专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

41. 发明授权

US09157142B2 Process for the vapor phase aluminization of a turbomachine metal part and donor liner and turbomachine vane comprising such a liner 有权
标题翻译：用于涡轮机金属部件和供体衬管和包括这种衬垫的涡轮机叶片的气相镀铝的方法
公开(公告)号：US09157142B2
公开(公告)日：2015-10-13
申请号：US13473200
申请日：2012-05-16
申请人： Maxime Francois Roger Carlin , Lucie Marie Ida Lanciaux
发明人： Maxime Francois Roger Carlin , Lucie Marie Ida Lanciaux
IPC分类号： F01D9/06 , C23C10/48 , F01D5/18 , C23C10/08 , C23C16/04 , C23C16/12 , C23C16/448 , F01D5/28
CPC分类号： C23C10/48 , C23C10/08 , C23C16/045 , C23C16/12 , C23C16/4488 , F01D5/189 , F01D5/288 , F01D9/065 , F05D2230/313 , F05D2230/314 , F05D2300/121 , Y02T50/67 , Y10T428/265 , Y10T428/31678
摘要： An aluminization process by vapor phase deposition for high-temperature oxidation protection of a metal turbomachine part. The part including a cavity into which a metal component is introduced and assembled from an opening in the part. A halide is formed by reaction between a halogen and a metal donor containing aluminum, then the halide is transported by a carrier gas in order to come into contact with the metal part, wherein the metal component has first, before the implementation of the process, been surface-enriched with aluminum in order to serve as an aluminum donor.
摘要翻译：通过气相沉积法对金属涡轮机部件进行高温氧化保护的镀铝工艺。所述部件包括空腔，金属部件从部件中的开口引入并组装到该腔中。通过卤素和含有铝的金属供体之间的反应形成卤化物，然后通过载气输送卤化物以与金属部分接触，其中金属组分首先在实施前，用铝表面富集，以作为铝供体。

42. 发明申请

US20150203954A1 COATING SYSTEM AND PROCESS 有权
标题翻译：涂料系统和工艺
公开(公告)号：US20150203954A1
公开(公告)日：2015-07-23
申请号：US14413726
申请日：2013-07-31
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： James W Neal , David A Litton , Russell A Beers , Benjamin Joseph Zimmerman , Michael J. Maloney
IPC分类号： C23C14/04 , C23C14/30
CPC分类号： C23C14/042 , C23C14/044 , C23C14/30 , F05D2230/313
摘要： A coating system for coating a part (10), such as a turbine blade or vane, has a mask (14) positioned adjacent to a first portion (16) of the part (10) to be coated and a mechanism (30) for moving the mask (14) relative to the part (10). The mechanism (30) may be a gear mechanism or a magnetic mechanism.
摘要翻译：用于涂覆诸如涡轮叶片或叶片的部分（10）的涂覆系统具有邻近待涂覆的部分（10）的第一部分（16）定位的掩模（14）和用于相对于所述部件（10）移动所述面罩（14）。机构（30）可以是齿轮机构或磁性机构。

43. 发明授权

US09068469B2 Gas turbine engines with abradable turbine seal assemblies 有权
标题翻译：具有可磨损涡轮机密封组件的燃气涡轮发动机
公开(公告)号：US09068469B2
公开(公告)日：2015-06-30
申请号：US13224035
申请日：2011-09-01
申请人： Bradley Reed Tucker , Jason Smoke , Mark C. Morris
发明人： Bradley Reed Tucker , Jason Smoke , Mark C. Morris
IPC分类号： F01D11/12 , F01D11/00
CPC分类号： F01D11/122 , F01D11/006 , F05D2230/313 , F05D2240/55 , F05D2300/123 , Y10T29/49297
摘要： A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.
摘要翻译：燃气涡轮发动机的涡轮部分包括壳体，转子组件和密封组件。转子组件包括转子盘，联接到转子盘的转子平台以及从转子平台延伸到主流热气流动路径中的转子叶片。定子组件包括具有定子叶片的定子平台，定子叶片从定子平台延伸到主流热气流动路径中。所述密封组件包括从所述转子平台沿第一方向延伸的第一流动障碍物，从所述定子平台沿第二方向延伸的第二流动障碍物，所述第一流动障碍物轴向地与所述第二流动盘旋重叠，使得所述第二流动盘旋器为内部在径向方向上的第一流动捣碎器，施加到第一流动捣碎器的硬涂层，以及施加到第二流动捣碎器的可磨损涂层。

44. 发明申请

US20150030459A1 TURBOMACHINE COMPONENT WITH A PARTING JOINT, AND A STEAM TURBINE COMPRISING SAID TURBOMACHINE COMPONENT 有权
标题翻译：具有分层接头的涡轮组件和包含均匀涡轮机组件的蒸汽涡轮机
公开(公告)号：US20150030459A1
公开(公告)日：2015-01-29
申请号：US14373651
申请日：2012-11-07
申请人： Siemens Aktiengesellschaft
发明人： Jorg Schurhoff
IPC分类号： F01D5/28 , C23C30/00
CPC分类号： F01D25/24 , C23C4/06 , C23C4/08 , C23C14/00 , C23C24/04 , C23C30/005 , F01D25/243 , F01D25/265 , F04D29/023 , F04D29/083 , F04D29/403 , F05D2230/311 , F05D2230/313 , F05D2230/314 , F05D2230/90 , F05D2240/55 , F05D2300/132 , F05D2300/17 , F05D2300/22 , F16L9/22
摘要： A turbomachine component is provided having at least two sub-components that are separated by a parting joint and each have a sealing surface at the parting joint, at least one of the two sealing surfaces being convex in order to form a linear contact of the two sealing surfaces. At least one of the sealing surfaces has a coating on it which includes a hard material, is a maximum of 30 μm thick and is applied using a vapour deposition method, or a coating which includes a chrome-containing alloy, is a maximum of 30 μm thick and is applied by a vapour deposition method, or is a maximum of 300 μm thick and applied using a thermal spraying method.
摘要翻译：提供了一种涡轮机组件，其具有由分离接头分开的至少两个子部件，并且每个在分离接头处具有密封表面，两个密封表面中的至少一个是凸形的，以形成两者的线性接触密封面。密封面中的至少一个在其上具有包括硬质材料的涂层，其最大厚度为30μm，并且使用气相沉积法施加，或包括含铬合金的涂层最多为30 通过气相沉积法施加，或最大厚度为300μm，并使用热喷涂法施加。

45. 发明授权

US08753071B2 Cooling channel systems for high-temperature components covered by coatings, and related processes 有权
标题翻译：用于涂层覆盖的高温部件的冷却通道系统及相关工艺
公开(公告)号：US08753071B2
公开(公告)日：2014-06-17
申请号：US12975609
申请日：2010-12-22
申请人： Ronald Scott Bunker
发明人： Ronald Scott Bunker
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , F01D5/288 , F04D29/023 , F04D29/584 , F05D2230/312 , F05D2230/313 , F05D2300/17 , F05D2300/21 , F05D2300/2118 , F05D2300/611 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A method for providing a fluid cooling system within a high temperature component is described. At least one microchannel is formed in an external surface of the component; and one or more coolant passage holes are then formed, extending from at least one of the microchannels to an interior region of the component. A layer of a metallic structural coating is then applied over the external surface. At least one slot, or a set of relatively small passive cooling holes, are then formed through the metallic structural coating; extending into at least a portion of the microchannels. A second coating layer is then applied over the first layer. In some embodiments, a sacrificial material is deposited into the microchannels before the first coating layer is applied. Related articles are also described.
摘要翻译：描述了一种在高温部件内提供流体冷却系统的方法。在组件的外表面中形成至少一个微通道; 然后形成一个或多个冷却剂通道孔，从微通道中的至少一个延伸到部件的内部区域。然后将一层金属结构涂层施加在外表面上。然后通过金属结构涂层形成至少一个狭槽或一组相对小的被动冷却孔; 延伸到微通道的至少一部分。然后将第二涂层施加在第一层上。在一些实施例中，在施加第一涂层之前将牺牲材料沉积到微通道中。还描述了相关文章。

46. 发明授权

US08656589B2 Aerofoil assembly and a method of manufacturing an aerofoil assembly 有权
标题翻译：机翼组件和制造机翼组件的方法
公开(公告)号：US08656589B2
公开(公告)日：2014-02-25
申请号：US11647441
申请日：2006-12-29
申请人： Hilmi Kurt-Elli
发明人： Hilmi Kurt-Elli
IPC分类号： F01D5/10
CPC分类号： F01D5/34 , F01D5/16 , F04D29/023 , F04D29/38 , F04D29/666 , F05D2230/312 , F05D2230/313 , F05D2230/314 , F05D2230/90 , F05D2260/96 , F05D2300/125 , F05D2300/2118 , F05D2300/611 , Y10T29/4932 , Y10T29/49321 , Y10T29/49325 , Y10T29/49746
摘要： An aerofoil assembly, for example a bladed rotor assembly (40B) comprises a rotor (42) carrying a plurality of rotor blades (44), at least one of the rotor blades (44) having a coating (46) on the surface of the rotor blade (44). At least one of the rotor blades (44) has a coating (46) having a different thickness, a different area of contact with the surface of the rotor blade (44), a different position of contact on the surface of the rotor blade (44), a different shape of contact on the surface of the rotor blade (44) and/or a different composition compared to at least one of the other rotor blades (44). The coating (46) is applied in a non-uniform manner to reduce the vibration level of the rotor blade (44), or rotor blades (44), with the highest vibration response for a given excitation by changing the bladed rotor assembly (40B) mode shapes and the relative vibration of the rotor blades (44).
摘要翻译：机翼组件，例如叶片转子组件（40B）包括承载多个转子叶片（44）的转子（42），至少一个转子叶片（44）在其表面上具有涂层（46）转子叶片（44）。转子叶片（44）中的至少一个具有不同厚度的涂层（46），与转子叶片（44）的表面的不同接触面积，转子叶片表面上的不同接触位置 44），与至少一个其它转子叶片（44）相比，在转子叶片（44）的表面上的不同形状的接触和/或不同的组成。以不均匀的方式施加涂层（46），以通过改变叶片转子组件（40B）来减小转子叶片（44）或转子叶片（44）的振动水平，对于给定的激发具有最高的振动响应）模式形状和转子叶片（44）的相对振动。

47. 发明申请

US20130280480A1 ANTI-WEAR COATING 有权
标题翻译：防磨损涂层
公开(公告)号：US20130280480A1
公开(公告)日：2013-10-24
申请号：US13880904
申请日：2011-10-25
申请人： Thomas Uihlein , Wolfgang Eichmann , Falko Heutling , Annegret Brendel
发明人： Thomas Uihlein , Wolfgang Eichmann , Falko Heutling , Annegret Brendel
IPC分类号： B32B7/02
CPC分类号： B32B7/02 , B32B2250/42 , C04B2237/04 , C04B2237/086 , C04B2237/363 , C04B2237/597 , C23C28/042 , C23C28/044 , C23C28/40 , F01D5/288 , F05D2230/313 , F05D2300/611 , Y10T428/24149
摘要： The invention relates to an anti-wear coating, specifically for components which are subject to erosion under mechanical loading, in particular for gas turbine components, said coating comprising at least two different individual layers which preferably alternate with one another multiply and are applied to a surface of a component which is to be coated. The individual layers comprise a ceramic main layer (45, 46, 47, 48) and a quasi-ductile, non-metallic intermediate layer (41, 42, 43, 44).
摘要翻译：本发明涉及一种抗磨损涂层，特别涉及在机械载荷下遭受侵蚀的部件，特别是对于燃气轮机部件，所述涂层包括至少两个不同的单独层，其优选地彼此交替并被施加到要被涂覆的部件的表面。各层包括陶瓷主层（45,46,47,48）和准延性非金属中间层（41,42,43,44）。

48. 发明申请

US20130058768A1 GAS TURBINE ENGINES WITH ABRADABLE TURBINE SEAL ASSEMBLIES 有权
标题翻译：具有可拆卸涡轮密封组件的气体涡轮发动机
公开(公告)号：US20130058768A1
公开(公告)日：2013-03-07
申请号：US13224035
申请日：2011-09-01
申请人： Bradley Reed Tucker , Jason Smoke , Mark C. Morris
发明人： Bradley Reed Tucker , Jason Smoke , Mark C. Morris
IPC分类号： F01D11/00 , B21D53/84
CPC分类号： F01D11/122 , F01D11/006 , F05D2230/313 , F05D2240/55 , F05D2300/123 , Y10T29/49297
摘要： A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.
摘要翻译：燃气涡轮发动机的涡轮部分包括壳体，转子组件和密封组件。转子组件包括转子盘，联接到转子盘的转子平台以及从转子平台延伸到主流热气流动路径中的转子叶片。定子组件包括具有定子叶片的定子平台，定子叶片从定子平台延伸到主流热气流动路径中。所述密封组件包括从所述转子平台沿第一方向延伸的第一流动障碍物，从所述定子平台沿第二方向延伸的第二流动障碍物，所述第一流动障碍物轴向地与所述第二流动盘旋重叠，使得所述第二流动盘旋器为内部在径向方向上的第一流动捣碎器，施加到第一流动捣碎器的硬涂层，以及施加到第二流动捣碎器的可磨损涂层。

49. 发明授权

US08349402B2 Applying vapour phase aluminide coating on airfoil internal cavities using improved method 有权
标题翻译：使用改进的方法在气翼内腔上涂覆气相铝化物涂层
公开(公告)号：US08349402B2
公开(公告)日：2013-01-08
申请号：US12763633
申请日：2010-04-20
申请人： Kin Keong Jek , Balaji R. Garimella
发明人： Kin Keong Jek , Balaji R. Garimella
IPC分类号： C23C16/00
CPC分类号： C23C16/045 , C23C16/06 , C23C16/448 , F01D5/288 , F05D2230/313 , F05D2230/90 , F05D2260/95 , F05D2300/611
摘要： A method of applying an aluminide coating to an internal cavity of a metal part, such as an airfoil. The method includes inserting a perforated sealed container containing a source of aluminide into the internal cavity and vaporizing the aluminide source to form an aluminide coating on the wall surface of the cavity.
摘要翻译：将铝化物涂层施加到诸如翼型的金属部件的内部空腔的方法。该方法包括将含有铝化物源的穿孔密封容器插入内部空腔中并汽化铝化物源以在空腔的壁表面上形成铝化物涂层。

50. 发明申请

US20120160664A1 CATHODIC ARC VAPOR DEPOSITION COATINGS FOR DIMENSIONAL RESTORATION OF SURFACES 审中-公开
标题翻译：用于尺寸恢复表面的阴极弧蒸气沉积涂料
公开(公告)号：US20120160664A1
公开(公告)日：2012-06-28
申请号：US13329599
申请日：2011-12-19
申请人： Steven Ivory , Brian S. Tryon , William Bogue
发明人： Steven Ivory , Brian S. Tryon , William Bogue
IPC分类号： C23C14/34
CPC分类号： C23C14/042 , B23P6/00 , B23P6/007 , C23C14/165 , C23C14/325 , C23C14/345 , F01D5/005 , F01D5/288 , F05D2230/313
摘要： A process for repairing a workpiece includes the steps of: providing a workpiece having at least one interior surface requiring restoration; providing a source of repair material; and depositing the repair material onto the at least one interior surface using a technique which is a near non-line of sight technique.
摘要翻译：修复工件的方法包括以下步骤：提供具有至少一个需要恢复的内表面的工件; 提供修理材料来源; 以及使用接近非视线技术的技术将所述修复材料沉积在所述至少一个内表面上。

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