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1. 发明申请

US20190032184A1 METHOD TO PREVENT ABNORMAL GRAIN GROWTH FOR BETA ANNEALED TI-6AL-4V FORGINGS 审中-公开
公开(公告)号：US20190032184A1
公开(公告)日：2019-01-31
申请号：US16151512
申请日：2018-10-04
申请人： Spirit AeroSystems, Inc.
发明人： Rahbar Nasserrafi , Gerald E. Hicks , Michael A. Walker , Craig M. Clasper
IPC分类号： C22F1/18 , C22C14/00 , C22F1/02
CPC分类号： C22F1/183 , C22C14/00 , C22F1/02
摘要： A method for heat-treating a titanium alloy, such as Ti-6Al-4V. The method may occur after or include a step of forging the titanium alloy such that localized, highly deformed grains are formed in the titanium alloy. Then the method may include steps of recrystallization annealing the titanium alloy by heating the titanium alloy to a temperature in a range between 30° F. to 200° F. below beta transus of the titanium alloy for 1 hour to 6 hours and then furnace cooling of the titanium alloy to 1200° F. to 1500° F. at a rate of 50° F. to 500° F. per hour. Following the recrystallization annealing, the method may include beta annealing the titanium alloy. These steps may be performed in a single heat treating cycle.

2. 发明授权

US09951405B2 Localized heat treating of net shape titanium parts 有权
公开(公告)号：US09951405B2
公开(公告)日：2018-04-24
申请号：US14613437
申请日：2015-02-04
申请人： Spirit AeroSystems, Inc.
发明人： Rahbar Nasserrafi , Steven Paul Meyer
IPC分类号： C22F1/00 , C22F1/18 , C22C14/00
CPC分类号： C22F1/008 , C22C14/00 , C22F1/183
摘要： A system and method for heat-treating a titanium part. The system may include foil, adhesive tape, and a localized heat source. The foil may include two sheets of foil made of a material more reactive (more prone to oxidize) than the titanium part, and the localized heat source may include a heating element mostly surrounded by insulation. The method may include taping the foil to opposing sides of the titanium part, thus sealing a portion of the titanium part to be heat treated from external atmosphere. The method may also include heating and placing the localized heat source near or against the foil until heat treating is complete. A small amount of air remaining between the heated foil and the titanium part has a preferential reaction with the foil, since it is more reactive than the titanium part. This prevents oxidation of the titanium part during localized heat treating.

3. 发明申请

US20160222498A1 LOCALIZED HEAT TREATING OF NET SHAPE TITANIUM PARTS 有权
标题翻译：网状钛片局部热处理
公开(公告)号：US20160222498A1
公开(公告)日：2016-08-04
申请号：US14613437
申请日：2015-02-04
申请人： Spirit AeroSystems, Inc.
发明人： Rahbar Nasserrafi , Steven Paul Meyer
IPC分类号： C22F1/00 , C22C14/00 , C22F1/18
CPC分类号： C22F1/008 , C22C14/00 , C22F1/183
摘要： A system and method for heat-treating a titanium part. The system may include foil, adhesive tape, and a localized heat source. The foil may include two sheets of foil made of a material more reactive (more prone to oxidize) than the titanium part, and the localized heat source may include a heating element mostly surrounded by insulation. The method may include taping the foil to opposing sides of the titanium part, thus sealing a portion of the titanium part to be heat treated from external atmosphere. The method may also include heating and placing the localized heat source near or against the foil until heat treating is complete. A small amount of air remaining between the heated foil and the titanium part has a preferential reaction with the foil, since it is more reactive than the titanium part. This prevents oxidation of the titanium part during localized heat treating.
摘要翻译：一种用于热处理钛部件的系统和方法。该系统可以包括箔，胶带和局部热源。箔可以包括由比钛部更多的反应性（更易于氧化）的材料制成的两片箔，并且局部热源可以包括主要被绝缘包围的加热元件。该方法可以包括将箔粘贴到钛部分的相对侧，从而将外部气氛中待热处理的钛部分的一部分密封。该方法还可以包括加热和将局部热源放置在箔片附近或靠近箔片上，直到热处理完成。加热的箔和钛部分之间剩余的少量空气与箔具有优先的反应，因为它比钛部分更具反应性。这防止了局部热处理期间钛部件的氧化。

4. 发明公开

US20230201950A1 METHOD OF BONDING METALLIC COMPONENTS TO FORM MACHINING PREFORM 审中-公开
公开(公告)号：US20230201950A1
公开(公告)日：2023-06-29
申请号：US17982129
申请日：2022-11-07
申请人： Spirit AeroSystems, Inc.
发明人： James Michael Wagner , Rahbar Nasserrafi , Paul Ray Toivonen , Heath Edward Misak , Craig Matthew Clasper
IPC分类号： B23K11/20 , B23K11/00
CPC分类号： B23K11/20 , B23K11/0006
摘要： A method of bonding two or more metallic components into a single piece. The bonding surfaces of the metallic components are protected from reaction with the environment. A force is applied to the metallic components to push the bonding surfaces together. Simultaneous with applying the force, an electric current is passed through the bonding surfaces to joule heat and weld the bonding surfaces together to form the single piece. The bonding surfaces may be protected by plating with a noble metal, applying a coating, shielding with a noble gas, or placing into a vacuum. A press may be used to apply the force. The force and the electric current may be sufficient to push out metal around the joint of the bonding surfaces, and at least one of the bonding surfaces may be drafted to facilitate pushing out the metal. The electric current may be pulsed to induce electroplasticity.

5. 发明授权

US10822682B2 Method to prevent abnormal grain growth for beta annealed Ti—6AL—4V forgings 有权
公开(公告)号：US10822682B2
公开(公告)日：2020-11-03
申请号：US16151512
申请日：2018-10-04
申请人： Spirit AeroSystems, Inc.
发明人： Rahbar Nasserrafi , Gerald E. Hicks , Michael A. Walker , Craig M. Clasper
IPC分类号： C22F1/18 , C22F1/02 , C22C14/00
摘要： A method for heat-treating a titanium alloy, such as Ti-6Al-4V. The method may occur after or include a step of forging the titanium alloy such that localized, highly deformed grains are formed in the titanium alloy. Then the method may include steps of recrystallization annealing the titanium alloy by heating the titanium alloy to a temperature in a range between 30° F. to 200° F. below beta transus of the titanium alloy for 1 hour to 6 hours and then furnace cooling of the titanium alloy to 1200° F. to 1500° F. at a rate of 50° F. to 500° F. per hour. Following the recrystallization annealing, the method may include beta annealing the titanium alloy. These steps may be performed in a single heat treating cycle.

6. 发明授权

US10307856B2 Method for joule heating diffusion bonded honeycomb core 有权
公开(公告)号：US10307856B2
公开(公告)日：2019-06-04
申请号：US14938549
申请日：2015-11-11
申请人： SPIRIT AEROSYSTEMS, INC.
发明人： Rahbar Nasserrafi , Dennis R. Lebeda , Michael Basala
IPC分类号： B23K11/00
摘要： A joule-heating press and method for manufacturing a metallic honeycomb core via diffusion bonding. The method may include printing a pattern of strips of a stop-off material to surfaces of a plurality of sheets of metal at locations where diffusion bonding is not desired and stacking the sheets of metal together in a sequence for forming the honeycomb core. Then the method may include steps of pressing the sheets of metal together between two press plates made of conductive material and applying electric current to the conductive material of the press plates. This allows current to flow through a thickness of the sheets of metal and the sheets of metal are thereby diffusion bonded to each other via joule heating at locations absent the stop-off material. Finally, the method may include a step of expanding the sheets of metal into the honeycomb core.

7. 发明申请

US20160047022A1 ALUMINUM-COPPER ALLOYS WITH IMPROVED STRENGTH 审中-公开
标题翻译：具有改进强度的铝 - 铜合金
公开(公告)号：US20160047022A1
公开(公告)日：2016-02-18
申请号：US14011320
申请日：2013-08-27
申请人： SPIRIT AEROSYSTEMS, INC.
发明人： Rahbar Nasserrafi , David E. Jakstis , Gerald E. Hicks , Darrell Wade
IPC分类号： C22F1/057 , C22C21/16 , C22C21/18 , C22F1/00
CPC分类号： C22F1/057 , C22C21/12 , C22C21/16 , C22C21/18 , C22F1/002
摘要： Aluminum alloys are provided that can comprise boron and vanadium and high amounts of titanium and zirconium. The aluminum alloys described herein can exhibit superior tensile properties at both room temperature and elevated temperatures and still maintain desirable ductility. The aluminum alloys can be used in applications where resistance to fatigue and breakdown at elevated temperatures is desirable, which includes applications in the aerospace and aeronautical fields.
摘要翻译：提供的铝合金可以包含硼和钒以及大量的钛和锆。本文所述的铝合金在室温和高温下都能表现出优异的拉伸性能，并且仍然保持理想的延展性。铝合金可用于耐高温下耐疲劳和击穿的应用，包括在航空和航空领域的应用。

8. 发明申请

US20220152939A1 SYSTEM AND METHOD FOR WELDING THERMOPLASTIC COMPONENTS TO CREATE COMPOSITE STRUCTURE 有权
公开(公告)号：US20220152939A1
公开(公告)日：2022-05-19
申请号：US17590147
申请日：2022-02-01
申请人： Spirit AeroSystems, Inc.
发明人： Mark Wadsworth , Kerrick Robert Dando , Rahbar Nasserrafi
IPC分类号： B29C65/20 , B29C65/30 , B29C65/00
摘要： A system and method for welding thermoplastic components by positioning and moving a heated plate between the components to melt their respective faying surfaces, and as the plate moves, pressing the components together so that the melted faying surfaces bond together as they cool and re-solidify, thereby creating a composite structure. The plate has a heated portion which is positioned between and heated to melt a portion of the first and second faying surfaces. A manipulator mechanism moves the plate along an interface from between the portion to between a series of subsequent portions of the first and second faying surfaces, thereby welding the thermoplastic components along the entire interface to create the composite structure. An injection device may also move behind the plate and reciprocally inject a polymer between the first and second faying surfaces to provide toughness and crack arresting properties.

9. 发明授权

US10094013B2 Method to prevent abnormal grain growth for beta annealed TI-6AL-4V forgings 有权
公开(公告)号：US10094013B2
公开(公告)日：2018-10-09
申请号：US14972972
申请日：2015-12-17
申请人： Spirit AeroSystems, Inc.
发明人： Rahbar Nasserrafi , Gerald E. Hicks , Michael A. Walker , Craig M. Clasper
IPC分类号： C22F1/18 , C22F1/02 , C22C14/00
摘要： A method for heat-treating a titanium alloy, such as Ti-6Al-4V. The method may occur after or include a step of forging the titanium alloy such that localized, highly deformed grains are formed in the titanium alloy. Then the method may include steps of recrystallization annealing the titanium alloy by heating the titanium alloy to a temperature in a range between 30° F. to 200° F. below beta transus of the titanium alloy for 1 hour to 6 hours and then furnace cooling of the titanium alloy to 1200° F. to 1500° F. at a rate of 50° F. to 500° F. per hour. Following the recrystallization annealing, the method may include beta annealing the titanium alloy. These steps may be performed in a single heat treating cycle.

10. 发明授权

US09649728B2 Bifurcation honeycomb sandwich structure with optimized doubler 有权
公开(公告)号：US09649728B2
公开(公告)日：2017-05-16
申请号：US14530784
申请日：2014-11-02
申请人： Spirit AeroSystems, Inc.
发明人： Rahbar Nasserrafi , Darrell A. Wade , Thanh A. Le
IPC分类号： B23K31/00 , B23K31/02 , B21D47/04
CPC分类号： B23K31/02 , B21D47/04
摘要： A method of shaping a metallic honeycomb panel using a continuous drive sheet. The metallic honeycomb panel may have a perforated upper sheet, a non-perforated lower sheet, and a metal honeycomb core fixed between the upper and lower sheets. The method may include the steps of designing and manufacturing the drive sheet using finite element analysis (FEA) and criteria regarding shaping of the metallic honeycomb panel, then welding the drive sheet to the lower face of the lower sheet. The drive sheet may cover all of the lower face of the lower sheet and may have varying thicknesses determined based on the criteria and the FEA. The method may also include the steps of heating the drive sheet and metallic honeycomb panel to a creep forming or hot-stretch forming temperature and urging the metallic honeycomb panel and drive sheet into a male or female die mold to be shaped.

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