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21. 发明授权

US6123506A Diffuser pipe assembly 有权
标题翻译：扩散管总成
公开(公告)号：US6123506A
公开(公告)日：2000-09-26
申请号：US233023
申请日：1999-01-20
申请人： Joseph Horace Brand , Andreas Eleftheriou
发明人： Joseph Horace Brand , Andreas Eleftheriou
IPC分类号： F04D29/44
CPC分类号： F04D29/441
摘要： The invention provides a diffuser assembly constructed of internal and external concentrically nested bowl-shaped shells for directing an outward flow of compressed air from a centrifugal compressor impeller to an axially rearward diffused annular flow. The shells can be easily manufactured from nested metal castings thereby eliminating much of the cost and time involved in fabricating prior art diffusers of multiple formed tubes brazed to a separately machined hub. The novel diffuser assembly has two concentrically nested bowl-shaped shells, each shell having an inner peripheral compressor impeller casing about a central opening, and an outer edge. Opposing nested surfaces of the shells have an array of mating grooves separated by abutting seam edges thus defining individual diffuser ducts extending from the compressor impeller casings to the outer shell edges when the shells are secured together.
摘要翻译：本发明提供了一种由内部和外部同心嵌套的碗形壳体构成的扩散器组件，用于将离心式压缩机叶轮向外的压缩空气流引导到轴向向后扩散的环形流。壳可以容易地由嵌套的金属铸件制造，从而消除了制造现有技术的多个成形管钎焊到单独加工的毂的扩散器所花费的大量成本和时间。新型扩散器组件具有两个同心嵌套的碗形壳，每个壳体具有围绕中心开口的内周边压缩机叶轮壳体和外边缘。壳体的相对的嵌套表面具有由邻接的接缝边缘分开的配合凹槽的阵列，从而限定当壳体固定在一起时从压缩机叶轮壳体延伸到外壳边缘的各个扩散器管道。

22. 发明授权

US09498850B2 Structural case for aircraft gas turbine engine 有权
标题翻译：飞机燃气轮机发动机结构
公开(公告)号：US09498850B2
公开(公告)日：2016-11-22
申请号：US13431121
申请日：2012-03-27
申请人： David Denis , Andreas Eleftheriou , David Harold Menheere
发明人： David Denis , Andreas Eleftheriou , David Harold Menheere
IPC分类号： F01D25/24 , B23K31/02 , F01D25/16
CPC分类号： F01D25/243 , B23K31/02 , B23K2101/001 , B23K2101/045 , B23K2101/08 , F01D25/162 , F05D2220/323 , F05D2230/232 , F05D2300/10 , Y02T50/671
摘要： The structural case has an annular body having a central axis and including a plurality of boss sections circumferentially interspaced from one another around the axis by a plurality of arcuate panel sections, each panel section having: two parallel arcuate structural flange members being axially interspaced from one another; a sheet metal wall extending between and interconnecting the two flange members; and at least one rib having an edge welded to the sheet-metal wall.
摘要翻译：结构壳体具有环形体，其具有中心轴线并且包括多个凸起部分，多个凸起部分通过多个弓形面板部分围绕轴线彼此周向间隔开，每个面板部分具有：两个平行的弧形结构凸缘部件，其从一个轴向间隔开另一个; 在两个凸缘构件之间延伸并互连的金属板壁; 以及至少一个具有焊接到金属板壁的边缘的肋。

23. 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。

24. 发明申请

US20100209251A1 FAN BLADE PLATFORM 有权
标题翻译：风扇平台
公开(公告)号：US20100209251A1
公开(公告)日：2010-08-19
申请号：US12372758
申请日：2009-02-18
申请人： David H. Menheere , Andreas Eleftheriou , Philip Ridyard
发明人： David H. Menheere , Andreas Eleftheriou , Philip Ridyard
IPC分类号： F01D5/00 , F01D5/22 , F01D5/30
CPC分类号： F01D5/3007 , F01D11/008 , F05D2220/36 , F05D2300/133 , F05D2300/505
摘要： 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.
摘要翻译：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。

25. 发明授权

US07765787B2 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：US07765787B2
公开(公告)日：2010-08-03
申请号：US11780609
申请日：2007-07-20
申请人： Andreas Eleftheriou , Kevin Walter Lobo , Maurice Weinberg , Quantai Liu
发明人： Andreas Eleftheriou , Kevin Walter Lobo , Maurice Weinberg , Quantai Liu
IPC分类号： F02K3/02
CPC分类号： F02K3/06 , F01D25/162 , F01D25/24 , F02C7/20 , F05D2230/60 , F05D2240/122 , F05D2240/304 , Y02T50/671
摘要： 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.
摘要翻译：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。

26. 发明申请

US20080086881A1 ANNULAR GAS TURBINE ENGINE CASE AND METHOD OF MANUFACTURING 审中-公开
标题翻译：环形气体涡轮发动机及其制造方法
公开(公告)号：US20080086881A1
公开(公告)日：2008-04-17
申请号：US11537890
申请日：2006-10-02
申请人： Andreas Eleftheriou , Steven Bokan , Barry Barnett , Steven Hunt , Czeslaw Wojtyczka , John Paterson
发明人： Andreas Eleftheriou , Steven Bokan , Barry Barnett , Steven Hunt , Czeslaw Wojtyczka , John Paterson
IPC分类号： B23P15/04
CPC分类号： F01D25/24 , F01D21/045 , F05D2230/20 , F05D2230/26 , F05D2230/50 , F05D2240/14 , Y02T50/671 , Y10T29/4932
摘要： 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.
摘要翻译：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

27. 发明授权

US06899513B2 Inflatable compressor bleed valve system 失效
标题翻译：充气式压缩机排气阀系统
公开(公告)号：US06899513B2
公开(公告)日：2005-05-31
申请号：US10613007
申请日：2003-07-07
申请人： Andreas Eleftheriou
发明人： Andreas Eleftheriou
IPC分类号： F01D17/10 , F01D25/12 , F02C9/18 , F03D1/00 , F04D27/02
CPC分类号： F04D27/0215 , F01D17/105 , F02C9/18 , F04D27/023
摘要： 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.
摘要翻译：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。

28. 发明申请

US20050109013A1 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：US20050109013A1
公开(公告)日：2005-05-26
申请号：US10883987
申请日：2004-07-06
申请人： Andreas Eleftheriou , Kevin Lobo , Maurice Weinberg , Quantal Liu
发明人： Andreas Eleftheriou , Kevin Lobo , Maurice Weinberg , Quantal Liu
IPC分类号： F01D5/22 , F01D25/24 , F02K3/06 , F02K3/04
CPC分类号： F01D5/22 , F01D25/24 , F02K3/06 , Y02T50/671 , Y02T50/673
摘要： 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.
摘要翻译：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。

29. 发明授权

US06619908B2 Axial and radial seal arrangement 有权
标题翻译：轴向和径向密封布置
公开(公告)号：US06619908B2
公开(公告)日：2003-09-16
申请号：US09950518
申请日：2001-09-10
申请人： Vittorio Bruno , Andreas Eleftheriou
发明人： Vittorio Bruno , Andreas Eleftheriou
IPC分类号： F01D1102
CPC分类号： F01D11/02 , F01D21/045 , F02C3/067 , F02C7/28 , F16J15/44
摘要： A method and apparatus carrying the method for sealing a radial gap between coaxial inner and outer rotating shafts of a gas turbine engine includes using a radial seal as a main seal to seal the gap for a normal engine operation condition, and using an axial seal as a back-up seal for a double seal of the gap. The radial seal provides a seal which meets relatively restrictive leakage requirements for the normal engine operation condition and the axial seal provides a back-up seal which meets less restrictive leakage requirements but is much more tolerant of radial displacement and vibration between the coaxial inner and outer rotating shafts. Thus, an engine operable condition is ensured under abnormal conditions, such as bird strikes, in which the coaxial relationship between the inner and outer rotating shafts are affected by unbalancing forces caused by the bird strike, thereby causing a failure of the radial seal. The inter-shaft axial and radial seal arrangement according to the present invention has a very simple structure which is convenient and economical to manufacture and maintain.
摘要翻译：携带用于密封燃气涡轮发动机的同轴内外旋转轴之间的径向间隙的方法的装置的方法和装置包括使用径向密封件作为主密封件，以密封用于正常发动机运行状态的间隙，并且使用轴向密封件用于间隙双重密封的备用密封件。径向密封件提供密封件，其对于正常的发动机操作条件而满足相对限制性的泄漏要求，并且轴向密封件提供满足较少限制性泄漏要求的备用密封件，但是更大程度上容许同轴内外部之间的径向位移和振动旋转轴。因此，在异常状态（例如鸟撞击）下确保发动机可操作状态，其中内外旋转轴之间的同轴关系受到由鸟撞击引起的不平衡力的影响，从而导致径向密封的故障。根据本发明的轴间轴向和径向密封装置具有非常简单的结构，其制造和维护方便且经济。

30. 发明授权

US06463992B1 Method of manufacturing seamless self-supporting aerodynamically contoured sheet metal aircraft engine parts using nickel vapor deposition 有权
标题翻译：使用镍蒸汽沉积制造无缝自支撑空气动力学钣金飞机发动机部件的方法
公开(公告)号：US06463992B1
公开(公告)日：2002-10-15
申请号：US09532302
申请日：2000-03-22
申请人： Michael John Dowhan , Joseph Horace Brand , Andreas Eleftheriou , Andrew Robertson Waterston
发明人： Michael John Dowhan , Joseph Horace Brand , Andreas Eleftheriou , Andrew Robertson Waterston
IPC分类号： B22D2300
CPC分类号： C23C16/01 , F02K1/48
摘要： A method of manufacturing a seamless self-supporting metal part using nickel vapor deposition, where the part has a selected minimum thickness, a first aerodynamically contoured surface and a second substantially parallel surface. The method replaces labor intensive welding of individually manufactured sheet metal segments for complex aerodynamic shapes, and produces a part with higher accuracy, less cost, controlled strength and hardness properties. Nickel vapor deposition is commonly used for plating electronic components, and for producing a metallic lining for plastic injection moulds. The seamless sheet metal part is cast by: fabricating a mould with at least one mould surface being a negative of the first surface of the part; enclosing the mould in a nickel vapor deposition chamber; depositing nickel on the mould surface by nickel vapor deposition until a blank of nickel is deposited having at least the minimum thickness and an external deposition surface; and separating the blank from the mould.
摘要翻译：一种使用镍气相沉积制造无缝自支撑金属部件的方法，其中所述部件具有选定的最小厚度，第一空气动力学轮廓表面和第二基本上平行的表面。该方法代替了复杂空气动力学形状的单独制造的金属片段的劳动密集型焊接，并且产生具有更高精度，更低成本，强度和硬度特性的部件。镍蒸汽沉积通常用于电子元件的电镀，以及用于制造注塑模具的金属衬里。无缝钣金件通过以下方式铸造：制造具有至少一个模具表面的模具，该模具表面是该零件的第一表面的负极; 将模具封装在镍蒸镀室中; 通过镍气相沉积将镍沉积在模具表面上，直到沉积至少具有最小厚度和外部沉积表面的镍的坯料; 并将坯料与模具分离。

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