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81. 发明授权

US08740553B2 Nozzle stage for a turbomachine compressor 有权
标题翻译：用于涡轮机压缩机的喷嘴级
公开(公告)号：US08740553B2
公开(公告)日：2014-06-03
申请号：US12981936
申请日：2010-12-30
申请人： Mathieu Caucheteux , Christophe Jacq
发明人： Mathieu Caucheteux , Christophe Jacq
IPC分类号： F01D9/04
CPC分类号： F01D9/042 , F01D9/044 , F01D11/001 , Y02T50/671
摘要： The invention relates to a nozzle stage for a turbomachine compressor, the stage comprising two coaxial shrouds, a radially inner shroud and a radially outer shroud, and radial vanes extending between the shrouds and being connected via their ends to the shrouds, together with a support for abradable material that is mounted by crimping onto the upstream and downstream edges of the inner shroud, the inner shroud presenting openings in which the radially inner ends of the vanes are inserted and fastened. The radially inner ends of the vanes are plane and do not have any projecting tenons.
摘要翻译：本发明涉及一种用于涡轮机械压缩机的喷嘴平台，该台架包括两个同轴护罩，径向内护罩和径向外护罩，以及在护罩之间延伸并且经由其端部连接到护罩的径向叶片以及支撑件对于通过卷曲安装到内护罩的上游和下游边缘上的可磨损材料，内护罩呈现开口，其中叶片的径向内端插入并固定在其中。叶片的径向内端是平面的，没有任何突出的榫头。

82. 发明授权

US08714922B2 Diffuser for decelerating a compressed fluid 有权
标题翻译：用于减压压缩流体的扩散器
公开(公告)号：US08714922B2
公开(公告)日：2014-05-06
申请号：US12523071
申请日：2008-01-24
申请人： Philip Twell
发明人： Philip Twell
IPC分类号： F01D9/04
CPC分类号： F04D29/541 , F01D9/041 , F01D9/042 , F05D2250/11 , F05D2250/18 , F05D2250/181 , F05D2250/182 , F05D2250/324 , F05D2250/70 , F05D2260/36
摘要： A diffuser for decelerating a compressed gas, is provided, which includes a ring divided at circumferential positions around the ring into several arcuate sections, the complete ring is assembled from these sections. The ring defines one or more passages, the cross-section of which increases in the direction of flow of a fluid through the diffuser. The interface between adjacent sections is configured so that relative movement between the sections is prevented. The interface is configured to have a series of interlocking serrations along the axial length of the diffuser. In an embodiment, there are two arcuate sections involving two interfaces, and the peaks and troughs of the serrations of each of the two sections are arranged at an angle to a longitudinal axis of the diffuser. A small relative movement between the sections is achieved when the two angles at the two interfaces have opposite signs.
摘要翻译：提供了用于使压缩气体减速的扩散器，其包括在环周围位置分成几个弧形部分的环，从这些部分组装完整的环。环限定一个或多个通道，其横截面在流体通过扩散器的流动方向上增加。相邻部分之间的界面被配置成防止部分之间的相对移动。该界面构造成沿着扩散器的轴向长度具有一系列互锁锯齿。在一个实施例中，存在两个涉及两个界面的弓形部分，并且两个部分中的每一个的锯齿的峰谷相对于扩散器的纵向轴线成一定角度。当两个界面处的两个角度具有相反的符号时，实现两个部分之间的小的相对运动。

83. 发明授权

US08696311B2 Apparatus and method for gas turbine engine vane retention 有权
标题翻译：燃气轮机叶片保持装置及方法
公开(公告)号：US08696311B2
公开(公告)日：2014-04-15
申请号：US13074295
申请日：2011-03-29
申请人： Andreas Eleftheriou , Richard Ivakitch
发明人： Andreas Eleftheriou , Richard Ivakitch
IPC分类号： F03B1/00
CPC分类号： F01D9/042 , F01D21/045 , F05D2260/30 , F05D2300/43 , F05D2300/432 , F05D2300/6012
摘要： A vane assembly of a gas turbine engine has a plurality of vanes extending radially and inwardly from an annular casing. An outer end of each vane radially and outwardly projects from the casing and is received in one of apertures defined in an elastomeric ring which is placed around the casing. A strap of a non-metallic material is placed in a pre-tensioned condition around the elastomeric ring to compress the elastomeric ring and to radially retain the outer end of each vane.
摘要翻译：燃气涡轮发动机的叶片组件具有从环形壳体径向向内延伸的多个叶片。每个叶片的外端径向向外突出并从壳体伸出并被容纳在围绕壳体放置的弹性环中限定的一个孔中。非金属材料的带子被放置在弹性体环周围的预张紧状态，以压缩弹性体环并径向保持每个叶片的外端。

84. 发明申请

US20140083099A1 MULTI-STAGE HIGH PRESSURE COMPRESSOR CASE 有权
标题翻译：多级高压压缩机箱
公开(公告)号：US20140083099A1
公开(公告)日：2014-03-27
申请号：US13623888
申请日：2012-09-21
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Ken F. Blaney , Neil L. Tatman
IPC分类号： F01D9/04 , B23P11/00 , F02C3/06
CPC分类号： F01D9/042 , F01D9/04 , F01D11/005 , F01D25/24 , Y10T29/49826
摘要： A compressor case assembly according to an exemplary embodiment of this disclosure, among other possible things, includes a case. A plurality of vane stages circumscribe an interior of the case. Each of the plurality of vane stages include a vane guide and at least one window for inserting a respective at least one vane there through. The at least one window is axially aligned with each of the vane guides The at least one window extends from an outer surface of the case into each of the vane guides.
摘要翻译：根据本公开的示例性实施例的压缩机壳体组件以及其他可能的事情包括壳体。多个叶片台围绕壳体的内部。多个叶片级中的每一个包括叶片引导件和用于在其中插入相应的至少一个叶片的至少一个窗口。至少一个窗口与每个叶片引导件轴向对齐。至少一个窗口从壳体的外表面延伸到每个叶片引导件中。

85. 发明授权

US08672623B2 Stator vane assembly 有权
标题翻译：定子叶片总成
公开(公告)号：US08672623B2
公开(公告)日：2014-03-18
申请号：US12720309
申请日：2010-03-09
申请人： Cedric B Harper
发明人： Cedric B Harper
IPC分类号： F01D9/02 , F01D9/04
CPC分类号： F01D9/042 , F05D2230/644 , F05D2250/314
摘要： A stator vane assembly includes: inner and outer vane supports, and vanes extending radially between the supports. The supports have openings for receiving the ends of the vanes, and each vane is connected to the supports by a vane boot. Each vane boot has: a rim portion shaped to locate the boot within the corresponding opening in the vane support, the rim portion engaging with the inner surface defining the opening, an abutting portion for abutting against the vane support in the region surrounding the opening, and a vane pocket for accommodating the end of the vane. The vane pockets of the vane boots are shaped so as to position the vane with a predetermined stagger angle.
摘要翻译：定子叶片组件包括：内叶片和外叶片支撑件以及在支撑件之间径向延伸的叶片。支撑件具有用于接收叶片的端部的开口，并且每个叶片通过叶片引导件连接到支撑件。每个叶片靴具有：成形为将靴子定位在叶片支撑件中的对应开口内的边缘部分，边缘部分与限定开口的内表面接合，用于在围绕开口的区域中抵靠叶片支撑件的抵接部分，以及用于容纳叶片的端部的叶片袋。叶片靴的叶片袋形成为以预定的交错角定位叶片。

86. 发明申请

US20140072419A1 ROTARY MACHINES AND METHODS OF ASSEMBLING 审中-公开
标题翻译：旋转机器和组装方法
公开(公告)号：US20140072419A1
公开(公告)日：2014-03-13
申请号：US13614297
申请日：2012-09-13
申请人： Manish Joshi , David Orus Fitts , Robert Edward Deallenbach
发明人： Manish Joshi , David Orus Fitts , Robert Edward Deallenbach
IPC分类号： F01D9/04 , B23P15/00 , B05B1/00
CPC分类号： F01D9/042 , B05B15/06 , B05B15/60 , F01D5/3092 , F01D25/246 , F05D2220/31 , F05D2240/128 , Y10T29/49245
摘要： A nozzle assembly is provided. The nozzle assembly includes at least one stationary nozzle. An outer ring having a predefined shape includes at least one groove defined therein and the groove is configured to receive at least a portion of the stationary nozzle therein. A coupling portion is formed integrally with the stationary nozzle or the outer ring such that the coupling portion extends outwardly therefrom. An attachment member is coupled to the coupling portion to facilitate substantially restricting movement of the stationary nozzle when the outer ring is substantially distorted.
摘要翻译：提供喷嘴组件。喷嘴组件包括至少一个固定喷嘴。具有预定形状的外圈包括限定在其中的至少一个凹槽，并且凹槽构造成在其中容纳固定喷嘴的至少一部分。联接部分与固定喷嘴或外环一体地形成，使得联接部分从其向外延伸。附接构件联接到联接部分，以便当外环基本变形时，基本上限制静止喷嘴的运动。

87. 发明授权

US08668448B2 Airfoil attachment arrangement 有权
标题翻译：翼型附件装置
公开(公告)号：US08668448B2
公开(公告)日：2014-03-11
申请号：US12915575
申请日：2010-10-29
申请人： Jorge I. Farah , Jaisukhlal V. Chokshi
发明人： Jorge I. Farah , Jaisukhlal V. Chokshi
IPC分类号： F01D5/32
CPC分类号： F01D9/042
摘要： An example airfoil retention arrangement includes a retention assembly having a first retention segment and a second retention segment. Each of the retention segments is separately moveable to an installed position relative to an airfoil assembly and a support structure. The retention segments each have a portion position between a lip of the airfoil assembly and a collar of the support structure when the retention segments are in the installed position. The retention assembly is configured to limit radial movement of an airfoil relative to the support structure when in the installed position.
摘要翻译：示例性翼型保持装置包括具有第一保持段和第二保留段的保持组件。每个保持段分别可移动到相对于翼型组件和支撑结构的安装位置。当保持段处于安装位置时，保持段各自具有在翼型组件的唇缘和支撑结构的套环之间的部分位置。保持组件构造成在处于安装位置时限制翼型件相对于支撑结构的径向移动。

88. 发明申请

US20140056711A1 AIRCRAFT ENGINE ANNULAR SHROUD COMPRISING AN OPENING FOR THE INSERTION OF BLADES 有权
标题翻译：包括开放刀片的飞机发动机安全防护罩
公开(公告)号：US20140056711A1
公开(公告)日：2014-02-27
申请号：US14112071
申请日：2012-05-03
申请人： Laurent Gilles Dezouche
发明人： Laurent Gilles Dezouche
IPC分类号： F01D5/22
CPC分类号： F01D5/225 , F01D9/042 , F01D25/246 , F04D29/542 , F04D29/644 , F05D2240/40 , Y10T29/4932
摘要： An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into the annular groove; and a closure device for closing off the insertion opening.
摘要翻译：飞机发动机环形护罩在其内表面上包括能够接纳多个叶片根部的周边环形槽; 用于将叶片根部插入到环形槽中的插入开口; 以及用于封闭插入开口的闭合装置。

89. 发明申请

US20140003926A1 COMPRESSOR FOR A GAS TURBINE AND METHOD FOR REPAIRING AND/OR CHANGING THE GEOMETRY OF AND/OR SERVICING SAID COMPRESSOR 审中-公开
标题翻译：用于燃气涡轮机的压缩机和修理和/或更改压缩机和/或维修压缩机的几何和方法
公开(公告)号：US20140003926A1
公开(公告)日：2014-01-02
申请号：US13929366
申请日：2013-06-27
申请人： ALSTOM Technology Ltd
发明人： Tobias STEFFEN , Marc RAUCH , Mauro CORRADI , Bjoern VEITH
IPC分类号： F01D9/04
CPC分类号： F01D9/042 , F01D11/12 , F04D29/023 , F04D29/526 , F05D2220/3216 , F05D2230/80 , F05D2240/11 , F05D2300/611 , Y10T29/49238
摘要： A compressor for a gas turbine having a rotor rotating about an axis and a housing coaxially surrounding the rotor, thereby defining a flow channel between the rotor and the housing for a fluid to be compressed. Alternating rows of vanes and blades are arranged within the flow channel, with the vanes being mounted in the inner wall of the housing, and the blades being mounted in the outer wall of the rotor.
摘要翻译：一种用于燃气轮机的压缩机，其具有围绕轴线旋转的转子和同轴地围绕转子的壳体，从而在转子和壳体之间限定用于待压缩流体的流动通道。叶片和叶片的交替排布置在流动通道内，其中叶片安装在壳体的内壁中，并且叶片安装在转子的外壁中。

90. 发明授权

US08562292B2 Steam turbine singlet interface for margin stage nozzles with pinned or bolted inner ring 有权
标题翻译：带有固定或螺栓连接的内圈的边缘级喷嘴的蒸汽轮机单线接口
公开(公告)号：US08562292B2
公开(公告)日：2013-10-22
申请号：US12958807
申请日：2010-12-02
申请人： Steven Sebastian Burdgick , Dominick Joseph Werther
发明人： Steven Sebastian Burdgick , Dominick Joseph Werther
IPC分类号： F01D9/02
CPC分类号： F01D9/042
摘要： A steam turbine singlet nozzle airfoil with integral outer sidewall is engaged with an inner ring and an outer ring in a nozzle assembly. The interface of the outer sidewall with the outer ring may include a plurality of mechanical hooks on one or both of the upstream face and the outer radial face of the outer sidewall that engage with complimentary structures on the outer ring. The outer interface may further include low energy welds along limited distances of one or both of the upstream or downstream interface of the outer sidewall and the outer ring. An inner radial end of the singlet nozzle airfoil is pinned into position and fastened to the inner ring. Without a need for high heat welds, distortion of the airfoil and the steam flow path and the associated rework is eliminated and stage performance is improved.
摘要翻译：具有整体外侧壁的蒸汽轮机单线喷嘴翼型件与喷嘴组件中的内环和外环接合。外侧壁与外环的界面可以包括在外侧壁的上游面和外径向面中的一个或两个上与外环上的互补结构接合的多个机械钩。外界面还可以包括沿着外侧壁和外环的上游或下游界面中的一个或两个的有限距离的低能量焊缝。单列喷嘴翼型的内径向端部被固定到位并紧固到内圈。不需要高热焊接，消除了翼型件和蒸汽流动路径的变形以及相关的返工，并且提高了工作台性能。

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