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1.发明申请Sleeve and housing assembly and method of adhesively bonding sleeve to housing 审中-公开套筒和壳体组件以及将套筒粘合到外壳上的方法公开(公告)号：US20080073855A1
公开(公告)日：2008-03-27
申请号：US11513302
申请日：2006-08-31
申请人： Richard Ivakitch , Philip Ridyard , David Denis
发明人： Richard Ivakitch , Philip Ridyard , David Denis
IPC分类号： F16J15/447
CPC分类号： F01D25/162 , F01D25/183 , F02C7/28 , F05D2230/23 , F05D2240/55
摘要： A sleeve mounting arrangement for use with a rotary component comprises a housing having a sleeve reception aperture defined along a rotation axis of the rotary component. The sleeve is positioned and retained within the housing by means of an adhesive provided in a pocket defined between the sleeve and the housing.
摘要翻译： 与旋转部件一起使用的套筒安装装置包括具有沿着旋转部件的旋转轴线限定的套筒接收孔的壳体。 套筒通过设置在套筒和壳体之间的凹穴中的粘合剂定位并保持在壳体内。
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公开(公告)号：US07908869B2
公开(公告)日：2011-03-22
申请号：US11532564
申请日：2006-09-18
申请人： Richard Ivakitch , Philip Ridyard , Patrick Chiu
发明人： Richard Ivakitch , Philip Ridyard , Patrick Chiu
CPC分类号： F04D29/4206 , F01D5/043 , F01D11/16 , F01D25/246 , F04D29/624 , F05B2260/301 , F05D2230/642 , F05D2250/70
摘要： 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, the compressor having a centrifugal impeller for pressurizing and impelling air into the combustion chamber. The engine also includes an impeller shroud covering the bladed portion of the centrifugal impeller, the impeller shroud having a support bracket having a thin and curved load-isolating profile for supporting a strut that secures the impeller shroud to a case of the engine.
摘要翻译： 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驱动，该压缩机具有用于对空气进行加压和推动的离心式叶轮 进入燃烧室。 发动机还包括覆盖离心式叶轮的叶片部分的叶轮护罩，叶轮护罩具有支撑托架，其具有薄且弯曲的负载隔离轮廓，用于支撑将叶轮护罩固定到发动机壳体上的支柱。
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公开(公告)号：US09951639B2
公开(公告)日：2018-04-24
申请号：US13358889
申请日：2012-02-10
CPC分类号： F01D11/005 , F01D9/042 , F05D2240/55 , Y10T29/49245
摘要： Vane assemblies for gas turbine engines and methods for assembling vane assemblies are disclosed. The vane assemblies may include at least one shroud having at least one vane-receiving portion, at least one vane having at least one end portion received in the vane-receiving portion, and at least one sealing member having an uncompressed cross-section that is substantially circular. The sealing member(s) are disposed between and in contact with the end portion of the vane and the vane-receiving portion of the shroud.
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公开(公告)号：US08967978B2
公开(公告)日：2015-03-03
申请号：US13558875
申请日：2012-07-26
申请人： David Denis , Richard Ivakitch
发明人： David Denis , Richard Ivakitch
CPC分类号： F01D5/025 , F02K3/06 , F05D2220/36 , Y10T29/49234 , Y10T29/49321
摘要： In a gas turbine engine, a fan rotor and a compressor rotor are connected to a joint which is attached to a shaft. The fan rotor is connected to the joint by a plurality of fasteners extending through mounting openings in the joint and through apertures in the fan rotor. A standard retaining ring is attached to the joint to cover a portion of an enlarged head of each of the respective fasteners in order to prevent removal of the respective fasteners from the mounting openings in the joint before the respective fasteners are connected to the fan rotor.
摘要翻译： 在燃气涡轮发动机中，风扇转子和压缩机转子连接到附接到轴的接头。 风扇转子通过多个紧固件连接到接头，多个紧固件延伸穿过接头中的安装开口并且通过风扇转子中的孔。 标准保持环附接到接头以覆盖每个相应紧固件的扩大头部的一部分，以便在相应的紧固件连接到风扇转子之前防止相应的紧固件从接头中的安装开口移除。
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公开(公告)号：US20130205800A1
公开(公告)日：2013-08-15
申请号：US13358889
申请日：2012-02-10
CPC分类号： F01D11/005 , F01D9/042 , F05D2240/55 , Y10T29/49245
摘要： Vane assemblies for gas turbine engines and methods for assembling vane assemblies are disclosed. The vane assemblies may include at least one shroud having at least one vane-receiving portion, at least one vane having at least one end portion received in the vane-receiving portion, and at least one sealing member having an uncompressed cross-section that is substantially circular. The sealing member(s) are disposed between and in contact with the end portion of the vane and the vane-receiving portion of the shroud.
摘要翻译： 公开了用于燃气涡轮发动机的叶片组件和组装叶片组件的方法。 叶片组件可以包括至少一个护罩，其具有至少一个叶片接收部分，至少一个叶片，其具有容纳在叶片容纳部分中的至少一个端部，以及至少一个具有未压缩横截面的密封构件， 大致圆形。 密封构件设置在叶片的端部和护罩的叶片接收部分之间并与之接触。
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公开(公告)号：US08998574B2
公开(公告)日：2015-04-07
申请号：US13223701
申请日：2011-09-01
CPC分类号： F01D5/225 , F05D2260/30
摘要： 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.
摘要翻译： 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：US20130251517A1
公开(公告)日：2013-09-26
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：US09353626B2
公开(公告)日：2016-05-31
申请号：US13614584
申请日：2012-09-13
CPC分类号： F01D5/025 , F02K3/06 , F04D29/266 , F05D2230/60 , F05D2250/292 , F05D2260/30 , F16D2001/0903 , Y10T29/49316
摘要： A rotor assembly for a gas turbine engine, with an annular sleeve having an inner member connected around the shaft to rotate together therewith and having an outer member with a first end connected to the inner member, the outer member defining an annular continuous frustoconical inner surface angled such as to extend closer to the central axis near the first end. A rotor disc includes an annular protuberance extending radially inwardly of the outer member and forced toward the first end, and having an annular continuous frustoconical outer surface complementary to the inner surface of the outer member and in torque-transmitting engagement therewith. The assembly includes means for axially pressing the sleeve and the disc against one another to maintain the complementary frustoconical surfaces in torque-transmitting engagement. A method of engaging a rotor disc to a driving shaft in a gas turbine engine is also provided.
摘要翻译： 一种用于燃气涡轮发动机的转子组件，其具有环形套筒，该内部构件围绕轴连接以与其一起旋转并具有外部构件，第一端连接到内部构件，外部构件限定环形连续的截头圆锥形内表面 成角度的，以便靠近第一端的中心轴线延伸。 转子盘包括沿着外部构件的径向向内延伸并被迫朝向第一端的环形突起，并且具有与外部构件的内表面互补的环形连续的截头圆锥形外表面和与其成扭矩传递接合。 组件包括用于将套筒和盘片彼此轴向按压以保持互补的截头圆锥形表面在扭矩传递接合中的装置。 还提供了一种将转子盘接合到燃气涡轮发动机中的驱动轴的方法。
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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
CPC分类号： F01D21/04 , F01D5/066 , F01D21/045 , F05D2220/36 , F05D2250/75 , Y10T29/49318
摘要： 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.
摘要翻译： 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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公开(公告)号：US07850173B2
公开(公告)日：2010-12-14
申请号：US11513230
申请日：2006-08-31
申请人： Richard Ivakitch
发明人： Richard Ivakitch
IPC分类号： F16J15/447 , B23P6/00
CPC分类号： F01D11/02 , B23K2101/001 , B23P6/005 , F05D2230/10 , F05D2230/232 , F05D2230/80 , F05D2250/70 , F16J15/44 , F16J15/445 , Y10T29/49718 , Y10T29/49719 , Y10T29/49728 , Y10T29/49737
摘要： A repairable labyrinth seal of a gas turbine engine comprises at least one fin having a base with a thickness and a tip portion extending therefrom. A shoulder distinguishes the base from the tip portion. The shoulder defines a machining site suitable for receiving a welded replacement piece for shaping a new tapered tip portion following removal of a worn tapered tip portion.
摘要翻译： 燃气涡轮发动机的可修复迷宫式密封件包括至少一个翅片，其具有厚度的基部和从其延伸的尖端部分。 肩部将基部与尖端部分区分开。 肩部限定了适于接收用于在移除磨损的锥形尖端部分之后成形新的锥形尖端部分的焊接更换件的加工位置。
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