请人： Jonathan B. Stagg
发明人： Jonathan B. Stagg
IPC分类号： F04D29/00 , F04D29/34 , F01D5/30 , F04D29/32 , B29C45/14 , F04D29/02 , F04D29/38 , B29C70/68 , B29L31/08
CPC分类号： F04D29/34 , B29C45/14336 , B29C70/68 , B29C2045/14327 , B29L2031/087 , F01D5/30 , F04D29/023 , F04D29/322 , F04D29/329 , F04D29/388 , F05D2230/23 , F05D2300/43
摘要： A fan member particularly for use in a vehicle cooling system. A formed metal hub member with a plurality of plastic polymer blade members. The blade members are overmolded on the hub member, preferably individually. The plastic polymer material is molded through openings in the hub member to help securely hold the blade members in place.
摘要翻译：一种特别用于车辆冷却系统的风扇。一种形成的具有多个塑料聚合物叶片构件的金属毂构件。叶片构件在轮毂构件上包覆成型，优选单独地包覆成型。塑料聚合物材料通过轮毂构件中的开口模制，以有助于将叶片构件牢固地保持在适当的位置。

9. 发明授权

US09482242B1 C-connect fastener for a ceiling fan blade 有权
标题翻译： C型连接紧固件，用于吊扇叶片
公开(公告)号：US09482242B1
公开(公告)日：2016-11-01
申请号：US14095262
申请日：2013-12-03
申请人： LITEX INDUSTRIES, LIMITED
发明人： John F Mares , Ming Chi Lin
IPC分类号： F04D29/34 , F04D29/64 , F04D29/32
CPC分类号： F04D29/644 , F04D25/088 , F04D29/322 , F04D29/34
摘要： C-connect fasteners (24) are provided for securing ceiling fan blades (26) to mounting brackets (20). Protuberant members (32) extend from the mounting brackets (20), and have heads (72) and shanks (74) which fit through apertures (62) in the ceiling fan blades (26). The C-connect fasteners (24) have an upper surface (36), a lower surface (38), and a peripheral edge (40) extending between the upper and lower surfaces (36, 38). An C-shaped opening (46) is formed in the peripheral edge (40) for sliding around the shank (74) and wedging the C-connect fastener (24) between the head (72) of the protuberant member (32) and the upper surface of ceiling fan blade (26). Resilient tabs (52) are spaced about the peripheral edge (40) the C-connect fastener (24) and press the upper surface (36) of the C-connect fastener (24) into the head (72) of the protuberant member (32).
摘要翻译： C连接紧固件（24）用于将吊扇（26）固定到安装支架（20）上。突起构件（32）从安装支架（20）延伸，并且具有通过吊扇叶片（26）中的孔（62）装配的头部（72）和柄部（74）。 C连接紧固件（24）具有在上表面和下表面（36,38）之间延伸的上表面（36），下表面（38）和周边边缘（40）。 C形开口（46）形成在周边边缘（40）中，用于围绕柄（74）滑动并将C连接紧固件（24）楔入突出构件（32）的头部（72）和吊扇叶片（26）的上表面。弹性突片（52）围绕C连接紧固件（24）的周边边缘（40）间隔开，并将C连接紧固件（24）的上表面（36）压入突起构件的头部（72） 32）。

10. 发明申请

US20160312629A1 APPARATUS FOR MOUNTING A BLADE ON A TURBINE DISK 审中-公开
标题翻译：用于安装涡轮盘上的叶片的装置
公开(公告)号：US20160312629A1
公开(公告)日：2016-10-27
申请号：US15096453
申请日：2016-04-12
申请人： Charles Evans , Andrew Narcus , Paul DiCristoforo
发明人： Charles Evans , Andrew Narcus , Paul DiCristoforo
IPC分类号： F01D5/30 , F01D5/02 , F01D5/12 , F04D29/32
CPC分类号： F01D5/3007 , F01D5/02 , F04D29/322 , F05D2230/10 , F05D2250/294 , F05D2250/71 , F05D2250/712
摘要： A turbine wheel or disk having a plurality of dovetail slots formed in its circumference for receiving a dovetail root of a blade such as a compressor or turbine blade. Each of the dovetail slots has a load face positioned to oppose a centrifugal load exerted by the dovetail root when a turbine is in operation. Each of the dovetail slots has a pair of opposing acute bottom corners formed between a radially inner edge of the load face and a bottom of the dovetail slot. Each of the acute bottom corners may have an undercut formed that includes a first radius of curvature and a second radius of curvature to form a clearance between the dovetail root and the dovetail slot. Each of the dovetail slots may have a curved bottom for receiving a rounded dovetail root.
摘要翻译：涡轮机叶轮或盘，其具有形成在其圆周上的多个燕尾槽，用于接收诸如压缩机或涡轮叶片的叶片的燕尾根。每个燕尾槽具有负载面，该负载面定位成当涡轮机运行时与燕尾根施加的离心负载相对。每个燕尾槽具有形成在负载面的径向内边缘和燕尾槽的底部之间的一对相对的急剧底角。每个急剧的底角可以具有形成的底切，其包括第一曲率半径和第二曲率半径，以形成燕尾根和燕尾槽之间的间隙。每个燕尾槽可以具有用于接收圆形燕尾根的弯曲底部。

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