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1. 发明申请

US20130224008A1 NANO-METAL COATED VANE COMPONENT FOR GAS TURBINE ENGINES AND METHOD OF MANUFACTURING SAME 有权
标题翻译：用于气体涡轮发动机的纳米金属涂层组件及其制造方法
公开(公告)号：US20130224008A1
公开(公告)日：2013-08-29
申请号：US13408096
申请日：2012-02-29
申请人： Kin-Leung CHEUNG , Enzo Macchia , Barry Bamett
发明人： Kin-Leung CHEUNG , Enzo Macchia , Barry Bamett
IPC分类号： F03B11/02 , B23P17/00
CPC分类号： B23P17/00 , B33Y80/00 , B82Y30/00 , F01D5/147 , F01D5/288 , F01D9/041 , F01D25/02 , F01D25/162 , F02C7/047 , F05D2230/31 , F05D2250/28 , F05D2300/10 , Y10T29/49229 , Y10T29/49323 , Y10T29/49339
摘要： A method of manufacturing a vane component of a gas turbine engine is described, and includes forming a core of the vane component using a rapid manufacturing process, and applying a coating of nanocrystalline metal onto the core, the nanocrystalline metal fully encapsulating the core and defining an outer structural surface of the vane component.
摘要翻译：描述了一种制造燃气涡轮发动机的叶片部件的方法，包括使用快速制造工艺形成叶片部件的芯部，并将纳米晶体金属涂层施加到芯部上，将纳米晶体金属完全封装在芯部上并限定叶片部件的外部结构表面。

2. 发明授权

US09427835B2 Nano-metal coated vane component for gas turbine engines and method of manufacturing same 有权
标题翻译：用于燃气涡轮发动机的纳米金属涂层叶片部件及其制造方法
公开(公告)号：US09427835B2
公开(公告)日：2016-08-30
申请号：US13408096
申请日：2012-02-29
申请人： Kin-Leung Cheung , Enzo Macchia , Barry Bamett
发明人： Kin-Leung Cheung , Enzo Macchia , Barry Bamett
IPC分类号： F01D5/14 , F01D9/04 , B23P17/00 , F01D5/28 , F01D25/02 , F01D25/16 , F02C7/047 , B82Y30/00
CPC分类号： B23P17/00 , B33Y80/00 , B82Y30/00 , F01D5/147 , F01D5/288 , F01D9/041 , F01D25/02 , F01D25/162 , F02C7/047 , F05D2230/31 , F05D2250/28 , F05D2300/10 , Y10T29/49229 , Y10T29/49323 , Y10T29/49339
摘要： A method of manufacturing a vane component of a gas turbine engine is described, and includes forming a core of the vane component using a rapid manufacturing process, and applying a coating of nanocrystalline metal onto the core, the nanocrystalline metal fully encapsulating the core and defining an outer structural surface of the vane component.
摘要翻译：描述了一种制造燃气涡轮发动机的叶片部件的方法，包括使用快速制造工艺形成叶片部件的芯部，并将纳米晶体金属涂层施加到芯部上，将纳米晶体金属完全封装在芯部上并限定叶片部件的外部结构表面。

3. 发明授权

US08871297B2 Method of applying a nanocrystalline coating to a gas turbine engine component 有权
标题翻译：将纳米晶体涂层施加到燃气涡轮发动机部件的方法
公开(公告)号：US08871297B2
公开(公告)日：2014-10-28
申请号：US13188938
申请日：2011-07-22
申请人： Barry Barnett , Kin-Leung Cheung , Thomas McDonough , Andreas Eleftheriou , Enzo Macchia
发明人： Barry Barnett , Kin-Leung Cheung , Thomas McDonough , Andreas Eleftheriou , Enzo Macchia
IPC分类号： B05C13/00 , B05D3/10 , B82Y30/00 , C23C18/16 , C23C30/00 , F01D5/30 , C23C28/02 , B22F1/00
CPC分类号： B05D3/102 , B05D1/36 , B22F1/0018 , B82Y30/00 , C23C18/1637 , C23C18/1651 , C23C28/023 , C23C30/00 , F01D5/288 , F01D5/3092 , F05D2300/172
摘要： A method of applying a nanocrystalline coating to a gas turbine engine component is described. The method comprises the steps of applying an intermediate bond coat to at least a portion of the component, and then applying the nanocrystalline coating to at least the portion of the component overtop of the intermediate bond coat. The component may include, for example, a blade of which a dovetail portion of the blade root is protected by applying the intermediate bond coat and the nanocrystalline coating thereto.
摘要翻译：描述了将纳米晶体涂层应用于燃气涡轮发动机部件的方法。该方法包括以下步骤：将中间粘合涂层施加到部件的至少一部分，然后将纳米晶体涂层施加到中间粘结涂层顶部的至少部分部分。组件可以包括例如通过将中间粘合涂层和纳米晶体涂层施加到其上来保护叶片根部的燕尾部分的叶片。

4. 发明申请

US20120082783A1 METHOD OF APPLYING A NANOCRYSTALLINE COATING TO A GAS TURBINE ENGINE COMPONENT 有权
标题翻译：将纳米结构涂层应用于气体涡轮发动机部件的方法
公开(公告)号：US20120082783A1
公开(公告)日：2012-04-05
申请号：US13188938
申请日：2011-07-22
申请人： Barry Barnett , Kin-Leung Cheung , Thomas McDonough , Andreas Eleftheriou , Enzo Macchia
发明人： Barry Barnett , Kin-Leung Cheung , Thomas McDonough , Andreas Eleftheriou , Enzo Macchia
IPC分类号： B05D5/00 , B05D1/36 , B05D7/14 , B82Y40/00
CPC分类号： B05D3/102 , B05D1/36 , B22F1/0018 , B82Y30/00 , C23C18/1637 , C23C18/1651 , C23C28/023 , C23C30/00 , F01D5/288 , F01D5/3092 , F05D2300/172
摘要： A method of applying a nanocrystalline coating to a gas turbine engine component is described. The method comprises the steps of applying an intermediate bond coat to at least a portion of the component, and then applying the nanocrystalline coating to at least the portion of the component overtop of the intermediate bond coat. The component may include, for example, a blade of which a dovetail portion of the blade root is protected by applying the intermediate bond coat and the nanocrystalline coating thereto.
摘要翻译：描述了将纳米晶体涂层应用于燃气涡轮发动机部件的方法。该方法包括以下步骤：将中间粘合涂层施加到部件的至少一部分，然后将纳米晶体涂层施加到中间粘结涂层顶部的至少部分部分。组件可以包括例如通过将中间粘合涂层和纳米晶体涂层施加到其上来保护叶片根部的燕尾部分的叶片。

5. 发明申请

US20120082556A1 NANOCRYSTALLINE METAL COATED COMPOSITE AIRFOIL 审中-公开
标题翻译：纳米金属涂层复合材料
公开(公告)号：US20120082556A1
公开(公告)日：2012-04-05
申请号：US13189077
申请日：2011-07-22
申请人： Enzo Macchia , Andreas Eleftheriou , George Guglielmin , Barry Bamett , Joe Lanzino , Thomas McDonough
发明人： Enzo Macchia , Andreas Eleftheriou , George Guglielmin , Barry Bamett , Joe Lanzino , Thomas McDonough
IPC分类号： F01D5/14 , B05D5/00 , B05D1/36
CPC分类号： F01D5/147 , F01D5/282 , F01D5/288 , F01D9/041 , F01D25/162
摘要： An airfoil for a gas turbine engine comprising a root, a tip, and leading and trailing edges extending between the root and the tip. The airfoil has a non-metallic core which is composed of a composite material, and a metallic coating disposed on at least a portion of the composite core, such as along the leading edge of the airfoil for example. The metallic coating is composed of a nanocrystalline metal, and forms an outer surface of the portion of the airfoil onto which the coating is applied.
摘要翻译：一种用于燃气涡轮发动机的翼型件，包括根部，尖端以及在根部和尖端之间延伸的前缘和后缘。机翼具有由复合材料构成的非金属芯，以及设置在复合芯的至少一部分上的金属涂层，例如沿翼型的前缘。金属涂层由纳米晶体金属组成，并形成其上施加涂层的翼型部分的外表面。

6. 发明授权

US08632299B2 Engine case with wash system 有权
标题翻译：发动机外壳带洗涤系统
公开(公告)号：US08632299B2
公开(公告)日：2014-01-21
申请号：US12956405
申请日：2010-11-30
申请人： Andreas Eleftheriou , David Menheere , Richard Ivakitch , Enzo Macchia
发明人： Andreas Eleftheriou , David Menheere , Richard Ivakitch , Enzo Macchia
IPC分类号： F01D25/26
CPC分类号： F01D25/002 , F01D25/24
摘要： A gas turbine engine includes a structure defining a circumferential passage in fluid communication with an internal passage in at least one strut radially extending into the engine, circumferential passage also in fluid communication with a plurality or nozzles or jets to provide a wash manifold integrated with the engine casing structure. One or more nozzles are provided in the manifold for directing a washing fluid injected into the duct.
摘要翻译：燃气涡轮发动机包括限定在径向延伸到发动机中的至少一个支柱中的内部通道流体连通的圆周通道的结构，圆周通道也与多个喷嘴或喷嘴流体连通，以提供与发动机套管结构。在歧管中设置一个或多个喷嘴，用于引导注入到管道中的洗涤流体。

7. 发明申请

US20120082559A1 AIRFOIL BLADE 有权
标题翻译： AIRFOIL刀片
公开(公告)号：US20120082559A1
公开(公告)日：2012-04-05
申请号：US13189118
申请日：2011-07-22
申请人： George Guglielmin , Joe Lanzino , Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Thomas McDonough
发明人： George Guglielmin , Joe Lanzino , Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Thomas McDonough
IPC分类号： F01D5/14 , B23P15/02
CPC分类号： F04D29/388 , B22F2998/00 , B82Y30/00 , C23C4/01 , C23C30/00 , F01D5/147 , F01D5/282 , F01D5/288 , F01D9/041 , F01D25/162 , F04D29/023 , F04D29/325 , Y02T50/672 , Y02T50/673 , Y10T29/49336 , C22C1/08
摘要： A fan blade of a gas turbine engine, and a method of producing same, is disclosed which is composed of a core substrate and a nanocrystalline metal coating provided on at least a portion of the airfoil of the fan blade. The method includes the steps of providing a fan blade core having an airfoil and then applying a nanocrystalline metal coating over at least a portion of the fan blade core.
摘要翻译：公开了一种燃气涡轮发动机的风扇叶片及其制造方法，其由芯基板和设置在风扇叶片的翼型的至少一部分上的纳米晶体金属涂层构成。该方法包括以下步骤：提供具有翼型件的风扇叶片芯，然后在风扇叶片芯的至少一部分上施加纳米晶体金属涂层。

8. 发明授权

US08278774B2 Gas turbine with wired shaft forming part of a generator/motor assembly 有权
标题翻译：燃气轮机，带有线轴，形成发电机/电动机总成的一部分
公开(公告)号：US08278774B2
公开(公告)日：2012-10-02
申请号：US12493841
申请日：2009-06-29
申请人： Enzo Macchia
发明人： Enzo Macchia
IPC分类号： F01D15/10 , F02C6/00 , H02K7/18 , H02P9/04 , F03H1/00 , F02K3/02
CPC分类号： F02C7/32 , F01D15/10 , F05D2220/76 , F05D2220/768 , H02K7/14 , H02K7/1823 , H02K23/52 , Y02T50/671
摘要： A gas turbine engine including an electrical assembly operable as at least one of an electric motor and a generator, with an electromagnetic rotor formed in part by a portion of one of a main shaft concentrically and drivingly connected to at least one turbine rotor and a tower shaft directly driven by the main shaft and extending generally radially therefrom.
摘要翻译：一种燃气涡轮发动机，其包括可操作为电动机和发电机中的至少一个的电气组件，其中电磁转子部分地由主轴中的一个的一部分同心地并且驱动地连接到至少一个涡轮转子和塔架轴由主轴直接驱动并且大致径向延伸。

9. 发明申请

US20120082553A1 METAL ENCAPSULATED STATOR VANE 审中-公开
标题翻译：金属封装的定子槽
公开(公告)号：US20120082553A1
公开(公告)日：2012-04-05
申请号：US13189059
申请日：2011-07-22
申请人： Andreas Eleftheriou , Barry Barnett , Joe Lanzino , Tom McDonough , George Guglelmin , Enzo Macchia , Melinda Bissinger
发明人： Andreas Eleftheriou , Barry Barnett , Joe Lanzino , Tom McDonough , George Guglelmin , Enzo Macchia , Melinda Bissinger
IPC分类号： F01D5/14 , B23P15/02
CPC分类号： F01D5/147 , F01D9/02 , F05D2230/90 , F05D2300/43 , Y10T29/49336
摘要： A hybrid vane airfoil for a gas turbine engine, such as a vane of a compressor stator, is disclosed which includes a non-metallic core, and an outer metallic shell at least partially covering the non-metallic core and which defines an outer surface of the airfoil. The non-metallic core is composed for example of a polymer, and the metallic outer shell is composed of a nanocrystalline metallic coating.
摘要翻译：公开了一种用于燃气涡轮发动机的混合叶片翼片，例如压缩机定子的叶片，其包括非金属芯和至少部分地覆盖非金属芯的外部金属壳，并且限定外部表面机翼。非金属芯由例如聚合物组成，金属外壳由纳米晶体金属涂层组成。

10. 发明授权

US06983603B2 Detection of gas turbine engine hot section condition 有权
标题翻译：检测燃气轮机发动机热段条件
公开(公告)号：US06983603B2
公开(公告)日：2006-01-10
申请号：US10278897
申请日：2002-10-24
申请人： Enzo Macchia
发明人： Enzo Macchia
IPC分类号： F02C9/00 , F02C9/28
CPC分类号： F01D17/085 , F05D2270/112
摘要： A system and a method for detecting gas turbine engine hot section condition using temperature measurements during engine operation. The system comprises a sensing unit for sensing a temperature distribution across a hot combustion gas stream generated by a gas turbine engine combustor. A signal processor receives temperature signals from the sensing unit and generates a combustor malfunction signal when the difference between a maximal temperature and a minimal temperature of the sensed temperature distribution is greater than a predetermined acceptable delta value.
摘要翻译：用于在发动机运行期间使用温度测量来检测燃气涡轮发动机热段条件的系统和方法。该系统包括用于感测由燃气涡轮发动机燃烧器产生的热燃烧气流的温度分布的感测单元。当感测温度分布的最大温度和最小温度之差大于预定的可接受增量值时，信号处理器从感测单元接收温度信号并产生燃烧器故障信号。

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