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公开(公告)号：US09080461B2
公开(公告)日：2015-07-14
申请号：US13364379
申请日：2012-02-02
Applicant: Richard Ivakitch , Andreas Eleftheriou , Philippe Bonniere
Inventor： Richard Ivakitch , Andreas Eleftheriou , Philippe Bonniere
CPC classification number: F01D21/04 , F01D5/066 , F01D21/045 , F05D2220/36 , F05D2250/75 , Y10T29/49318
Abstract: A gas turbine engine having at least one spool assembly, the at least one spool assembly including a fan rotor, a compressor disposed downstream of the fan rotor, a turbine and a shaft connecting the fan rotor, compressor and turbine, a joint affixed to an upstream end of the shaft, and including a first link connecting the fan rotor to the shaft and a second link connecting the compressor to the shaft, the second link being less rigid then the first link.
Abstract translation: 一种具有至少一个阀芯组件的燃气涡轮发动机，所述至少一个阀芯组件包括风扇转子，设置在所述风扇转子下游的压缩机，涡轮机和连接所述风扇转子，压缩机和涡轮机的轴， 并且包括将风扇转子连接到轴的第一连杆和将压缩机连接到轴的第二连杆，第二连杆比第一连杆刚性小。
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22.发明授权Method of applying a nanocrystalline coating to a gas turbine engine component 有权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
Applicant: Barry Barnett , Kin-Leung Cheung , Thomas McDonough , Andreas Eleftheriou , Enzo Macchia
Inventor： Barry Barnett , Kin-Leung Cheung , Thomas McDonough , Andreas Eleftheriou , Enzo Macchia
CPC classification number: B05D3/102 , B05D1/36 , B22F1/0018 , B82Y30/00 , C23C18/1637 , C23C18/1651 , C23C28/023 , C23C30/00 , F01D5/288 , F01D5/3092 , F05D2300/172
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US20130058771A1
公开(公告)日：2013-03-07
申请号：US13223701
申请日：2011-09-01
Applicant: David Harold MENHEERE , Richard IVAKITCH , Andreas ELEFTHERIOU
Inventor： David Harold MENHEERE , Richard IVAKITCH , Andreas ELEFTHERIOU
CPC classification number: F01D5/225 , F05D2260/30
Abstract: A vane assembly of a gas turbine engine includes a plurality of circumferentially spaced vanes extending radially between an outer case and an inner case. A spring-tensioned stator restraining strap is provided around the outer case and surrounding outer ends of the respective vanes. The outer ends of the vanes are received in corresponding openings defined in the outer case and project radially outwardly from the outer case. The spring-tensioned strap compresses the respective vanes radially and inwardly in position.
Abstract translation: 燃气涡轮发动机的叶片组件包括在外壳和内壳之间径向延伸的多个周向隔开的叶片。 弹簧张紧的定子限制带设置在外壳周围并且围绕相应叶片的外端。 叶片的外端容纳在限定在外壳中的相应开口中，并从外壳径向向外突出。 弹簧张紧的带子将各个叶片径向和内向压缩在适当位置。
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公开(公告)号：US20100209251A1
公开(公告)日：2010-08-19
申请号：US12372758
申请日：2009-02-18
Applicant: David H. Menheere , Andreas Eleftheriou , Philip Ridyard
Inventor： David H. Menheere , Andreas Eleftheriou , Philip Ridyard
CPC classification number: F01D5/3007 , F01D11/008 , F05D2220/36 , F05D2300/133 , F05D2300/505
Abstract: A fan blade platform assembly comprises a plate insert shaped and dimensioned to span a gap formed between the opposed facing platforms of adjacent fan blades of a turbo fan engine. The plate insert can be retained in engagement under arresting shoulders provided on the adjacent fan blades by a spring force exerted by a spring insert held captive and in contact between the plate insert and an outer surface of the fan hub.
Abstract translation: 风扇叶片平台组件包括板形插件，其形状和尺寸设计成跨越形成在涡轮风扇发动机的相邻风扇叶片的相对的相对平台之间的间隙。 板插件可以通过由弹簧插入件夹持的弹簧力设置在相邻风扇叶片上的止动肩部下保持接合，并且在板插入件和风扇毂的外表面之间接触。
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公开(公告)号：US07765787B2
公开(公告)日：2010-08-03
申请号：US11780609
申请日：2007-07-20
Applicant: Andreas Eleftheriou , Kevin Walter Lobo , Maurice Weinberg , Quantai Liu
Inventor： Andreas Eleftheriou , Kevin Walter Lobo , Maurice Weinberg , Quantai Liu
IPC: F02K3/02
CPC classification number: F02K3/06 , F01D25/162 , F01D25/24 , F02C7/20 , F05D2230/60 , F05D2240/122 , F05D2240/304 , Y02T50/671
Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.
Abstract translation: 用于燃气轮机的壳体包括提供改进的结构效率的结构。 公开了用于在发动机壳体中传递负载的改进的负载路径和装置。
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Patent Agency Ranking
公开(公告)号：US20080086881A1
公开(公告)日：2008-04-17
申请号：US11537890
申请日：2006-10-02
Applicant: Andreas Eleftheriou , Steven Bokan , Barry Barnett , Steven Hunt , Czeslaw Wojtyczka , John Paterson
Inventor： Andreas Eleftheriou , Steven Bokan , Barry Barnett , Steven Hunt , Czeslaw Wojtyczka , John Paterson
IPC: B23P15/04
CPC classification number: F01D25/24 , F01D21/045 , F05D2230/20 , F05D2230/26 , F05D2230/50 , F05D2240/14 , Y02T50/671 , Y10T29/4932
Abstract: The method is used for making an annular gas turbine engine case, the method comprises flowforming a first area of the preform to provide a first annular case portion having a first thickness and a second area having a second thickness, the first and the second average thickness being different.
Abstract translation: 该方法用于制造环形燃气涡轮发动机壳体，该方法包括流动成形预成型件的第一区域以提供具有第一厚度的第一环形壳体部分和具有第二厚度的第二区域，第一和第二平均厚度 不同
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公开(公告)号：US20080072566A1
公开(公告)日：2008-03-27
申请号：US11535515
申请日：2006-09-27
Applicant: Andreas ELEFTHERIOU , David DENIS
Inventor： Andreas ELEFTHERIOU , David DENIS
IPC: F02K3/02
CPC classification number: F02K3/06 , F02C6/08 , F05D2250/14
Abstract: A gas turbine engine has a compressor assembly and a turbine assembly rotationally mounted on a shaft, the turbine assembly being driven by hot gases discharged from a combustion chamber disposed between the compressor and turbine assemblies and an engine case encasing a portion of the engine, the case having an oblong bleed hole having a major axis parallel to a gaspath direction and a minor axis perpendicular to the gaspath direction.
Abstract translation: 燃气涡轮发动机具有压缩机组件和旋转地安装在轴上的涡轮机组件，涡轮组件由从设置在压缩机和涡轮机组件之间的燃烧室排出的热气体以及封装发动机的一部分的发动机壳体驱动， 壳体具有长轴与气路方向平行的长轴和与气路方向垂直的短轴。
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公开(公告)号：US20070280819A1
公开(公告)日：2007-12-06
申请号：US11757648
申请日：2007-06-04
Applicant: Andreas ELEFTHERIOU , David DENIS , Denis LECLAIR , Yves ROUSSEL
Inventor： Andreas ELEFTHERIOU , David DENIS , Denis LECLAIR , Yves ROUSSEL
IPC: F03B11/02
CPC classification number: F02K3/06 , F01D25/162 , F01D25/24 , F02C7/20 , F05D2230/60 , F05D2240/122 , F05D2240/304 , Y02T50/671
Abstract: A casing for an aircraft turbine bypass engine comprises a splitter having slots to receive and be welded to a plurality of struts extending between an outer ring and an inner hub of the casing.
Abstract translation: 用于飞机涡轮机旁路引擎的壳体包括具有狭槽的分离器，其具有接收并焊接到在壳体的外环和内毂之间延伸的多个支柱。
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公开(公告)号：US06899513B2
公开(公告)日：2005-05-31
申请号：US10613007
申请日：2003-07-07
Applicant: Andreas Eleftheriou
Inventor： Andreas Eleftheriou
CPC classification number: F04D27/0215 , F01D17/105 , F02C9/18 , F04D27/023
Abstract: A compressor bleed valve system for bleeding air from a gas turbine engine compressor comprises a bladder inflatable between at least a collapsed position and an expanded position for selectively opening and closing a compressor airbleed passage.
Abstract translation: 用于从燃气涡轮发动机压缩机排出空气的压缩机排气阀系统包括在至少塌陷位置和膨胀位置之间充气的气囊，用于选择性地打开和关闭压缩机空气通道。
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公开(公告)号：US20050109013A1
公开(公告)日：2005-05-26
申请号：US10883987
申请日：2004-07-06
Applicant: Andreas Eleftheriou , Kevin Lobo , Maurice Weinberg , Quantal Liu
Inventor： Andreas Eleftheriou , Kevin Lobo , Maurice Weinberg , Quantal Liu
CPC classification number: F01D5/22 , F01D25/24 , F02K3/06 , Y02T50/671 , Y02T50/673
Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.
Abstract translation: 用于燃气轮机的壳体包括提供改进的结构效率的结构。 公开了用于在发动机壳体中传递负载的改进的负载路径和装置。
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