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公开(公告)号：US06619908B2
公开(公告)日：2003-09-16
申请号：US09950518
申请日：2001-09-10
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。
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32.发明授权Method of manufacturing seamless self-supporting aerodynamically contoured sheet metal aircraft engine parts using nickel vapor deposition 有权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
IPC分类号： B22D2300
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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公开(公告)号：US09766019B2
公开(公告)日：2017-09-19
申请号：US13036463
申请日：2011-02-28
申请人： Andreas Eleftheriou , David Menheere , Daniel Alecu , Darius Jehangir Karanjia , Daniel Van Den Ende
发明人： Andreas Eleftheriou , David Menheere , Daniel Alecu , Darius Jehangir Karanjia , Daniel Van Den Ende
CPC分类号： F28D21/0003 , F02C7/08 , F02C7/10 , F02C7/143 , F28D9/0018 , F28F2250/102 , F28F2265/26 , F28F2265/30 , Y02T50/675
摘要： A gas turbine engine recuperator 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 passages having an arcuate profile in a plane perpendicular to a central axis of the recuperator to reduce a swirl of the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and providing fluid flow communication between an air inlet and an air outlet, design to sealingly respective plenum of the gas turbine engine.
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公开(公告)号：US09316111B2
公开(公告)日：2016-04-19
申请号：US13326434
申请日：2011-12-15
申请人： Andreas Eleftheriou , Daniel Alecu
发明人： Andreas Eleftheriou , Daniel Alecu
摘要： An active tip clearance control (ATCC) system of a gas turbine engine includes an ejector to selectively drive an air flow passing through the ATCC system. A high pressure air flow as a motive flow of the ejector is controlled by a valve according to engine operation requirements.
摘要翻译： 燃气涡轮发动机的主动顶尖间隙控制（ATCC）系统包括用于选择性地驱动通过ATCC系统的空气流的喷射器。 作为喷射器的动力流动的高压空气流由根据发动机操作要求的阀门控制。
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公开(公告)号：US09109448B2
公开(公告)日：2015-08-18
申请号：US13428720
申请日：2012-03-23
CPC分类号： F01D9/042
摘要： A vane assembly for a gas turbine engine includes an annular shroud having openings therein and a plurality of vanes extending radially from the shroud and each having an extremity received within one of the openings. A grommet is positioned within each opening for shielding the vane extremity from the annular shroud. The grommet includes an annular protrusion for providing sealing between the opening and the vane extremity, and an annular restraint element adjacent the protrusion for retaining the vane in place relative to the shroud.
摘要翻译： 用于燃气涡轮发动机的叶片组件包括其中具有开口的环形护罩和从护罩径向延伸的多个叶片，并且每个叶片具有容纳在一个开口内的末端。 护环位于每个开口内，用于屏蔽叶片末端与环形护罩。 索环包括用于在开口和叶片末端之间提供密封的环形突起，以及邻近突起的环形约束元件，用于相对于护罩保持叶片在适当位置。
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公开(公告)号：US09074489B2
公开(公告)日：2015-07-07
申请号：US13429839
申请日：2012-03-26
CPC分类号： F01D17/162 , F04D9/042 , F04D29/563 , Y10T29/49245
摘要： A connector assembly for variable inlet guide vanes in a compressor case of a gas turbine engine comprises an annular case insert having a plurality of circumferentially distributed open-ended receptacles. The annular case insert is sized so as to be received inside a compressor case, with the plurality of circumferentially distributed open-ended receptacles being in register with holes in the compressor case. Bushings have an outer diameter sized to be received in a respective one of the receptacles of the annular case insert, and an inner diameter adapted to receive a connector portion of a vane. Sets of the bushing and the connector portion of a vane in one of the receptacles forming a rotational joint. A method for installing vanes in a compressor case is also provided.
摘要翻译： 用于燃气涡轮发动机的压缩机壳体中的可变入口导向叶片的连接器组件包括具有多个周向分布的开放式容器的环形壳体插入件。 环形壳体插入件的尺寸被设计成容纳在压缩机壳体内部，多个周向分布的开放式容器与压缩机壳体中的孔对准。 衬套的外径尺寸被设计成容纳在环形盒插入件的插座的相应一个中，并且适于容纳叶片的连接器部分的内径。 在一个容器中形成旋转接头的套管和叶片的连接器部分。 还提供了一种用于在压缩机壳体中安装叶片的方法。
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公开(公告)号：US08956108B2
公开(公告)日：2015-02-17
申请号：US13469712
申请日：2012-05-11
IPC分类号： 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。
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公开(公告)号：US20130202450A1
公开(公告)日：2013-08-08
申请号：US13365557
申请日：2012-02-03
CPC分类号： F01D5/025 , F05D2220/36 , F16B5/02 , F16B19/02 , F16B33/002 , F16B37/065 , F16D1/076 , Y10T29/4973 , Y10T403/7047
摘要： A fan and shaft assembly for a turbofan gas turbine engine comprises a shaft and a fan. Sets of aligned throughbores are respectively of the shaft and the fan, at a junction between the shaft and the fan. Fastening systems are provided for the sets of aligned throughbores. Each fastening system comprises a sleeve received in one of the sets of aligned throughbores and sized to fit without play in the set of aligned throughbores. A head of the sleeve abuts a surface at the junction between the shaft and the fan. A fastener is inserted in the sleeve and extends beyond both ends of the sleeve to clamp the fan to the shaft, the fastener being loosely received in the sleeve. A method for replacing a component of a fastening system retaining a fan to a shaft is provided as well.
摘要翻译： 用于涡轮风扇燃气涡轮发动机的风扇和轴组件包括轴和风扇。 在轴和风扇之间的连接处，排列的通孔组分别为轴和风扇。 提供紧固系统用于对齐的通孔组。 每个紧固系统包括容纳在一组对准的通孔中的套筒，并且其尺寸适于在不对齐的一组对准的通孔中配合。 套筒的头部与轴和风扇之间的连接处的表面相邻。 紧固件插入套筒中并且延伸超过套筒的两端以将风扇夹紧到轴上，紧固件被松动地容纳在套筒中。 还提供了一种用于将保持风扇的紧固系统的部件替换到轴的方法。
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公开(公告)号：US08197189B2
公开(公告)日：2012-06-12
申请号：US11945490
申请日：2007-11-27
IPC分类号： F01D5/10
CPC分类号： F01D5/10 , F01D25/24 , F05D2250/15 , F05D2260/96
摘要： A retaining ring is mounted in frictional engagement with a static gas turbine engine part, such as a compressor shroud, in order to provide frictional damping.
摘要翻译： 保持环安装成与诸如压缩机护罩的静态燃气涡轮发动机部件摩擦接合，以提供摩擦阻尼。
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公开(公告)号：US20080083227A1
公开(公告)日：2008-04-10
申请号：US11543793
申请日：2006-10-06
IPC分类号： F02C1/00
CPC分类号： F01D25/18
摘要： A single oil nozzle unit is mounted in a bearing compartment of a gas turbine engine for providing multiple individual jets for the individual bearing components in the bearing compartment.
摘要翻译： 单个油嘴单元安装在燃气涡轮发动机的轴承室中，用于为轴承室中的各个轴承部件提供多个单独的喷嘴。
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