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公开(公告)号：US06371725B1
公开(公告)日：2002-04-16
申请号：US09607753
申请日：2000-06-30
IPC分类号： F01D102
CPC分类号： F01D5/14 , F01D9/042 , F02K3/06 , F05B2260/301 , F05D2220/327 , F05D2230/60 , F05D2240/80 , Y02T50/671 , Y02T50/673
摘要： A fan outlet guide vane includes integral outer and inner platforms conforming to arcuate sides thereof, and multiple mounting bosses on the platforms. The platform sides are arcuate to conform with the vane sides for improving aerodynamic efficiency. The multiple mounting bosses improve mounting of the vanes to corresponding supporting rings.
摘要翻译： 风扇出口导叶包括符合其弓形侧面的整体外部和内部平台，以及平台上的多个安装凸台。 平台侧面弧形以符合叶片侧面，以提高空气动力学效率。 多个安装凸台改善了叶片对相应支撑环的安装。
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公开(公告)号：US08371812B2
公开(公告)日：2013-02-12
申请号：US12325174
申请日：2008-11-29
IPC分类号： F03B11/02
CPC分类号： F01D25/28 , F01D9/02 , F01D9/065 , F05D2230/60
摘要： A turbine frame assembly for a gas turbine engine includes: (a) a turbine frame including: (i) an outer ring; (ii) a hub; (ii) a plurality of struts extending between the hub and the outer ring; (b) a two-piece strut fairing surrounding each of the struts, including: (i) an inner band; (ii) an outer band; and (iii) an airfoil-shaped vane extending between the inner and outer bands; (d) a plurality of nozzle segments disposed between the outer ring and the hub, each nozzle segment being an integral metallic casting including: (i) an arcuate outer band; (ii) an arcuate inner band; and (ii) an airfoil-shaped vane.
摘要翻译： 一种用于燃气涡轮发动机的涡轮机框架组件包括：（a）涡轮机框架，包括：（i）外圈; （ii）枢纽; （ii）在轮毂和外圈之间延伸的多个支柱; （b）围绕每个支柱的两件式支柱整流罩，包括：（i）内带; （ii）外带; 和（iii）在内带和外带之间延伸的翼型叶片; （d）设置在外圈和轮毂之间的多个喷嘴段，每个喷嘴段是一体的金属铸件，其包括：（i）弓形外带; （ii）弧形内带; 和（ii）翼型叶片。
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3.发明申请公开(公告)号：US20100135786A1
公开(公告)日：2010-06-03
申请号：US12325175
申请日：2008-11-29
IPC分类号： F01D25/00
CPC分类号： F01D9/065 , F01D25/18 , F05D2260/201
摘要： A service tube apparatus for a gas turbine engine includes a service tube assembly having: (a) an elongated, hollow service tube; and (b) a service tube baffle surrounding the service tube which is pierced with a plurality of impingement cooling holes.
摘要翻译： 一种用于燃气涡轮发动机的服务管装置，包括一个服务管组件，其具有：（a）细长的中空服务管; 和（b）围绕服务管的服务管挡板，其被多个冲击冷却孔刺穿。
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公开(公告)号：US20100132374A1
公开(公告)日：2010-06-03
申请号：US12325174
申请日：2008-11-29
IPC分类号： F02C7/20
CPC分类号： F01D25/28 , F01D9/02 , F01D9/065 , F05D2230/60
摘要： A turbine frame assembly for a gas turbine engine includes: (a) a turbine frame including: (i) an outer ring; (ii) a hub; (ii) a plurality of struts extending between the hub and the outer ring; (b) a two-piece strut fairing surrounding each of the struts, including: (i) an inner band; (ii) an outer band; and (iii) an airfoil-shaped vane extending between the inner and outer bands; (d) a plurality of nozzle segments disposed between the outer ring and the hub, each nozzle segment being an integral metallic casting including: (i) an arcuate outer band; (ii) an arcuate inner band; and (ii) an airfoil-shaped vane.
摘要翻译： 一种用于燃气涡轮发动机的涡轮机框架组件包括：（a）涡轮机框架，包括：（i）外圈; （ii）枢纽; （ii）在轮毂和外圈之间延伸的多个支柱; （b）围绕每个支柱的两件式支柱整流罩，包括：（i）内带; （ii）外带; 和（iii）在内带和外带之间延伸的翼型叶片; （d）设置在外圈和轮毂之间的多个喷嘴段，每个喷嘴段是一体的金属铸件，其包括：（i）弓形外带; （ii）弧形内带; 和（ii）翼型叶片。
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公开(公告)号：US06296203B1
公开(公告)日：2001-10-02
申请号：US09578120
申请日：2000-05-24
IPC分类号： B64D2726
CPC分类号： B64D27/18 , B64D27/26 , B64D2027/266 , B64D2027/268 , F16C11/0614 , F16C2326/43
摘要： A thrust mount includes a platform mountable to an aircraft pylon, and includes end clevises and a center clevis therebetween. An equalizer lever includes opposite ends, and a center therebetween pivotally joined to the center clevis. Thrust links are pivotally joined to the lever ends. And, a pair of elastomeric snubbers are disposed adjacent respective ends of the lever inside the end clevises in frictional abutment therebetween.
摘要翻译： 推力支架包括可安装到飞机塔架的平台，并且包括端部托架和其间的中心卡环。 平衡杠杆包括相对的端部，并且其间枢转地连接到中心钩的中心。 枢轴连杆可枢转地连接到杠杆端。 并且，一对弹性缓冲器设置在杠杆的相应端部之内，在端部夹具内部的摩擦接合处。
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公开(公告)号：US07771164B2
公开(公告)日：2010-08-10
申请号：US11612289
申请日：2006-12-18
IPC分类号： F03B3/16
CPC分类号： F01D9/042 , F05D2230/64 , Y10T29/49245
摘要： A method of assembling a turbine includes positioning a turbine nozzle against a forward inner nozzle support extending from a rotor assembly, and coupling a cover to the forward inner nozzle support. The method also includes inserting a tab that extends from the cover within at least one aperture defined in the turbine nozzle.
摘要翻译： 组装涡轮机的方法包括将涡轮喷嘴定位在从转子组件延伸的前向内部喷嘴支撑件上，以及将盖子连接到前部内部喷嘴支撑件。 该方法还包括在限定在涡轮喷嘴中的至少一个孔内插入从盖延伸的突片。
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公开(公告)号：US07147429B2
公开(公告)日：2006-12-12
申请号：US10942765
申请日：2004-09-16
IPC分类号： F01B25/16
CPC分类号： F01D11/08 , F01D5/143 , F01D5/225 , F05D2250/70 , F05D2260/30 , Y02T50/67 , Y02T50/673
摘要： A turbine assembly includes a shroud for being mounted around a last stage of the low pressure turbine rotor. The shroud includes an arcuate body having spaced-apart forward and aft ends and spaced-apart circumferential ends. Attachments are provided for securing the shroud body to the surrounding engine case. An arcuate extension member protrudes rearward from the aft end of the shroud body. The extension member has an inner surface which defines a portion of the gas flowpath through the engine. Seals may be provided to prevent leakage between adjacent shroud segments. The shroud is especially useful for protecting a downstream turbine frame from debris and thermal stress.
摘要翻译： 涡轮组件包括用于安装在低压涡轮转子的最后级上的护罩。 护罩包括弓形体，其具有间隔开的前端和后端以及间隔开的圆周端。 提供了用于将护罩主体固定到周围的发动机壳体上的附件。 弓形延伸构件从护罩主体的后端向后突出。 延伸构件具有限定通过发动机的气体流径的一部分的内表面。 可以设置密封件以防止相邻护罩段之间的泄漏。 护罩特别适用于保护下游涡轮机架免受碎片和热应力。
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公开(公告)号：US08328511B2
公开(公告)日：2012-12-11
申请号：US12486126
申请日：2009-06-17
IPC分类号： F01D9/02
CPC分类号： F01D25/246 , F01D9/041 , F05D2230/642 , F05D2250/71 , F05D2250/711 , F05D2250/712 , Y02T50/671 , Y02T50/673
摘要： A turbine nozzle includes radially inner and outer bands integrally joined to opposite ends of an airfoil. The outer band has forward and aft hooks extending radially outwardly at axially opposite ends. And the hooks have different prechorded circumferential curvatures.
摘要翻译： 涡轮喷嘴包括一体地连接到翼型件的相对端的径向内部和外部带。 外带具有在轴向相对端径向向外延伸的前钩和后钩。 并且钩具有不同的前置圆周曲率。
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公开(公告)号：US06843449B1
公开(公告)日：2005-01-18
申请号：US10774771
申请日：2004-02-09
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268 , Y02T50/44
摘要： A fail-safe lug is carried by an engine frame member and receives a clevis carried by an engine mount member. The mount member includes side links that transmit transverse loads between the engines and the airframe and a thrust link that transmits axial, engine thrust loads between the engine and the airframe. A fail-safe pin is carried by the clevis and has an outer diameter that is smaller than an aperture in the lug and through which the pin passes, so that no loads are imposed on the fail-safe pin in normal operation. When one or more of the links are no longer capable of transmitting loads, the fail-safe arrangement becomes operative to accommodate the loads transmitted between the engine and the airframe.
摘要翻译： 发动机框架构件承载故障安全接线片，并接收由发动机安装构件承载的U形夹。 安装构件包括在发动机和机身之间传递横向载荷的侧连杆和在发动机和机身之间传递轴向的发动机推力载荷的推力连杆。 一个故障安全销由U形夹承载，并且外径小于凸耳中的孔径，并且销通过该孔，从而在正常操作中不会对故障安全销施加负载。 当一个或多个链路不再能够发送负载时，故障安全装置可操作以适应发动机和机身之间传递的负载。
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公开(公告)号：US06401448B1
公开(公告)日：2002-06-11
申请号：US09652179
申请日：2000-08-31
IPC分类号： F02C720
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268 , F02C7/20
摘要： A system for mounting an aircraft engine to an aircraft includes four forward mounting features, two mid mounting features, and four aft mounting features disposed on the engine. The forward, mid and the aft mounting features, respectively, are equally spaced circumferentially about the engine. The method of mounting the engine includes connecting the first and fourth forward mounting features to mounting structure, the first and fourth aft mounting features to mounting structure, and the first and second mid mounting features to mounting structure when the aircraft engine is used in a top mounted installation. Alternatively, the first and second forward mounting features, the first and second aft mounting features, and the first mid mounting feature are connected to mounting structure when the aircraft engine is used in a first side mounted installation; or the third and fourth forward mounting features, the third and fourth aft mounting features, and the second mid mounting feature are connected to mounting structure when the aircraft engine is used in a second side mounted installation. Another arrangement includes connecting the second and third forward mounting features, the second and third aft mounting features, and the first and second mid mounting features to mounting structure when the aircraft engine is used in a bottom mounted installation.
摘要翻译： 用于将飞机发动机安装到飞行器的系统包括四个前进安装特征，两个中间安装特征以及设置在发动机上的四个后部安装特征。 分别的前，后和后安装特征围绕发动机周向等间隔。 安装发动机的方法包括将第一和第四前进安装特征连接到安装结构，第一和第四后部安装特征连接到安装结构，并且当飞机发动机用于顶部时，第一和第二中部安装特征与安装结构 安装安装。 或者，当在第一侧面安装的设备中使用飞机发动机时，第一和第二正向安装特征，第一和第二后部安装特征以及第一中间安装特征连接到安装结构; 或第三和第四前进安装特征，第三和第四后部安装特征，并且当飞机发动机用于第二侧面安装装置时，第二中间安装特征连接到安装结构。 另一种布置包括当飞机发动机用于底部安装的装置时，连接第二和第三前进安装特征，第二和第三后部安装特征，以及将第一和第二中间安装特征连接到安装结构。
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