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1. 发明申请

US20180087397A1 RETAINING RING END GAP FEATURES 审中-公开
公开(公告)号：US20180087397A1
公开(公告)日：2018-03-29
申请号：US15274306
申请日：2016-09-23
申请人： United Technologies Corporation
发明人： Joseph T. Caprario , Noah Wadsworth , Mark E. Marler , James P. Allore , Elizabeth F. Vinson
IPC分类号： F01D25/04 , F01D9/02
CPC分类号： F01D25/04 , F01D5/3015 , F01D5/323 , F01D9/02 , F05D2220/32 , F05D2260/30 , F05D2260/36
摘要： A gas turbine engine and a retaining ring are disclosed. The gas turbine engine includes a rotating disc assembly, including a rotating disc, a cover plate, and a retaining ring disposed between the rotating disc and the cover plate, wherein the retaining ring axially retains the rotating disc and the cover plate, the retaining ring including a rotating disc face to interface with the rotating disc; a cover plate face to interface with the cover plate; and an end gap portion defining an end gap, wherein at least one of the rotating disc face, the cover plate face, and the end gap portion includes a stress reducing feature.

2. 发明申请

US20170218776A1 TURBINE BLADE ATTACHMENT CURVED RIB STIFFENERS 审中-公开
公开(公告)号：US20170218776A1
公开(公告)日：2017-08-03
申请号：US15009366
申请日：2016-01-28
申请人： United Technologies Corporation
发明人： Charles Thistle , Mohamed Hassan
IPC分类号： F01D5/14 , F01D5/30 , F01D5/18
CPC分类号： F01D5/147 , F01D5/081 , F01D5/082 , F01D5/18 , F01D5/3007 , F01D5/3038 , F01D5/323 , F01D5/326 , F05D2220/32 , F05D2230/00 , F05D2230/411 , F05D2230/53 , F05D2230/90 , F05D2240/24 , F05D2240/30 , F05D2250/141 , F05D2250/712 , F05D2260/20 , F05D2260/941 , F05D2300/133 , F05D2300/174 , F05D2300/175 , F05D2300/177 , F05D2300/605 , F05D2300/607 , Y02T50/676
摘要： The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam. The fir tree coupling may comprise a channel through the rounded base across a portion of the radius of curvature from the first side to the second side. The channel may comprise a sidewall having a sidewall step cut into a portion of the channel sidewall.

3. 发明授权

US09593596B2 Compliant intermediate component of a gas turbine engine 有权
标题翻译：符合燃气轮机的中间部件
公开(公告)号：US09593596B2
公开(公告)日：2017-03-14
申请号：US14142754
申请日：2013-12-28
申请人： Rolls-Royce Corporation
发明人： Richard C. Uskert , David J. Thomas , Adam L. Chamberlain
IPC分类号： F01D25/26 , F01D5/28 , F01D5/30 , F01D5/32 , F01D11/00 , F01D25/14 , F01D25/28 , F04D29/32 , F04D29/02
CPC分类号： F01D25/26 , F01D5/284 , F01D5/3007 , F01D5/323 , F01D11/006 , F01D25/14 , F01D25/28 , F04D29/023 , F04D29/322 , F05D2260/941 , F05D2300/6032 , F05D2300/6033 , Y10T29/4932
摘要： One aspect of present application provides an intermediate structure in a gas turbine engine. The intermediate structure is positioned between a first component and another component. The first component may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure.
摘要翻译：本申请的一个方面在燃气涡轮发动机中提供中间结构。中间结构位于第一部件和另一部件之间。第一组分可以是复合组分。组件可能是互锁的。中间结构可以是承载。还公开了使用中间结构的方法。

4. 发明授权

US09540093B2 Bladed rotor wheel for a turbine engine 有权
标题翻译：用于涡轮发动机的叶片转子轮
公开(公告)号：US09540093B2
公开(公告)日：2017-01-10
申请号：US14236254
申请日：2012-08-02
申请人： Luc Henri Chatenet , John Le Quellec
发明人： Luc Henri Chatenet , John Le Quellec
IPC分类号： B64C11/04 , F01D5/32 , F04D29/32 , F04D29/66 , F01D5/30
CPC分类号： B64C11/04 , F01D5/3092 , F01D5/323 , F04D29/322 , F04D29/668 , F05D2260/30 , Y02T50/672 , Y10T29/49332
摘要： A bladed rotor wheel for a turbine engine, the rotor wheel including a disk including, formed in its outer periphery, at least one slot for mounting the roots of blades, and a spacer mounted between each blade root and a bottom of the slot. The spacer includes at least one member of type that is bistable in position and that can occupy a first stable position for assembly or disassembly in which the member does not exert force on the blade root, and a second stable position in which the bistable member exerts a radial force on the blade root. The spacer also includes at least one resilient damper member mounted between the bottom of the slot and the blade root.
摘要翻译：一种用于涡轮发动机的叶片转子轮，所述转子轮包括盘，所述盘包括在其外周形成至少一个用于安装叶根的至少一个槽和安装在每个叶根和槽的底部之间的间隔件。间隔件包括至少一个类型的构件，其中双稳态的位置可以占据用于组装或拆卸的第一稳定位置，其中构件不对叶片根施加力;以及第二稳定位置，双稳态构件叶片根部的径向力。间隔件还包括安装在槽的底部和叶片根部之间的至少一个弹性阻尼器构件。

5. 发明授权

US09470099B2 Securing device for axially securing a blade root of a turbomachine blade 有权
标题翻译：用于轴向固定涡轮机叶片的叶根的固定装置
公开(公告)号：US09470099B2
公开(公告)日：2016-10-18
申请号：US13885045
申请日：2011-11-11
申请人： Rudolf Stanka , Manfred Dopfer , Martin Pernleitner , Wilfried Schuette
发明人： Rudolf Stanka , Manfred Dopfer , Martin Pernleitner , Wilfried Schuette
IPC分类号： F01D5/30 , F01D5/26 , F01D5/32
CPC分类号： F01D5/3007 , F01D5/26 , F01D5/3092 , F01D5/323 , F05D2250/71 , F05D2300/501
摘要： A securing device (20) for axially securing a blade root (12) of a blade in a groove (11) of a turbine engine. The outer contour (24) of the securing device (20) that faces a groove wall, in particular a groove base (33), is curved at least in some regions, the outer contour (24) having three different radii (R1, R2, R3) in some regions.
摘要翻译：一种用于将叶片的叶根（12）轴向固定在涡轮发动机的凹槽（11）中的固定装置（20）。固定装置（20）的面向凹槽壁的外轮廓（24）至少在一些区域中弯曲，外轮廓（24）具有三个不同的半径（R1，R2 ，R3）。

6. 发明授权

US09429030B2 Device for locking a root of a rotor blade 有权
标题翻译：用于锁定转子叶片根部的装置
公开(公告)号：US09429030B2
公开(公告)日：2016-08-30
申请号：US13816083
申请日：2011-08-08
申请人： Jacques Rene Bart , Antoine Jean-Philippe Beaujard
发明人： Jacques Rene Bart , Antoine Jean-Philippe Beaujard
IPC分类号： F01D5/32 , F01D5/30
CPC分类号： F01D5/326 , F01D5/3084 , F01D5/323
摘要： A device for locking a root of a rotor blade in a groove in a rotor disk of a turbomachine including: a circular ring sector configured to be mounted, transversely to the axis of the turbomachine, in a groove in the rotor disk; at least one locking wedge, which is rigidly secured and perpendicular to the ring sector, and extends parallel to the axis of the ring sector so as to hold the root of the blade radially in the groove; and at least one locking tooth extending from the ring sector radially with respect to the axis of the ring sector, so as to prevent the root of the blade from moving axially in the groove.
摘要翻译：一种用于将转子叶片的根部锁定在涡轮机的转子盘中的槽中的装置，包括：圆形环形部分，其被构造成横向于涡轮机的轴线安装在转子盘的凹槽中; 至少一个锁定楔，其刚性地固定并垂直于所述环形部分，并且平行于所述环形部分的轴线延伸，以将所述刀片的根部径向地保持在所述凹槽中; 以及至少一个从所述环形部分相对于所述环形部分的轴线径向延伸的锁定齿，以防止所述刀片的根部在所述凹槽中轴向移动。

7. 发明授权

US09422820B2 Method and system for self-locking a closure bucket in a rotary machine 有权
标题翻译：用于在旋转机器中自锁锁闭桶的方法和系统
公开(公告)号：US09422820B2
公开(公告)日：2016-08-23
申请号：US13886188
申请日：2013-05-02
申请人： Nuovo Pignone SRL
发明人： Marco Pieri
IPC分类号： F01D5/32 , F01D5/30
CPC分类号： F01D5/326 , F01D5/303 , F01D5/32 , F01D5/323 , Y10T29/4932
摘要： A system includes a turbomachine that includes at least one rotor disk or stage having a peripheral portion disposed about a rotational axis of the rotor disk or stage. The peripheral portion includes a groove that extends circumferentially about the peripheral portion. The groove has a first groove surface and a second surface disposed opposite the first groove surface. The turbomachine also includes a closure bucket disposed adjacent at least one bucket within the groove. The closure bucket has a first surface that interfaces with the first groove surface and a second groove surface disposed opposite the first surface. The closure bucket blocks circumferential movement of the at least one bucket within the groove relative to the rotor disk or stage. The turbomachine further includes a single wedge disposed between and contacting the second surface of the closure bucket and the second groove surface to secure the closure bucket within the groove.
摘要翻译：一种系统包括涡轮机，该涡轮机包括至少一个转子盘或载物台，该转子盘或台具有围绕转子盘或载物台的旋转轴线设置的周边部分。周边部分包括围绕周边部分周向延伸的凹槽。槽具有第一槽表面和与第一槽表面相对设置的第二表面。涡轮机还包括一个与槽内的至少一个铲斗相邻设置的封闭铲斗。封闭桶具有与第一槽表面相接的第一表面和与第一表面相对布置的第二槽表面。闭合斗相对于转子盘或台，阻止槽内的至少一个铲斗的周向运动。涡轮机还包括设置在封闭桶的第二表面之间并接触封闭桶的第二表面和第二槽表面的单个楔以将封闭桶固定在凹槽内。

8. 发明申请

US20160222805A1 TURBINE BLADE AND GAS TURBINE 审中-公开
标题翻译：涡轮叶片和气体涡轮
公开(公告)号：US20160222805A1
公开(公告)日：2016-08-04
申请号：US15026006
申请日：2014-09-04
申请人： Siemens Aktiengesellschaft
发明人： Peter Schroder
IPC分类号： F01D5/30 , F01D5/32
CPC分类号： F01D5/3015 , F01D5/323 , F01D5/326 , F05D2220/32 , F05D2240/30
摘要： A turbine blade with a turbine blade airfoil and a turbine blade base for securing the turbine blade in a turbine shaft groove of a turbine shaft, wherein the turbine blade base includes a retaining device that retains securing device that secures a flat covering element arranged at the top of the turbine blade base. The retaining device is arranged on the outside of the turbine blade base.
摘要翻译：具有涡轮机叶片翼型和涡轮叶片基座的涡轮机叶片，其用于将涡轮机叶片固定在涡轮机轴的涡轮机轴槽中，其中涡轮机叶片基座包括保持装置，其保持固定装置，该固定装置固定布置在涡轮叶片基座顶部。保持装置设置在涡轮叶片基座的外侧。

9. 发明申请

US20160153303A1 SNAP IN PLATFORM DAMPER AND SEAL ASSEMBLY FOR A GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的平台阻尼器和密封组件的SNAP
公开(公告)号：US20160153303A1
公开(公告)日：2016-06-02
申请号：US14339019
申请日：2014-07-23
申请人： United Technologies Corporation
发明人： Matthew A. Hough
IPC分类号： F01D11/00 , B23P15/04 , F01D5/22
CPC分类号： F01D11/006 , F01D5/22 , F01D5/3007 , F01D5/323 , F05D2260/96
摘要： A turbine assembly includes a first turbine blade circumferentially adjacent to a second turbine blade. The first turbine blade includes a first platform with a first underplatform surface. The second turbine blade includes a second platform with a second underplatform surface. The first underplatform surface and the second underplatform surface at least partially defines a cavity. A damper with a platform rub surface is included adjacent the first underplatform surface and the second underplatform surface. A seal is included with a forward portion, an aft portion, and a damper interface portion therebetween. The damper interface portion extends along a damper underside and the forward portion and the aft portion adjacent the first underplatform surface and the second underplatform surface.
摘要翻译：涡轮组件包括与第二涡轮机叶片周向相邻的第一涡轮机叶片。第一涡轮叶片包括具有第一底板平台表面的第一平台。第二涡轮机叶片包括具有第二平台下表面的第二平台。第一底板下表面和第二平台下表面至少部分地限定空腔。具有平台摩擦表面的阻尼器包括在第一底板表面和第二平台下表面附近。密封件包括在其间的前部，后部和阻尼器接口部分。阻尼器接口部分沿着阻尼器下侧延伸，并且前部和后部与第一底板平面和第二平台下表面相邻。

10. 发明申请

US20160097289A1 SLIDER 审中-公开
标题翻译：滑块
公开(公告)号：US20160097289A1
公开(公告)日：2016-04-07
申请号：US14856958
申请日：2015-09-17
申请人： ROLLS-ROYCE PLC
发明人： Christopher BENSON
IPC分类号： F01D5/32
CPC分类号： F01D5/326 , F01D5/30 , F01D5/3007 , F01D5/3092 , F01D5/323
摘要： A slider for chocking a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc. The slider, in use, is slidingly inserted in an axially-extending cavity formed in the base of the root and in the disc at the base of the slot to urge the blade radially outwardly and thereby mate flanks of the root to flanks of the slot. The slider is arc-shaped and the cavity is correspondingly arc-shaped. The normal to the plane of the arc of the arc-shaped cavity is substantially perpendicular to the engine axis such that, when inserted in the cavity, the slider also retains the root axially in the slot.
摘要翻译：一种用于在盘的边缘中的对应的轴向延伸槽中堵塞燃气涡轮发动机的叶片的燕尾根的滑块。使用中的滑块滑动地插入形成在根部的基部中的轴向延伸的空腔中，并且在槽的基部处滑动地推动叶片径向向外，从而将根部的侧面与槽的侧面配合。滑块为弧形，腔体为弧形。弧形腔的弧的平面的法线基本上垂直于发动机轴线，使得当插入空腔时，滑块还将根部轴向保持在狭槽中。

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