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. 发明申请

US20050022501A1 Turbofan case and method of making 有权
标题翻译： Turbofan案例和制作方法
公开(公告)号：US20050022501A1
公开(公告)日：2005-02-03
申请号：US10628556
申请日：2003-07-29
申请人： Andreas Eleftheriou , Kevin Lobo , Maurice Weinberg , Quantai Liu
发明人： Andreas Eleftheriou , Kevin Lobo , Maurice Weinberg , Quantai Liu
IPC分类号： F01D5/22 , F01D25/24 , F02K3/06 , F02K3/02
CPC分类号： F01D5/22 , F01D25/24 , F02K3/06 , Y02T50/671 , Y02T50/673
摘要： A casing for a gas turbine includes a fan case, an intermediate case and a gas generator case integrated with one another.
摘要翻译：用于燃气轮机的壳体包括彼此集成的风扇壳体，中间壳体和气体发生器壳体。

42. 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。

43. 发明授权

US09395122B2 Diffusing gas turbine engine recuperator 有权
标题翻译：扩散燃气涡轮发动机换热器
公开(公告)号：US09395122B2
公开(公告)日：2016-07-19
申请号：US13036428
申请日：2011-02-28
申请人： Andreas Eleftheriou , David Menheere , Daniel Alecu , Darius Jehangir Karanjia
发明人： Andreas Eleftheriou , David Menheere , Daniel Alecu , Darius Jehangir Karanjia
IPC分类号： F02C7/08 , F28D9/00 , F02C7/10 , F28F13/08 , F28D21/00
CPC分类号： F02C7/10 , F02C7/08 , F02C7/14 , F05D2220/32 , F05D2260/213 , F05D2260/96 , F28D9/0018 , F28D21/0003 , F28D2021/0026 , F28F13/08
摘要： A gas turbine engine recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust inlet having a smaller cross-sectional area than that of the exhaust outlet, and a cross sectional area of each exhaust passage progressively increasing from the exhaust inlet to the exhaust outlet such as to diffuse the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and provide fluid flow communication between an air inlet and an air outlet designed to sealingly engage respective plenums of the gas turbine engine.
摘要翻译：一种燃气涡轮发动机换热器，包括排气通道，其提供排气入口和排气出口之间的流体流动连通，所述排气入口被定向为接收来自所述发动机的涡轮机的排气流，所述排气出口被定向成将排气流输送到大气，排气入口具有比排气出口小的横截面面积，并且每个排气通道的横截面面积从排气入口逐渐增加到排气出口，从而扩散排气流。空气通道与排气通道处于热交换关系，并且在空气入口和设计成密封地接合燃气涡轮发动机的各个通风室的空气出口之间提供流体流动连通。

44. 发明授权

US08979484B2 Casing for an aircraft turbofan bypass engine 有权
标题翻译：套装飞机涡扇风机旁路引擎
公开(公告)号：US08979484B2
公开(公告)日：2015-03-17
申请号：US13344057
申请日：2012-01-05
申请人： Andreas Eleftheriou , David Menheere , David Denis
发明人： Andreas Eleftheriou , David Menheere , David Denis
IPC分类号： F01D25/24 , F01D9/06
CPC分类号： F01D9/065 , F01D25/162 , F01D25/24 , F05D2230/232 , F05D2230/237
摘要： A casing for an aircraft turbofan bypass engine includes an outer ring, an inner hub and a plurality of struts radially extending therebetween. An annular portion of an engine core casing having an outer wall and an inner wall, is disposed between the outer ring and inner hub, forming an annular splitter supporting an upstream splitter tip structure. The annular splitter further includes an intermediate wall disposed in the annular splitter fixed to the outer wall and the struts, to distribute loads from the annular splitter box to the struts.
摘要翻译：用于飞行器涡扇风扇旁路发动机的壳体包括外环，内毂和在它们之间径向延伸的多个支柱。具有外壁和内壁的发动机芯壳的环形部分设置在外环和内毂之间，形成支撑上游分流器顶端结构的环形分流器。环形分离器还包括设置在固定到外壁和支柱的环形分配器中的中间壁，以将负载从环形分配箱分配到支柱。

45. 发明授权

US08801376B2 Fabricated intermediate case with engine mounts 有权
标题翻译：带发动机支架的制造中间箱
公开(公告)号：US08801376B2
公开(公告)日：2014-08-12
申请号：US13224379
申请日：2011-09-02
申请人： Andreas Eleftheriou , David Menheere , Quantai Liu
发明人： Andreas Eleftheriou , David Menheere , Quantai Liu
IPC分类号： F01D25/14
CPC分类号： F02C7/20 , F05D2230/232
摘要： A fabricated engine case has a plurality of circumferentially spaced struts radially extending between an outer case and an inner case. A mount apparatus is affixed to the outer case of the engine case. The mount apparatus is a mount base radially spaced apart from a circumferential skin of the outer case and a load bearing member extending radially inwardly to connect the mount base to an outer end of one of the struts.
摘要翻译：制造的发动机壳体具有在外壳和内壳之间径向延伸的多个周向间隔的支柱。发动机壳体的外壳附着有安装装置。安装装置是与外壳的圆周表皮径向间隔开的安装基座和径向向内延伸的承载构件，以将安装基座连接到一个支柱的外端。

46. 发明申请

US20130298522A1 GEARED FAN ASSEMBLY 有权
标题翻译：齿轮风扇总成
公开(公告)号：US20130298522A1
公开(公告)日：2013-11-14
申请号：US13469712
申请日：2012-05-11
申请人： Andreas Eleftheriou , David Menheere
发明人： Andreas Eleftheriou , David Menheere
IPC分类号： F02C3/04 , B23P11/00 , F01D15/12
CPC分类号： F02K3/06 , F02C3/06 , F02C3/107 , F02C7/36 , F05D2260/40311 , Y10T29/49231
摘要： An assembly for a gas turbine engine, with a gearbox including a first portion having a first input gear coupled to a rotatable turbine shaft, a first output gear, and defining a first transmission path between the first input and output gears, and a second portion having a second input gear coupled to the turbine shaft, a second output gear, and defining a second transmission path between the second input and output gears different from the first transmission path. A fan rotor is coupled to the first output gear and a booster rotor is coupled to the second output gear on a same side of the gearbox than the coupling between the fan rotor and the first output gear. A method of assembling a drive for a fan rotor and a booster rotor in a gas turbine engine is also disclosed.
摘要翻译：一种用于燃气涡轮发动机的组件，其具有包括第一部分的齿轮箱，第一部分具有联接到可旋转的涡轮轴的第一输入齿轮，第一输出齿轮，并且限定第一输入和输出齿轮之间的第一传动路径，以及第二部分具有联接到涡轮机轴的第二输入齿轮，第二输出齿轮，并且在不同于第一传动路径的第二输入齿轮和输出齿轮之间限定第二传动路径。风扇转子联接到第一输出齿轮，并且增强转子与齿轮箱的与风扇转子和第一输出齿轮之间的联接相同的一侧耦合到第二输出齿轮。还公开了一种在燃气轮机中组装用于风扇转子和升压转子的驱动装置的方法。

47. 发明申请

US20130014513A1 CONNECTION FOR GENERATOR IN A GAS TURBINE ENGINE 有权
标题翻译：发电机在气体发动机中的连接
公开(公告)号：US20130014513A1
公开(公告)日：2013-01-17
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： F02C6/00
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。

48. 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。

49. 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。

50. 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。

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