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1. 发明申请

US20180163744A1 SYSTEMS AND METHODS FOR MAKING BLADE SHEATHS 审中-公开
公开(公告)号：US20180163744A1
公开(公告)日：2018-06-14
申请号：US15374676
申请日：2016-12-09
申请人： Hamilton Sundstrand Corporation
发明人： Sergey Mironets , Daniel Ursenbach
IPC分类号： F04D29/38 , F04D29/32
CPC分类号： F04D29/388 , B22F3/1055 , B22F5/04 , B22F7/062 , B23K9/044 , B23K15/0086 , B23K26/342 , B23K2101/001 , B23K2103/14 , B23P15/04 , B33Y80/00 , F01D5/147 , F01D5/286 , F02K3/06 , F04D29/023 , F04D29/324 , F04D29/325 , F05D2220/36 , F05D2230/31 , F05D2240/303 , F05D2300/121 , F05D2300/133 , F05D2300/171 , Y02P10/295
摘要： A method of making a sheath for an airfoil may include the steps of forming an upper sleeve and a lower sleeve, and forming a central portion bonded to the upper sleeve and the lower sleeve. The central portion may be formed by depositing a material on the upper sleeve and the lower sleeve. A portion of the material may be removed from at least one of the central portion, the upper sleeve, or the lower sleeve. The sheath may include a first flank, a central portion bonded to the first flank, and a second flank bonded to the central portion. The central portion may have a substantially uniform microstructure resulting from additive manufacturing.

2. 发明申请

US20180156232A1 COMPOSITE BLADE, COMPRISING A LEADING-EDGE REINFORCEMENT MADE OF ANOTHER MATERIAL 审中-公开
公开(公告)号：US20180156232A1
公开(公告)日：2018-06-07
申请号：US15570003
申请日：2016-04-28
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Alexandre DAMIENS , Frédéric Jean-Bernard POUZADOUX , Gilles Pierre-Marie NOTARIANNI
IPC分类号： F04D29/38
CPC分类号： F04D29/388 , F01D5/147 , F01D5/282 , F01D5/288 , F02C7/04 , F05D2250/73 , F05D2300/133 , F05D2300/603 , Y02T50/672
摘要： The invention relates to a blade made of composite material, provided with a reinforcement (17) made of a stronger material with regard to a leading edge (5) likely to be struck by solid objects, which comprises, under the aerodynamic portion of the blade, extensions (18, 19) attached to the blade root. According to the invention, the extensions (18, 19) are dissymmetric, the extension (18) located on the suction side being generally further back from the leading edge (5) than the extension (19) on the pressure side.

3. 发明授权

US09765634B2 Composite turbine engine blade with structural reinforcement 有权
公开(公告)号：US09765634B2
公开(公告)日：2017-09-19
申请号：US13949703
申请日：2013-07-24
申请人： SNECMA
发明人： Vincent Fameau , Aude Abadie
IPC分类号： F04D29/32 , F01D5/28 , F01D5/14 , F04D29/02
CPC分类号： F01D5/282 , F01D5/147 , F04D29/023 , F04D29/324 , F05D2220/36 , F05D2240/303 , F05D2300/133 , F05D2300/603
摘要： The invention relates to a turbine engine blade, particularly made of composite material, including: on the one hand, an airfoil (10) which exhibits: a leading edge (12), a trailing edge (14) opposite to the leading edge (12), intrados (16) and extrados (18) lateral walls which connect the leading edge (12) to the trailing edge (14), et on the other hand, a structural reinforcement (20) including a base (24) extending into two fins (26, 28) and designed to be applied to the leading edge (12) and the lateral walls (16, 18) of the airfoil (10), characterized in that the fins (26, 28) of the structural reinforcement (20) and/or the lateral walls (16, 18) of the airfoil (10) are shaped to maintain an assembly space (30) with nonzero thickness between at least one of the fins (26, 28) and the airfoil (10) when the structural reinforcement (20) is in place on the airfoil (10), said assembly space (30) extending from a free end (27, 29) of said fin (26, 28) toward the base (24) of the structural reinforcement (20).

4. 发明申请

US20170246707A1 FRICTION WELDING 审中-公开
公开(公告)号：US20170246707A1
公开(公告)日：2017-08-31
申请号：US15420627
申请日：2017-01-31
申请人： ROLLS-ROYCE PLC
发明人： Simon E. BRAY , Andrew R. WALPOLE , John P. E. FORSDIKE , Gavin J. BAXTER
IPC分类号： B23K20/12 , F01D5/28
CPC分类号： B23K20/129 , B23K20/12 , B23K20/1225 , B23K20/123 , B23K20/24 , B23K2101/001 , F01D5/28 , F05D2220/32 , F05D2300/133 , F05D2300/175
摘要： A method for friction welding of inter alia coarse grain superalloy components, involving conditioning a shear zone of components to be welded by; a) pre-determining temperature profile for which the material of the shear zone of the components approaches viscoplasticity but does not undergo undesirable phase transformations, b) introducing friction at one or both surfaces of the components to be welded to provide a pre-defined quantum of energy sufficient to generate a peak temperature of the temperature profile at that surface whilst simultaneously applying pressure to the surfaces which is below a pressure which will cause upset at the surface, c) withdrawing the friction and/or pressure allowing the heat to disperse by conduction through the shear zone; d) after the temperature at the surface falls below peak temperature, repeating steps b) and c); and repeating step d) as necessary until the pre-determined temperature gradient is achieved throughout the shear zone.

5. 发明申请

US20170218775A1 TURBINE BLADE ATTACHMENT RAILS FOR ATTACHMENT FILLET STRESS REDUCTION 审中-公开
公开(公告)号：US20170218775A1
公开(公告)日：2017-08-03
申请号：US15009328
申请日：2016-01-28
申请人： United Technologies Corporation
发明人： Charles Thistle , Mohamed Hassan
IPC分类号： F01D5/14 , F01D5/30 , F01D5/18 , F01D5/02
CPC分类号： F01D5/147 , F01D5/02 , F01D5/081 , F01D5/18 , F01D5/3007 , F05D2220/32 , F05D2230/20 , F05D2240/81 , F05D2260/20 , F05D2300/133 , F05D2300/174 , F05D2300/177 , Y02T50/676
摘要： The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a base, a first side, and a second side, a rail extending from the base of the load beam between the first side and the second side, a tooth running parallel to the longitudinal axis disposed on the first side of the load beam. The rail may comprise at least one of, a convex sidewall having a convex curvature, a concave sidewall having a concave curvature, or a vertical sidewall extending perpendicular to the base. The rail may comprise a sidewall comprising a sidewall step wherein the sidewall has a step cut into a portion of the rail. The rail may comprise a tapered sidewall wherein the tapered sidewall extends at an angle to the base.

6. 发明申请

US20160368238A1 EROSION AND WEAR PROTECTION FOR COMPOSITES AND PLATED POLYMERS 审中-公开
标题翻译：复合材料和涂料聚合物的腐蚀和磨损保护
公开(公告)号：US20160368238A1
公开(公告)日：2016-12-22
申请号：US14903880
申请日：2014-07-09
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： William Bogue , Grant O. Cook, III , Gary M. Lomasney , Joseph Parkos , Colin J. Kling , Charles R. Watson
IPC分类号： B32B3/26 , B32B15/20 , C25D5/56 , C23C16/06 , C25D11/20 , C25D9/04 , B32B15/08 , C23C14/20
CPC分类号： C25D5/56 , B05D5/00 , B05D7/02 , B22C7/023 , B22C9/043 , B22C9/10 , B28B1/24 , B28B7/342 , B28B11/04 , B28B11/243 , B32B3/263 , B32B7/12 , B32B15/04 , B32B15/08 , B32B15/20 , B32B37/12 , B32B37/1284 , B32B37/14 , B32B2255/10 , B32B2307/202 , B32B2307/554 , B32B2603/00 , B33Y10/00 , B33Y80/00 , B62D35/00 , C04B35/76 , C04B35/806 , C09D5/26 , C23C14/20 , C23C16/06 , C23C18/1633 , C23C18/165 , C23C18/2013 , C23C18/22 , C23C18/31 , C23C26/00 , C23C28/02 , C25D3/02 , C25D3/38 , C25D3/46 , C25D5/48 , C25D9/04 , C25D11/20 , F01D5/00 , F01D5/147 , F01D5/187 , F01D5/284 , F01D5/288 , F01D9/02 , F01D9/041 , F01D11/08 , F01D25/005 , F04D29/023 , F04D29/324 , F04D29/542 , F05D2220/32 , F05D2230/10 , F05D2230/22 , F05D2230/30 , F05D2230/312 , F05D2230/314 , F05D2240/122 , F05D2240/304 , F05D2300/10 , F05D2300/11 , F05D2300/121 , F05D2300/132 , F05D2300/133 , F05D2300/1616 , F05D2300/171 , F05D2300/177 , F05D2300/20 , F05D2300/30 , F05D2300/44 , F05D2300/501 , F05D2300/603 , F05D2300/611 , F05D2300/614 , F42B10/02
摘要： A composite component and a plated polymer component are disclosed. The composite component may comprise a body portion formed from an organic matrix composite, a first metal coating applied to a surface of the body portion, and an outer metal layer on the first metal coating that is erosion-resistant. The plated polymer component may comprise a polymer substrate, a metal plating layer applied to a surface of the polymer substrate, and at least one selectively thickened region in the metal plating layer. The at least one selectively thickened region may assist in protecting the plated polymer component against wear and/or erosion.
摘要翻译：公开了复合组分和镀覆聚合物组分。复合部件可以包括由有机基质复合材料形成的主体部分，施加到主体部分的表面上的第一金属涂层以及耐腐蚀的第一金属涂层上的外部金属层。镀覆的聚合物组分可以包括聚合物基材，施加到聚合物基材的表面的金属镀层，以及金属镀层中的至少一个选择性增稠区域。所述至少一个选择性增稠的区域可有助于保护镀覆的聚合物组分免受磨损和/或侵蚀。

7. 发明申请

US20160230574A1 VANE STAGES 审中-公开
公开(公告)号：US20160230574A1
公开(公告)日：2016-08-11
申请号：US14616274
申请日：2015-02-06
申请人： United Technologies Corporation
发明人： Mark E. Simonds , Steven J. Feigleson
IPC分类号： F01D9/04 , F01D11/00 , F01D25/00
CPC分类号： F01D9/041 , F01D11/001 , F01D11/003 , F01D25/005 , F01D25/243 , F01D25/246 , F05D2220/32 , F05D2230/10 , F05D2230/60 , F05D2240/12 , F05D2240/55 , F05D2240/80 , F05D2300/133 , F05D2300/603
摘要： A vane stage includes an arcuate platform defining a axial centerline axis having a pair of flanges that extend radially inward from the platform. The flanges are axially spaced from one another and from respective forward and aft ends of the platform. The vane stage includes a vane extending radially outward from the platform and a seal carrier mounted to the flanges of the platform. A method for constructing a vane stage includes sliding a seal carrier between flanges of an arcuate platform. Each flange includes at least a pair of through holes and interfaces with a respective axial side of the seal carrier. The method includes drilling through holes in each axial side of the seal carrier by using the through holes of each flange as guides.
摘要翻译：叶片台包括限定具有从平台径向向内延伸的一对凸缘的轴向中心线轴的弓形平台。凸缘彼此轴向间隔开并且与平台的相应的前后端部间隔开。叶片台包括从平台径向向外延伸的叶片和安装到平台的凸缘的密封载体。用于构造叶片台的方法包括将密封载体滑动到弓形平台的凸缘之间。每个凸缘包括至少一对通孔和与密封载体的相应轴向侧的界面。该方法包括通过使用每个凸缘的通孔作为引导件，在密封载体的每个轴向侧的孔中钻孔。

8. 发明授权

US09410431B2 Nose cone assembly 有权
标题翻译：鼻锥组装
公开(公告)号：US09410431B2
公开(公告)日：2016-08-09
申请号：US13290225
申请日：2011-11-07
申请人： Kristofer J. Bottome , Paul Mason , Eric P. Ravey
发明人： Kristofer J. Bottome , Paul Mason , Eric P. Ravey
IPC分类号： F01D5/06 , F02C7/04
CPC分类号： F02C7/04 , F01D5/066 , F05D2220/32 , F05D2260/31 , F05D2300/121 , F05D2300/133 , F05D2300/171 , F05D2300/2102 , F05D2300/44 , F05D2300/603 , F05D2300/614 , Y02T50/672 , Y02T50/673
摘要： A nose cone assembly is provided comprising a nose cone 104, a support ring 106 on which the nose cone 104 is mounted, and an insulating layer 110 disposed between the nose cone 104 and the support ring 106, the insulating layer 110 at least partially comprising glass fibers.A composite nose cone is also provided comprising an attachment region A, in which composite fibers are oriented substantially perpendicular to an axis of rotation of the nose cone 104, and an impact region I, in which composite fibers are oriented substantially parallel to the axis of rotation of the nose cone 104. Also provided is a support ring 106 for a nose cone assembly, the support ring 106 comprising an annular main body 140 and an annular projecting attachment flange 142, the attachment flange 142 terminating in a plurality of circumferentially spaced attachment tabs 144, wherein the attachment flange 142 forms with the main body 140 a cross section having at least two C curves 160, 162.
摘要翻译：提供鼻锥组件，其包括鼻锥体104，安装鼻锥体104的支撑环106以及设置在鼻锥体104和支撑环106之间的绝缘层110，绝缘层110至少部分地包括玻璃纤维。还提供了复合鼻锥，其包括附接区域A，其中复合纤维被定向成基本上垂直于鼻锥体104的旋转轴线，以及冲击区域I，其中复合纤维被定向成基本上平行于鼻锥体104的旋转。还提供了用于鼻锥组件的支撑环106，支撑环106包括环形主体140和环形突出的附接凸缘142，附接凸缘142终止于多个周向间隔开的附件凸片144，其中附接凸缘142与主体140形成具有至少两个C曲线160,162的横截面。

9. 发明授权

US09394791B2 Rotor 有权
标题翻译：转子
公开(公告)号：US09394791B2
公开(公告)日：2016-07-19
申请号：US13767869
申请日：2013-02-14
申请人： Bosch Mahle Turbo Systems GmbH & Co. KG
发明人： Michal Klusacek
IPC分类号： F01D5/02 , F01D5/04 , F02C6/12
CPC分类号： F01D5/02 , F01D5/048 , F02C6/12 , F05D2220/40 , F05D2300/133 , F05D2300/611
摘要： A rotor of a charging device may include at least two parts fastened to each other and configured to enclose a hollow space. The two parts may be fastened to each other via a negative pressure within the hollow space.
摘要翻译：充电装置的转子可以包括彼此紧固并构造成封闭中空空间的至少两个部件。两个部分可以通过中空空间内的负压彼此紧固。

10. 发明申请

US20160175988A1 METHOD TO IMMOBILIZE AN ENTRAPPED CONTAMINANT WITHIN A HONEYCOMB STRUCTURE 审中-公开
标题翻译：在蜂窝结构中固定加入的污染物的方法
公开(公告)号：US20160175988A1
公开(公告)日：2016-06-23
申请号：US14909323
申请日：2014-07-29
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Brian K. Holland , William Bogue , Jeffrey Denton
IPC分类号： B23K31/02 , G01N21/94 , F02K1/78 , G01N21/3563
CPC分类号： B23K31/02 , F01D5/005 , F02K1/78 , F05D2230/232 , F05D2230/40 , F05D2300/133 , F05D2300/174 , F05D2300/701 , G01N21/3563 , G01N21/552 , G01N21/94 , G01N2021/3595 , G01N2201/0221
摘要： A method of immobilizing a contaminant within a component includes identifying the contaminate; and thermally processing the component via a specific thermal cycle related to the contaminate. A method of repairing a component includes immobilizing a contaminant within the component; and weld repairing the component subsequent to immobilizing the contaminant. An aerospace component includes a honeycomb structure with a thermally decomposed contaminate and a weld repair.
摘要翻译：将组分中污染物固定的方法包括识别污染物; 并通过与污染物相关的特定热循环热处理该组件。修复部件的方法包括将污染物固定在所述部件内; 并在固定污染物之后焊接修补部件。航空航天部件包括具有热分解污染物和焊接修复的蜂窝结构。

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