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1. 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。

2. 发明申请

US20120082551A1 GAS TURBINE BLADE AND METHOD OF PROTECTING SAME 有权
标题翻译：气体涡轮叶片及其保护方法
公开(公告)号：US20120082551A1
公开(公告)日：2012-04-05
申请号：US13189043
申请日：2011-07-22
申请人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
发明人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
IPC分类号： F01D5/30
CPC分类号： F01D5/3092 , F01D5/005 , F01D5/28 , F05B2230/90 , F05D2220/32 , F05D2230/80 , F05D2230/90 , F05D2260/94 , F05D2300/11 , F05D2300/121 , F05D2300/13 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/134 , F05D2300/143 , F05D2300/16 , F05D2300/1614 , F05D2300/1616 , F05D2300/609
摘要： An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed.
摘要翻译：燃气涡轮发动机的翼型叶片包括配置成与配合的转子毂配合连接的根部以及远离根部延伸的翼型件。根由第一金属组成，并且在其至少一部分上具有由第二金属组成的纳米晶体金属涂层。还公开了通过将纳米晶体金属涂层施加到叶片根部的一部分来保护这种叶片的方法。

3. 发明申请

US20120082541A1 GAS TURBINE ENGINE CASING 审中-公开
标题翻译：燃气轮机发动机
公开(公告)号：US20120082541A1
公开(公告)日：2012-04-05
申请号：US13189100
申请日：2011-07-22
申请人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
发明人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
IPC分类号： F01D25/24 , B23P17/00
CPC分类号： F01D25/246 , F01D21/045 , F02K3/06 , Y02T50/672 , Y10T29/49229
摘要： An engine casing for a gas turbine engine, such as, but not limited to, a gas turbine engine fan case, is disclosed which includes an annular case shell formed of a substrate material that is at least partially coated by a nanocrystalline metal coating. A method of manufacturing such an engine casing is also provided. The present engine casing provides improved containment capability in the event of a blade release or other failure during operation of the engine.
摘要翻译：公开了一种用于燃气涡轮发动机的发动机壳体，例如但不限于燃气涡轮发动机风扇壳体，其包括由至少部分地由纳米晶体金属涂层涂覆的基底材料形成的环形壳体壳体。还提供了制造这种发动机壳体的方法。本发动机壳体在发动机操作期间在叶片释放或其他故障的情况下提供改进的容纳能力。

4. 发明授权

US09429029B2 Gas turbine blade and method of protecting same 有权
标题翻译：燃气轮机叶片及其保护方法
公开(公告)号：US09429029B2
公开(公告)日：2016-08-30
申请号：US13189043
申请日：2011-07-22
申请人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
发明人： Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Tom McDonough , George Guglielmin , Joe Lanzino
IPC分类号： F03B3/12 , F01D5/30
CPC分类号： F01D5/3092 , F01D5/005 , F01D5/28 , F05B2230/90 , F05D2220/32 , F05D2230/80 , F05D2230/90 , F05D2260/94 , F05D2300/11 , F05D2300/121 , F05D2300/13 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/134 , F05D2300/143 , F05D2300/16 , F05D2300/1614 , F05D2300/1616 , F05D2300/609
摘要： An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed.
摘要翻译：燃气涡轮发动机的翼型叶片包括配置成与配合的转子毂配合连接的根部以及远离根部延伸的翼型件。根由第一金属组成，并且在其至少一部分上具有由第二金属组成的纳米晶体金属涂层。还公开了通过将纳米晶体金属涂层施加到叶片根部的一部分来保护这种叶片的方法。

5. 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。

6. 发明授权

US09587645B2 Airfoil blade 有权
标题翻译：翼型叶片
公开(公告)号：US09587645B2
公开(公告)日：2017-03-07
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 , F04D29/38 , B82Y30/00 , C23C30/00 , F01D5/28 , F01D9/04 , F01D25/16 , F04D29/02 , F04D29/32
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。

7. 发明申请

US20130255277A1 GAS TURBINE ENGINE NOSE CONE 审中-公开
标题翻译：燃气涡轮发动机油
公开(公告)号：US20130255277A1
公开(公告)日：2013-10-03
申请号：US13435738
申请日：2012-03-30
申请人： Enzo Macchia , Andreas Eleftheriou , Thomas Peter McDonough , George Guglielmin , Joe Lanzino , Barry Barnett
发明人： Enzo Macchia , Andreas Eleftheriou , Thomas Peter McDonough , George Guglielmin , Joe Lanzino , Barry Barnett
IPC分类号： F02C7/00 , F02C3/04 , B05D1/18 , F01D25/00
CPC分类号： F02C7/04 , F05D2250/232 , F05D2300/605 , F05D2300/608 , F05D2300/612
摘要： A nose cone for a turbofan gas turbine engine includes a central tip, an outer perimeter and a substantially conical outer wall extending therebetween which encloses a cavity therewithin. The outer wall includes an inner substrate layer facing the cavity and an outer layer which overlies and at least partially encloses the inner substrate layer. The outer layer is composed entirely of a nanocrystalline metal forming an outer surface of the nose cone.
摘要翻译：用于涡轮风扇燃气涡轮发动机的鼻锥包括中心尖端，外周边和在其间延伸的基本上圆锥形的外壁，其在其中封闭空腔。外壁包括面向空腔的内部基底层和覆盖并至少部分地包围内部基底层的外层。外层完全由形成鼻锥外表面的纳米晶体金属构成。

8. 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。

9. 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。

10. 发明授权

US09169780B2 Connection for generator in a gas turbine engine 有权
标题翻译：燃气轮机发电机连接
公开(公告)号：US09169780B2
公开(公告)日：2015-10-27
申请号：US13183848
申请日：2011-07-15
申请人： Barry Barnett , Daniel Alecu , Andreas Eleftheriou
发明人： Barry Barnett , Daniel Alecu , Andreas Eleftheriou
IPC分类号： F02C7/06 , F02C7/32 , F02C7/36
CPC分类号： F02C7/06 , F02C7/32 , F02C7/36 , F05D2260/202
摘要： A gas turbine engine having an electric generator includes a transmission shaft extending along a longitudinal axis of the engine and drivingly interconnecting a turbine shaft of the engine and a rotor shaft of the electric generator. The transmission shaft is engaged by splined mating connections with the turbine shaft and the rotor shaft. The transmission shaft has a shear neck defining a reduced radial wall thickness with respect to a remainder of the transmission shaft such as to provide a weakened region of the transmission shaft. An annular support structure, concentric with and surrounding the transmission shaft, is axially located between the shear neck and a forward end of the transmission shaft engaged to the turbine shaft, and includes a bearing operable to rotationally support the transmission shaft.
摘要翻译：具有发电机的燃气涡轮发动机包括：沿着发动机的纵轴延伸的传动轴，并将发动机的涡轮轴与发电机的转子轴驱动连接。传动轴通过与涡轮轴和转子轴的花键配合连接接合。传动轴具有剪切颈部，其相对于传动轴的其余部分限定径向壁厚度减小，以便提供传动轴的弱化区域。与传动轴同心并且围绕传动轴的环形支撑结构轴向地位于剪切颈部和接合到涡轮轴的传动轴的前端之间，并且包括可操作以可旋转地支撑传动轴的轴承。

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