专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20170307311A1 Simple Heat Exchanger Using Super Alloy Materials for Challenging Applications 审中-公开
公开(公告)号：US20170307311A1
公开(公告)日：2017-10-26
申请号：US15138491
申请日：2016-04-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Frederick M. Schwarz , Paul W. Duesler
IPC分类号： F28F21/08 , F28F1/28 , F02C9/18 , F02C3/04 , F28F1/40 , F02C7/18 , F28D1/047
CPC分类号： F28F21/087 , F01D9/065 , F02C7/185 , F02K3/02 , F05D2260/213 , F05D2300/175 , F05D2300/182 , F28D1/0475 , F28D7/12 , F28F1/28 , F28F1/40 , Y02T50/676
摘要： A heat exchanger system for use in a gas turbine engine has a plurality of circumferentially spaced heat exchangers. The spaced heat exchangers are formed of a nickel alloy material including more than 50-percent by volume gamma-prime intermetallic phase material. A gas turbine engine is also disclosed.

2. 发明申请

US20170159155A1 Nb-Silicide Based Composites, High-Temperature Component and High-Temperature Heat Engine Employing the Same 审中-公开
公开(公告)号：US20170159155A1
公开(公告)日：2017-06-08
申请号：US14913099
申请日：2015-05-25
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Yuting WANG
IPC分类号： C22C27/02 , F01D9/04 , F01D25/00 , F01D5/28
CPC分类号： C22C27/02 , B22F5/04 , C22C29/18 , F01D5/28 , F01D9/041 , F01D25/005 , F05D2220/32 , F05D2300/13 , F05D2300/17 , F05D2300/182 , F05D2300/6032 , Y02T50/672
摘要： To provide a Nb-silicide based composite achieving both mechanical characteristics and toughness at high levels in an ultrahigh temperature region (1200° C. or more) as well as a high-temperature component and a high-temperature heat engine which employ the same. The Nb-silicide based composite according to the present invention includes 13 to 23 at % of Si, 2.0 to 10 at % of Cr, 5.0 to 23 at % of Ti, 0.0 to 6.0 at % of Al, 0.10 to 8.0 at % of Zr, 1.0 to 8.0 at % of Hf, 0.0 to 2.0 at % of W, 0.10 to 6.0 at % of Sn, 3.1 to 8.0 at % of Mo, 0.20 to 5.0 at % of B, and the balance being Nb and inevitable impurities.

3. 发明授权

US09422814B2 Repair of a coating on a turbine component 有权
标题翻译：修复涡轮机部件上的涂层
公开(公告)号：US09422814B2
公开(公告)日：2016-08-23
申请号：US12836107
申请日：2010-07-14
申请人： Glenn Lee , Om Prakash Yadav , Dylan Lim
发明人： Glenn Lee , Om Prakash Yadav , Dylan Lim
IPC分类号： F01D5/28 , F01D5/00 , C23C10/02 , C23C10/04 , C23C10/18 , C23C10/28 , C23C10/30
CPC分类号： C23C4/01 , B24C1/04 , C23C4/02 , C23C4/06 , C23C4/134 , C23C10/02 , C23C10/04 , C23C10/18 , C23C10/28 , C23C10/30 , F01D5/005 , F01D5/288 , F01D9/02 , F01D25/005 , F05D2220/32 , F05D2230/312 , F05D2230/40 , F05D2230/80 , F05D2230/90 , F05D2300/182 , Y02T50/673 , Y10T29/49318
摘要： A method is provided for repairing an area of damaged coating on a component of a turbine module in a gas turbine engine, the component formed of a base material having a diffusion coating applied to the base material. The repair may be accomplished in place by directly heating the area to which a touch-up coating material has been applied with a hot gas plasma without the need to place the component in an oven for curing and heat treatment of the touch-up coating applied to the damaged area.
摘要翻译：提供了一种用于修复燃气涡轮发动机中的涡轮机模块的部件上的损坏涂层的区域的方法，该部件由具有施加到基材的扩散涂层的基材形成。可以通过使用热气体等离子体直接加热已经涂覆有润色涂层材料的区域来完成修复，而不需要将组件放置在烘箱中用于固化和加热涂覆的涂覆涂层到受损区域。

4. 发明申请

US20180258776A1 METHOD OF MANUFACTURING A COATED TURBINE BLADE AND A COATED TURBINE VANE 审中-公开
公开(公告)号：US20180258776A1
公开(公告)日：2018-09-13
申请号：US15915200
申请日：2018-03-08
申请人： ROLLS-ROYCE plc
发明人： Andrew Hewitt , Ian W. R. Harrogate
IPC分类号： F01D5/28 , F01D9/04 , C23C28/00
CPC分类号： F01D5/288 , B22F3/1055 , B22F5/04 , B33Y80/00 , C23C4/02 , C23C4/11 , C23C28/321 , C23C28/3215 , C23C28/3455 , F01D9/041 , F05D2230/312 , F05D2230/313 , F05D2230/90 , F05D2240/12 , F05D2240/121 , F05D2240/122 , F05D2240/80 , F05D2250/294 , F05D2300/173 , F05D2300/182 , F05D2300/2118 , F05D2300/611
摘要： A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).

5. 发明授权

US09803482B2 Rotor for a turbine or a compressor or a turbine/compressor geometry 有权
公开(公告)号：US09803482B2
公开(公告)日：2017-10-31
申请号：US14598176
申请日：2015-01-15
申请人： Bosch Mahle Turbo Systems GmbH & Co. KG
发明人： Thomas Striedelmeyer , Jochen Schray , Andreas Prang , Christian Holzschuh
IPC分类号： F01D5/04 , F04D29/20 , F01D5/02 , F04D29/26 , B23K1/00 , F04D29/02 , B23K101/00
CPC分类号： F01D5/025 , B23K1/0018 , B23K2101/001 , F04D29/023 , F04D29/20 , F04D29/266 , F05D2220/40 , F05D2230/232 , F05D2230/238 , F05D2230/60 , F05D2230/90 , F05D2240/60 , F05D2300/174 , F05D2300/182 , Y10T29/49243 , Y10T29/49245
摘要： A rotor for at least one of a turbine and a compressor of a supercharging device may include a shaft defining an axis of rotation and at least one impeller. The at least one impeller may have a thread which is arranged coaxially to the axis of rotation. The shaft may include a complementary thread which is arranged coaxially to the axis of rotation. The shaft and the at least one impeller may be secured together via the respective threads. The shaft and the at least one impeller may be fixed with respect to one another via at least one of a soldered connection, a welded connection, an adhesive bond, a clamped connection and a crystallization connection.

6. 发明申请

US20160326621A1 REPAIR OF A COATING ON A TURBINE COMPONENT 审中-公开
标题翻译：维修涡轮机组件上的涂层
公开(公告)号：US20160326621A1
公开(公告)日：2016-11-10
申请号：US15215834
申请日：2016-07-21
申请人： United Technologies Corporation
发明人： Glenn Lee , Om Prakash Yadav , Dylan Lim
IPC分类号： C23C4/01 , F01D25/00 , C23C4/06 , C23C4/02 , C23C4/134 , F01D9/02 , B24C1/04
CPC分类号： C23C4/01 , B24C1/04 , C23C4/02 , C23C4/06 , C23C4/134 , C23C10/02 , C23C10/04 , C23C10/18 , C23C10/28 , C23C10/30 , F01D5/005 , F01D5/288 , F01D9/02 , F01D25/005 , F05D2220/32 , F05D2230/312 , F05D2230/40 , F05D2230/80 , F05D2230/90 , F05D2300/182 , Y02T50/673 , Y10T29/49318
摘要： A method is provided for repairing an area of damaged coating on a component of a turbine module in a gas turbine engine, the component formed of a base material having a diffusion coating applied to the base material. The repair may be accomplished in place by directly heating the area to which a touch-up coating material has been applied with a hot gas plasma without the need to place the component in an oven for curing and heat treatment of the touch-up coating applied to the damaged area.
摘要翻译：提供了一种用于修复燃气涡轮发动机中的涡轮机模块的部件上的损坏涂层的区域的方法，该部件由具有施加到基材的扩散涂层的基材形成。可以通过使用热气体等离子体直接加热已经涂覆有润色涂层材料的区域来完成修复，而不需要将组件放置在烘箱中用于固化和加热涂覆的涂覆涂层到受损区域。

7. 发明申请

US20130084190A1 TITANIUM ALUMINIDE ARTICLES WITH IMPROVED SURFACE FINISH AND METHODS FOR THEIR MANUFACTURE 审中-公开
标题翻译：具有改进的表面处理的钛酸钡文章及其制造方法
公开(公告)号：US20130084190A1
公开(公告)日：2013-04-04
申请号：US13250231
申请日：2011-09-30
申请人： Bernard Patrick BEWLAY , Bruce KNUDSEN
发明人： Bernard Patrick BEWLAY , Bruce KNUDSEN
IPC分类号： F01D5/14 , B32B3/00 , B24B1/00
CPC分类号： B24B21/165 , B24B1/00 , B24B19/14 , C21D7/04 , C22F1/183 , F01D5/28 , F01D5/286 , F05D2300/182 , F05D2300/516 , Y02T50/672 , Y02T50/673 , Y10T428/24802
摘要： Titanium-containing articles having improved surface finishes and methods for improving surface finishes on titanium containing articles are provided. One method includes passing an abrasive medium across a surface of an titanium aluminide alloy-containing article, for example, a turbine blade, at high linear speed; deforming the surface of the titanium aluminide alloy-containing article with the abrasive medium and reducing a surface roughness of the surface of the titanium aluminide alloy-containing article and improving the surface finish of the surface. Surface finishes of 20 microinches Ra or less can be obtained. Though aspects of the invention can be used in fabricating high performance turbine blades, the methods disclosed can be applied to the treatment of any titanium-containing article for which it is difficult to obtain an improved surface finish.
摘要翻译：提供了具有改进的表面光洁度的含钛制品和用于改善含钛制品的表面光洁度的方法。一种方法包括使磨料介质以高线速度穿过含钛铝化物合金制品例如涡轮叶片的表面; 使用研磨介质使含铝化铝合金的制品的表面变形，并降低含钛铝合金制品的表面的表面粗糙度并改善表面的表面光洁度。可以获得20微英寸或更小的表面光洁度。尽管本发明的方面可以用于制造高性能涡轮叶片，但是所公开的方法可以应用于难以获得改进的表面光洁度的任何含钛制品的处理。

8. 发明申请

US20180163291A1 HIGH-TEMPERATURE PROTECTIVE LAYER FOR TITANIUM ALUMINIDE ALLOYS 审中-公开
公开(公告)号：US20180163291A1
公开(公告)日：2018-06-14
申请号：US15825170
申请日：2017-11-29
申请人： MTU Aero Engines AG
发明人： Martin SCHLOFFER , Heiko WARNECKE
IPC分类号： C23C14/16 , B32B15/01 , C22C14/00
CPC分类号： C23C14/165 , B32B15/01 , B32B15/016 , C22C14/00 , C22C21/003 , C22C30/00 , C23C30/00 , F01D5/288 , F05D2300/121 , F05D2300/174 , F05D2300/182
摘要： Disclosed is a process for coating a component of a TiAl alloy in order to improve the high-temperature resistance of the component. The process comprises depositing a Pt- and Cr-free protective layer alloy comprising Ti, Al, Nb, Mo and B and optionally one or more of W, Si, C, Zr, Y, Hf, Er and Gd on the component by physical vapor deposition at a temperature of less than or equal to 600° C. The protective layer alloy has a higher Al content than the TiAl alloy of the component. A coated component made by this process is also disclosed.

9. 发明授权

US09970307B2 Turbine nozzles with slip joints impregnated by oxidation-resistant sealing material and methods for the production thereof 有权
公开(公告)号：US09970307B2
公开(公告)日：2018-05-15
申请号：US14219622
申请日：2014-03-19
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Shezan Kanjiyani , Bradley Reed Tucker , Natalie Wali , Daniel Hicks , Bill Macelroy
IPC分类号： F01D11/00 , B23P15/04 , B23K1/00 , F01D9/04 , F01D17/16 , B23K101/00 , F01D5/28
CPC分类号： F01D11/005 , B23K1/0018 , B23K2101/001 , B23P15/04 , F01D5/28 , F01D9/041 , F01D9/042 , F01D11/00 , F01D17/162 , F05D2300/182 , Y02T50/673 , Y10T29/49321
摘要： Embodiments of a turbine nozzle having slip joints impregnated by an oxidation-resistant sealing material are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the method includes providing a support ring, a slip joint ring substantially concentric with the support ring and radially spaced apart therefrom, and a plurality of vanes fixedly coupled to the support ring. The plurality of vanes extends radially from the support ring into a plurality of circumferentially-spaced slots provided in the slip joint ring to form a plurality of slip joints therewith. The plurality of slip joints are impregnated with a silicon-modified aluminide sealing material. The silicon-modified aluminide sealing material impedes gas flow into the radial slip joints during operation of the turbine nozzle, while also fracturing to permit relative radial movement between the plurality of vanes and the slip joint ring along the plurality of slip joints.

10. 发明申请

US20140227080A1 SEAL SUPPORT OF TITANIUM ALUMINIDE FOR A TURBOMACHINE 审中-公开
标题翻译：钛酸钡的密封支持用于涡轮机
公开(公告)号：US20140227080A1
公开(公告)日：2014-08-14
申请号：US14166167
申请日：2014-01-28
申请人： MTU Aero Engines AG
发明人： Frank STIEHLER , Stephan KLAEN , Stefan BUSAM , Bernhard THEIS
IPC分类号： F02C7/28
CPC分类号： F02C7/28 , F01D11/001 , F05D2300/182 , Y10T29/49297
摘要： Disclosed is a turbomachine having an annular flow duct and a housing structure surrounding the flow duct and a multiplicity of guide vanes and rotor blades which are arranged in the flow duct. The rotor blades are rotatably accommodated in the housing structure whereas the guide vanes are fixed in the housing structure, a plurality of guide vanes forming an annular guide vane ring. The housing structure has a seal in the region of the radially inner flow duct boundary in order to prevent hot gas escaping from the flow duct, which seal is arranged on guide vane roots of the guide vanes of the guide vane ring via a seal support and forms a seal against a rotatable seal surface, the seal support being formed from an intermetallic material, in particular a TiAl material.
摘要翻译：公开了一种涡轮机，其具有环形流动管道和围绕流动管道的壳体结构以及布置在流动管道中的多个导向叶片和转子叶片。转子叶片可旋转地容纳在壳体结构中，而导叶固定在壳体结构中，多个导叶形成环形导叶环。壳体结构在径向内流道边界的区域中具有密封，以防止热气从流动管道逸出，该密封件通过密封支撑件设置在导向叶片环的导向叶片的导叶根部上，形成对可旋转密封表面的密封，密封支撑由金属间材料，特别是TiAl材料形成。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式