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41. 发明授权

US08083474B2 Turbocharger 有权
标题翻译：涡轮增压器
公开(公告)号：US08083474B2
公开(公告)日：2011-12-27
申请号：US12311468
申请日：2007-10-01
申请人： Shigeo Hashimoto , Noboru Hamaguchi , Yasuaki Jinnai
发明人： Shigeo Hashimoto , Noboru Hamaguchi , Yasuaki Jinnai
IPC分类号： F02D23/00
CPC分类号： F01D17/165 , F01D25/005 , F02B37/24 , F02C6/12 , F05D2220/40 , F05D2230/313 , F05D2230/90 , F05D2300/121 , F05D2300/132 , F05D2300/171 , F05D2300/611
摘要： To provide a turbocharger whose lifetime is long, which is capable of inexpensively and precisely performing nozzle vane angle synchronous control by using inexpensive and highly wear resistant components in a link mechanism for driving a rotation mechanism of nozzle vanes of an adjustable nozzle mechanism. As pins fixedly arrayed in a ring plate rotatably supported on the turbocharger, that set an angle of the nozzle vanes for controlling an amount of exhaust gas for rotating a turbine rotor, each pin in which a hard coating with a thickness of approximately 2 μm which is formed of Al, Cr, Si, and N by physical vapor deposition is formed onto an austenitic stainless steel as a base material, is used.
摘要翻译：为了提供寿命长的涡轮增压器，其能够通过在用于驱动可调节喷嘴机构的喷嘴叶片的旋转机构的连杆机构中使用廉价且高度耐磨的部件来廉价且精确地执行喷嘴叶片角同步控制。作为固定地布置在可旋转地支撑在涡轮增压器上的环板中的销，其设置喷嘴叶片的角度以控制用于旋转涡轮机转子的排气量，每个销具有大约2μm的厚度的硬涂层，由作为基材的奥氏体不锈钢形成由Al，Cr，Si，N形成的物理气相沉积。

42. 发明申请

US20110259017A1 HOT GAS PATH COMPONENT COOLING SYSTEM 有权
标题翻译：热气路成分冷却系统
公开(公告)号：US20110259017A1
公开(公告)日：2011-10-27
申请号：US12765372
申请日：2010-04-22
申请人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
发明人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
IPC分类号： F02C7/12 , F28F13/18
CPC分类号： F01D25/12 , F01D5/186 , F01D5/187 , F02C7/12 , F05D2230/11 , F05D2230/13 , F05D2230/313 , F05D2230/314 , F05D2230/90 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： A cooling system for a hot gas path component is disclosed. The cooling system may include a component layer and a cover layer. The component layer may include a first inner surface and a second outer surface. The second outer surface may define a plurality of channels. The component layer may further define a plurality of passages extending generally between the first inner surface and the second outer surface. Each of the plurality of channels may be fluidly connected to at least one of the plurality of passages. The cover layer may be situated adjacent the second outer surface of the component layer. The plurality of passages may be configured to flow a cooling medium to the plurality of channels and provide impingement cooling to the cover layer. The plurality of channels may be configured to flow cooling medium therethrough, cooling the cover layer.
摘要翻译：公开了一种用于热气路径部件的冷却系统。冷却系统可以包括组件层和覆盖层。组件层可以包括第一内表面和第二外表面。第二外表面可以限定多个通道。组件层可以进一步限定大体上在第一内表面和第二外表面之间延伸的多个通道。多个通道中的每一个可以流体地连接到多个通道中的至少一个。覆盖层可以位于邻近部件层的第二外表面处。多个通道可以被配置成将冷却介质流动到多个通道并且向覆盖层提供冲击冷却。多个通道可以被配置成流过冷却介质，冷却覆盖层。

43. 发明授权

US07988412B2 Structures for damping of turbine components 有权
标题翻译：涡轮机组件阻尼结构
公开(公告)号：US07988412B2
公开(公告)日：2011-08-02
申请号：US11844462
申请日：2007-08-24
申请人： Canan Uslu Hardwicke , John McConnell Delvaux , Bradley Taylor Boyer , James William Vehr
发明人： Canan Uslu Hardwicke , John McConnell Delvaux , Bradley Taylor Boyer , James William Vehr
IPC分类号： F01D5/16
CPC分类号： F01D25/06 , F01D5/16 , F05D2230/31 , F05D2230/312 , F05D2230/313 , F05D2230/90 , F05D2250/60 , F05D2260/96 , F05D2300/17 , F05D2300/171 , F05D2300/501
摘要： Disclosed is a coating for gas turbine components including at least one material having vibration-damping properties. Further disclosed is an airfoil of a gas turbine having damped vibrational characteristics including an airfoil substrate and a coating applied to the airfoil substrate including at least one material having vibration-damping properties. A method of damping vibration of a gas turbine component includes applying a coating including at least one material having damping properties to the turbine component.
摘要翻译：公开了一种用于燃气轮机部件的涂层，其包括至少一种具有阻尼性能的材料。还公开了具有阻尼振动特性的燃气涡轮机翼型，其包括翼型基板和施加到翼型基板上的涂层，该涂层包括至少一种具有阻尼性能的材料。一种阻尼燃气涡轮机部件的振动的方法包括将包括至少一种具有阻尼特性的材料涂覆到涡轮部件上。

44. 发明授权

US07981530B2 Dysprosia stabilized zirconia abradable 有权
标题翻译：氧化镝稳定氧化锆易磨损
公开(公告)号：US07981530B2
公开(公告)日：2011-07-19
申请号：US11808244
申请日：2007-06-07
申请人： Dieter R. Sporer , Ulrike Taeck , Mitchell R. Dorfman , Andrew R. Nicoll , Massimo Giannozzi , Iacopo Giovannetti
发明人： Dieter R. Sporer , Ulrike Taeck , Mitchell R. Dorfman , Andrew R. Nicoll , Massimo Giannozzi , Iacopo Giovannetti
IPC分类号： B32B9/00 , C23C4/10
CPC分类号： F01D11/122 , C04B35/48 , C04B35/488 , C04B38/067 , C04B2111/00146 , C04B2111/00982 , C04B2111/2084 , C23C4/11 , F01D5/005 , F01D5/288 , F05D2230/311 , F05D2230/312 , F05D2230/313 , F05D2230/80 , F05D2230/90 , F05D2300/134 , F05D2300/15 , F05D2300/2118 , Y02T50/67 , Y02T50/672 , Y10T428/2982 , C04B38/0074
摘要： Ceramic abradable materials, in particular thermally sprayable ceramic abradable powder materials, and abradable seals formed by thermally spraying the materials include dysprosia (Dy2O3) and zirconia (ZrO2). Coatings are porous whereby the porosity, in part, is induced by plastic or fugitive phases. Abradable seal coatings comprising dysprosia and zirconia exhibit improved thermal shock and sintering resistance and can be worn into tolerance by untreated, bare turbine blades, at least in certain regimes of relative blade speed and coating porosity. Ceramic abradable seal coatings comprising dysprosia and zirconia can be used up to 1200° C.
摘要翻译：陶瓷耐磨材料，特别是可热喷涂的陶瓷耐磨粉末材料和通过热喷涂材料形成的耐磨密封件包括恶臭（Dy2O3）和氧化锆（ZrO2）。涂层是多孔的，其中孔隙率在一定程度上是由塑性或非挥发性相引起的。包括恶臭和氧化锆的可磨损的密封涂层表现出改善的热冲击和耐烧结性，并且可以至少在某些相对叶片速度和涂层孔隙率的条件下，通过未处理的裸露的涡轮叶片磨损到公差中。包含镝和氧化锆的陶瓷耐磨密封涂层最多可以用于1200°C

45. 发明申请

US20100266419A1 ENGINE COMPONENT FOR A GAS TURBINE 审中-公开
标题翻译：发动机组件用于气体涡轮机
公开(公告)号：US20100266419A1
公开(公告)日：2010-10-21
申请号：US12675800
申请日：2008-08-29
申请人： Ulf Reinmöller , Christian Siry
发明人： Ulf Reinmöller , Christian Siry
IPC分类号： F01D5/14 , B05D7/00 , C23C16/50
CPC分类号： F01D5/288 , C23C14/0605 , C23C16/26 , F05D2230/313 , F05D2230/314 , F05D2260/95 , F05D2300/224
摘要： The object of the invention is an engine component for arrangement in the gas flow of a gas turbine. According to the invention, at least one part of the surface of said component subjected to the gas flow in operation comprises a modified amorphous carbon layer containing hydrogen that is applied using a vacuum coating technique.
摘要翻译：本发明的目的是用于布置在燃气轮机的气流中的发动机部件。根据本发明，在操作中经受气体流动的所述部件的表面的至少一部分包括使用真空涂覆技术施加的包含氢的改性无定形碳层。

46. 发明申请

US20090148694A1 Layer System Comprising Two Pyrochlore Phases 有权
标题翻译：包含两个热解阶段的层系统
公开(公告)号：US20090148694A1
公开(公告)日：2009-06-11
申请号：US12087481
申请日：2006-12-15
申请人： Axel Kaiser , Eckart Schumann , Ramesh Subramanian
发明人： Axel Kaiser , Eckart Schumann , Ramesh Subramanian
IPC分类号： B32B15/04
CPC分类号： C23C28/3215 , C23C28/321 , C23C28/345 , C23C28/3455 , C23C28/36 , F01D5/288 , F05D2230/312 , F05D2230/313 , Y02T50/67 , Y02T50/671 , Y10T428/12618 , Y10T428/24942 , Y10T428/2495 , Y10T428/24975 , Y10T428/26
摘要： Heat-insulating layer systems have to be provided with along service life of the heat-insulating layer in addition to having good heat-insulating properties. The inventive layer system comprises a ceramic layer which contains a mixture of two pyrochlore phases.
摘要翻译：除了具有良好的绝热性能之外，绝热层系统必须具有绝缘层的使用寿命。本发明的层系统包括含有两个烧绿石相的混合物的陶瓷层。

47. 发明申请

US20090098346A1 ATOMIC LAYER DEPOSITION FOR TURBINE COMPONENTS 审中-公开
标题翻译：用于涡轮机构的原子层沉积
公开(公告)号：US20090098346A1
公开(公告)日：2009-04-16
申请号：US11877271
申请日：2007-10-23
申请人： Chien-Wei Li
发明人： Chien-Wei Li
IPC分类号： B32B3/18
CPC分类号： F01D5/284 , C23C16/403 , C23C16/45525 , C23C16/45555 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/34 , C23C28/341 , C23C28/345 , C23C28/3455 , C23C28/42 , C23C30/00 , F01D5/288 , F05D2230/31 , F05D2230/313 , Y10T428/12576 , Y10T428/12597 , Y10T428/12611 , Y10T428/2462
摘要： A method and superalloy component for depositing a layer of material onto gas turbine engine components by atomic layer deposition. A superalloy component may have a ceramic thermal barrier coating on at least a portion of its surface, comprising a superalloy substrate and a bonding coat; and aluminum oxide (Al2O3) layer may be deposited on top of an yttria-stabilized zirconia layer and form a bonding coat by atomic layer deposition. The yttria-stabilized zirconia layer may have a plurality of micron sized gaps extending from the top surface of the ceramic coating towards the substrate and defining a plurality of columns of the yttria-stabilized zirconia layer. Also, atomic layer deposition may be used to lay an aluminum oxide (Al2O3) layer over a tantalum oxide (Ta2O5) layer on a silicon-based substrate. Using atomic layer deposition to coat the gas turbine engine components permits conformal coating of the columnar surface to permit gap expansion and contraction without sintering of the columnar surface or spalling of the coating, and form an oxidation resistant bonding coat.
摘要翻译：一种用于通过原子层沉积将材料层沉积到燃气涡轮发动机部件上的方法和超合金部件。超级合金部件可以在其表面的至少一部分上具有陶瓷热障涂层，其包括超合金基底和粘合涂层; 并且氧化铝（Al 2 O 3）层可以沉积在氧化钇稳定的氧化锆层的顶部上，并通过原子层沉积形成粘结层。氧化钇稳定的氧化锆层可以具有从陶瓷涂层的顶表面朝向衬底延伸的多个微米尺寸的间隙并且限定多个氧化钇稳定的氧化锆层的柱。此外，可以使用原子层沉积在硅基衬底上的氧化钽（Ta 2 O 5）层上层叠氧化铝（Al 2 O 3）层。使用原子层沉积来涂覆燃气涡轮发动机部件允许圆柱形表面的共形涂覆以允许间隙膨胀和收缩，而不会烧结柱状表面或剥落涂层，并形成抗氧化粘合涂层。

48. 发明申请

US20090041586A1 TURBINE NOZZLE SECTOR 有权
标题翻译：涡轮喷嘴部分
公开(公告)号：US20090041586A1
公开(公告)日：2009-02-12
申请号：US12185304
申请日：2008-08-04
申请人： Jean-Luc BACHA , Olivier Jean Daniel BAUMAS , Lucie LANCIAUX , Sophie LAVISON
发明人： Jean-Luc BACHA , Olivier Jean Daniel BAUMAS , Lucie LANCIAUX , Sophie LAVISON
IPC分类号： F01D5/18
CPC分类号： F01D9/04 , F01D5/187 , F05D2230/313 , F05D2240/122 , F05D2240/304 , F05D2260/205 , F05D2260/607 , F05D2260/95 , Y02T50/67 , Y02T50/676
摘要： A turbine nozzle sector that comprises an outer platform segment and an inner platform segment between which there extend one or more hollow vanes. Each vane presents a trailing edge cavity for feeding with cooling air and communicating with a plurality of vents distributed along the trailing edge of the vane, these vents serving to exhaust a fraction of the cooling air. Said cavity communicates with an air outlet hole situated level with the outer platform and enabling a fraction of the cooling air to be exhausted.
摘要翻译：涡轮喷嘴扇区，其包括外平台段和内平台段，在该平台段之间延伸一个或多个中空叶片。每个叶片具有用于供给冷却空气并与沿着叶片的后缘分布的多个通风口连通的后缘空腔，这些通风口用于排出一部分冷却空气。所述空腔与位于与外平台水平位置的出气孔连通，并使一部分冷却空气排出。

49. 发明申请

US20090022583A1 Turbine blade with a cover plate and a protective layer applied to the cover plate 有权
标题翻译：具有盖板和保护层的涡轮叶片施加到盖板上
公开(公告)号：US20090022583A1
公开(公告)日：2009-01-22
申请号：US11918809
申请日：2006-01-20
申请人： Albert Schrey , Gerhard Schwass , Armin de Lazzer
发明人： Albert Schrey , Gerhard Schwass , Armin de Lazzer
IPC分类号： F01D11/12 , F01D5/14 , B23P15/04
CPC分类号： F01D5/225 , F01D5/288 , F01D11/12 , F01D11/122 , F05C2201/0463 , F05D2230/232 , F05D2230/30 , F05D2230/312 , F05D2230/313 , F05D2230/90 , F05D2300/226 , F05D2300/228 , F05D2300/2284 , Y10T29/4932
摘要： The invention relates to a turbine blade with a cover plate shaped onto the pan of the blade. The aim of the invention is to provide a turbine blade of this type that, while having a high level of efficiency, is designed for a particularly reliable and safe operation in a turbine, particularly of a steam turbine. To this end, the invention provides that a protective layer made on an alternative material is applied to the surface of the cover plate facing away from the pan of the blade. The friction behavior with regard to a turbine component, particularly a sealing strip, which is opposite the protective layer, can be specifically influenced whereby enabling favorable emergency running properties to be provided in the event of rubbing.
摘要翻译：本发明涉及具有形成在叶片的盘上的盖板的涡轮叶片。本发明的目的是提供一种具有高水平效率的这种类型的涡轮叶片，其被设计用于在涡轮机，特别是蒸汽涡轮机中的特别可靠和安全的操作。为此，本发明提供了将替代材料制成的保护层施加到盖板的远离叶片盘的表面。对于与保护层相对的涡轮机部件，特别是密封条，可以具体地影响摩擦性能，从而在摩擦的情况下提供有利的紧急行驶性能。

50. 发明申请

US20090004364A1 Method For Protecting New/Used Engine Parts 审中-公开
标题翻译：保护新/二手发动机零件的方法
公开(公告)号：US20090004364A1
公开(公告)日：2009-01-01
申请号：US12204463
申请日：2008-09-04
申请人： Terry Hollis , Chris Williams , Gary Prus , Jerry Sileo
发明人： Terry Hollis , Chris Williams , Gary Prus , Jerry Sileo
IPC分类号： C23C14/54
CPC分类号： B23P6/007 , B23P6/002 , B23P9/04 , C21D7/06 , C23C14/021 , C23C14/028 , C23C14/0641 , C23C14/16 , F01D5/005 , F01D5/286 , F01D5/288 , F05D2230/313 , F05D2230/314 , F05D2230/80 , F05D2230/90 , F05D2300/2284 , F05D2300/506 , F05D2300/702 , Y02T50/673
摘要： New and used parts of gas and steam turbine engines are protected by imparting a controlled residual compressive stress to given portions of the part and then coated by a CVD or PVD process at low temperatures with layers of TiN or alloys thereof at alternate selective hard and less hardened levels. The protective treatment is particularly efficacious for airfoils of compressor blades/vanes of gas turbine engines and airfoils of airfoils and certain components of steam turbine engines. This method is targeted to reduce erosion, corrosion and stress-corrosion cracking in these parts.
摘要翻译：气体和蒸汽涡轮发动机的新旧部件通过在部件的给定部分施加受控的残余压应力来保护，然后在低温下用CVD或PVD工艺涂覆，其中TiN层或其合金层具有交替的选择性硬和较少硬化水平。保护处理对于燃气涡轮发动机的压缩机叶片/叶片的机翼和翼型件和蒸汽涡轮发动机的某些部件的翼型特别有效。该方法的目标是减少这些部件的侵蚀，腐蚀和应力腐蚀开裂。

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