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1. 发明申请

US20180080332A1 INTERMEDIATE CASING GUIDE VANE WHEEL 审中-公开
公开(公告)号：US20180080332A1
公开(公告)日：2018-03-22
申请号：US15707428
申请日：2017-09-18
申请人： Safran Aircraft Engines
发明人： Marc-Antoine Anatole GOT , Cédric ZACCARDI
IPC分类号： F01D9/04 , F01D5/28
CPC分类号： F01D9/041 , F01D5/282 , F01D5/3069 , F01D9/042 , F01D25/246 , F05D2220/36 , F05D2240/12 , F05D2260/31 , F05D2300/603 , Y02T50/672
摘要： An OGV wheel comprising guide vanes made of polymer matrix composite material reinforced by fibers, each having a vane root and a vane tip, the vane roots being fastened on a hub of the wheel by first connection means and the vane tip being fastened on an outer shroud of the wheel by second connection means, the first connection means including a bearing plane secured to the hub and a first backing plate for securing to the hub, the vane roots being sandwiched between the bearing plane and the first backing plate, and the second connection means including a second backing plate for securing to the shroud, the vane tip being sandwiched between the shroud and the second backing plate.

2. 发明授权

US09896949B2 Bonded fan platform 有权
公开(公告)号：US09896949B2
公开(公告)日：2018-02-20
申请号：US14862390
申请日：2015-09-23
申请人： United Technologies Corporation
发明人： Thomas J. Robertson
IPC分类号： F01D5/14 , F01D5/30 , F01D5/12 , F04D29/02 , F04D29/32 , F02K3/06 , F01D5/28 , F01D11/00
CPC分类号： F01D5/3069 , F01D5/12 , F01D5/147 , F01D5/282 , F01D5/3053 , F01D11/005 , F01D11/008 , F02K3/06 , F04D29/023 , F04D29/324 , F05D2220/36 , F05D2240/80 , F05D2240/81 , F05D2260/30 , F05D2260/36 , F05D2300/603 , Y02T50/676
摘要： A fan is provided. The fan may comprise a fan blade and a blade platform coupled to the fan blade. The blade platform may be a thermoplastic. A fan blade platform is also provided. The fan blade platform may comprise a first platform half comprising a slot at a first end of the first platform half and a first receiving member at a second end of the first platform half opposite the first end of the first platform half. A second platform half may comprise a hook. The second platform half may also include a second receiving member at a second end of the second platform half opposite the first end of the second platform half with the hook configured to interface with the slot. A pin may be configured to pass through the first receiving member and the second receiving member.

3. 发明申请

US20160376919A1 TRUNNION RETENTION FOR A TURBINE ENGINE 审中-公开
标题翻译：涡轮发动机的保护
公开(公告)号：US20160376919A1
公开(公告)日：2016-12-29
申请号：US14747132
申请日：2015-06-23
申请人： General Electric Company
发明人： Brandon Wayne MILLER , Ian Francis PRENTICE , Daniel Alan NIERGARTH
IPC分类号： F01D21/04 , F01D7/00 , F02C3/04 , F01D5/30 , F01D25/16
CPC分类号： F01D21/045 , B64C11/06 , F01D5/3007 , F01D5/3023 , F01D5/3069 , F01D7/00 , F01D25/162 , F02C3/04 , F04D27/0292 , F04D29/323 , F05D2220/32 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/50 , F05D2240/80 , F05D2260/30 , F05D2260/33 , F05D2260/74 , F05D2260/79 , Y02T50/672 , Y02T50/673
摘要： A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.
摘要翻译：提供了一种用于燃气涡轮发动机的风扇。风扇包括多个风扇叶片，盘和用于将风扇叶片附接到盘的耳轴机构。盘可以由多个单独的盘段形成，其中耳轴机构将多个风扇叶片中的一个附接到相应的盘片段。还提供保持构件。保持构件包括用于在耳轴机构的主附接系统失效时抓住耳轴机构的一部分的装置。

4. 发明申请

US20160102565A1 TIP-CONTROLLED INTEGRALLY BLADED ROTOR FOR GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的TIP控制的整体式叶片转子
公开(公告)号：US20160102565A1
公开(公告)日：2016-04-14
申请号：US14973943
申请日：2015-12-18
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Alexandre Ayers
IPC分类号： F01D7/02 , F01D5/30 , F01D5/22 , F01D5/02
CPC分类号： F01D7/02 , F01D5/02 , F01D5/225 , F01D5/3069 , F01D5/34 , F01D11/16 , F01D11/22 , F05D2220/32 , F05D2240/20 , F05D2300/501
摘要： An integrally bladed rotor for a gas turbine engine includes a hub, a plurality of blades radially extending from the hub and being integrally formed therewith. The hub having a rim from which the blades project and a pair of axially opposed split hub members extending at least radially inward from the rim. Each of the split hub members has a radially outer flex arm portion extending form the hub and a radially inner moment flange portion. At least one moment inducing element separately formed from the hub is mounted axially between the opposed split hub members and acts on the moment flange portions of the opposed split hub members to generate an inward bending moment on the flex arm portions of the opposed split hub members during rotation of the rotor, thereby deflecting the rim and the blades of the rotor radially inwardly.
摘要翻译：用于燃气涡轮发动机的整体叶片转子包括轮毂，从轮毂径向延伸并与其一体形成的多个叶片。所述轮毂具有叶片从其突出的边缘，以及一对轴向相对的分开的轮毂构件，其至少从轮缘径向向内延伸。每个分离轮毂构件具有从轮毂延伸的径向外部柔性臂部分和径向内侧力矩凸缘部分。从轮毂分开形成的至少一个力矩引导元件被轴向地安装在相对的分开的轮毂件之间并且作用在相对的分开轮毂件的力矩凸缘部分上，以在相对的分开轮毂构件的挠性臂部分上产生向内的弯曲力矩在转子旋转期间，从而使转子的轮缘和叶片径向向内偏转。

5. 发明申请

US20150308273A1 SHROUDED SINGLE CRYSTAL DUAL ALLOY TURBINE DISK 审中-公开
公开(公告)号：US20150308273A1
公开(公告)日：2015-10-29
申请号：US14542209
申请日：2014-11-14
申请人： HONEYWELL INTERNATIONAL INC.
发明人： James S. Perron , William C. Baker , Derek A. Rice
IPC分类号： F01D5/02 , B23K20/02 , C25D5/02 , B23K20/24 , B23K31/02 , F01D5/30 , B23K20/00
CPC分类号： F01D5/02 , B23K20/002 , B23K20/02 , B23K20/24 , B23K31/02 , C25D5/02 , F01D5/286 , F01D5/3061 , F01D5/3069 , F01D5/34 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/236 , F05D2230/31 , F05D2230/40 , F05D2230/60 , F05D2230/90 , F05D2260/941 , F05D2260/96 , F05D2300/14 , F05D2300/143 , F05D2300/607 , Y10T29/4932 , Y10T29/49321 , Y10T29/49336
摘要： A turbine engine component for a gas turbine engine includes an inner disk, an outer shroud, and a plurality of blades. Each blade comprises a blade root and an airfoil body. The blade root is plated at least in part with a noble metal, and is coupled to the inner disk. The airfoil body extends at least partially between the blade root and the outer shroud.

6. 发明申请

US20150292332A1 METHOD FOR BUILDING STAGES OF CENTRIFUGAL RADIAL TURBINES 有权
标题翻译：离心式涡轮机建筑阶段的方法
公开(公告)号：US20150292332A1
公开(公告)日：2015-10-15
申请号：US14437573
申请日：2013-10-10
申请人： EXERGY S.P.A.
发明人： Claudio Spadacini , Marco Rizzi
IPC分类号： F01D5/04 , F01D5/30
CPC分类号： F01D5/041 , F01D5/3061 , F01D5/3069 , F05D2230/234 , F05D2230/642
摘要： The present invention relates to a method for building centrifugal radial stages of turbines, in which the first and the second end of each blade (4) are connected to respective two support rings (2, 3) joining, by means of laser welding, at least a first semi-portion (10) belonging to the respective end of the blade (4) to a respective second semi-portion (10) belonging to the respective support ring (2, 3) so as to form a resilient yielding connecting portion (10, 15) along a radial direction, and providing at least a stop portion (11) belonging to the end of the blade (4) facing, along the radial direction, at least a stop element (14) of the respective support ring (2, 3). The resilient yielding connecting portion (10, 15) enables the strop portion (11) to enter into contact with the stop element (14) when the stage (1) is subjected to the functioning loads of the turbine.
摘要翻译：本发明涉及一种用于建造涡轮机的离心径向级的方法，其中每个叶片（4）的第一和第二端连接到相应的两个支撑环（2,3），所述两个支撑环通过激光焊接在至少一个属于所述叶片（4）的相应端部的第一半部分（10）到属于相应的支撑环（2,3）的相应的第二半部分（10），以便形成弹性屈服连接部分（10,15），并且至少提供属于所述叶片（4）的端部的至少一个止动部分（11），所述止动部分沿着所述径向方向面向所述相应支撑环的至少一个止动元件（14）（2,3）。当舞台（1）承受涡轮机的功能负载时，弹性屈服连接部分（10,15）使得脚蹬部分（11）能够与止动元件（14）接触。

7. 发明申请

US20150110633A1 RETENTION ASSEMBLY WITH A CONICAL INTERFACE FOR A PROPELLER BLADE 审中-公开
标题翻译：具有用于螺旋桨叶片的界面的保持装置
公开(公告)号：US20150110633A1
公开(公告)日：2015-04-23
申请号：US14057189
申请日：2013-10-18
申请人： Hamilton Sundstrand Corporation
发明人： David P. Nagle , Paul A. Carvalho
IPC分类号： F01D5/30 , F01D5/14
CPC分类号： F01D5/3069 , B64C11/06 , B64C11/26 , F01D5/147
摘要： A retention assembly for a propeller blade includes an inner ring that is conformally shaped to a bore of an annular loop, the annular loop being associated with a root portion of the propeller blade; a base that is configured to be immediately adjacent the annular loop; an annular outer ring including a bearing race interface that is conical in shape and includes a radially inner surface that conforms to a radially outer surface of the annular loop; and an adhesive that adhesively connects complementary surfaces of the outer ring and the annular loop. Also, a propeller blade assembly includes a propeller blade having a blade portion and a root portion; and the retention assembly that is configured to attach to the propeller blade.
摘要翻译：用于螺旋桨叶片的保持组件包括内环，该内环与环形环的孔共形地成形，该环与螺旋桨叶的根部相关联; 被配置成紧邻环形环的基座; 环形外环，其包括圆锥形的轴承座圈接口，并且包括符合环形环的径向外表面的径向内表面; 以及粘合剂连接外环和环形环的互补表面的粘合剂。此外，螺旋桨叶片组件包括具有叶片部分和根部部分的螺旋桨叶片; 以及构造成附接到螺旋桨叶片的保持组件。

8. 发明申请

US20100239424A1 SPLIT DISK ASSEMBLY FOR A GAS TURBINE ENGINE 有权
标题翻译：用于燃气涡轮发动机的分体盘组件
公开(公告)号：US20100239424A1
公开(公告)日：2010-09-23
申请号：US12405272
申请日：2009-03-17
申请人： Fadi S. Maalouf , Eric W. Malmborg , Matthew E. Bintz
发明人： Fadi S. Maalouf , Eric W. Malmborg , Matthew E. Bintz
IPC分类号： F01D5/30
CPC分类号： F01D5/3038 , F01D5/3069
摘要： A split disk assembly for a gas turbine engine includes a forward disk section and an aft disk section, the aft disk section engageable with the forward disk section to retain a multitude of rotor blades therebetween.
摘要翻译：用于燃气涡轮发动机的分裂盘组件包括前盘部分和后盘部分，后盘部分可与前盘部分接合以在其间保持多个转子叶片。

9. 发明申请

US20030002987A1 Compressor rotor blade spacer apparatus 有权
标题翻译：压缩机转子叶片间隔装置
公开(公告)号：US20030002987A1
公开(公告)日：2003-01-02
申请号：US09891513
申请日：2001-06-27
发明人： Dwight Eric Davidson
IPC分类号： F01D005/32
CPC分类号： F01D5/323 , F01D5/30 , F01D5/3069 , F01D11/005 , F05D2230/24 , F05D2230/64 , F05D2260/30
摘要： An integral compressor rotor spacer cartridge fits within the dovetail region of the rim of a compressor rotor wheel to retain the dovetail portion of the rotor blade maintain an angular spaced relationship between the rotor blades. The dovetail portion of the rotor blade is retained in a pocket or notched portion of the spacer cartridge.
摘要翻译：整体式压缩机转子间隔器套筒配合在压缩机转子轮的边缘的燕尾区域内，以保持转子叶片的燕尾部分保持转子叶片之间的角度间隔的关系。转子叶片的燕尾部分保持在间隔盒的口袋或凹口部分中。

10. 发明授权

US5431541A Ceramic blade attachment system 失效
标题翻译：陶瓷刀片附件系统
公开(公告)号：US5431541A
公开(公告)日：1995-07-11
申请号：US159094
申请日：1993-11-29
申请人： James E. Shaffer
发明人： James E. Shaffer
IPC分类号： F01D5/30
CPC分类号： F01D5/3069
摘要： A turbine blade having a preestablished rate of thermal expansion is attached to a turbine disc having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine blade and forms a turbine assembly. The turbine blade has a root portion defining a pair of sides having a pair of grooves therein. The turbine assembly includes a pair of flanges between which the turbine blades are positioned. Each of the pair of flanges has a plurality of grooves defined therein. The grooves within the pair of flanges are aligned with the grooves in the blades and have a space formed therebetween. A plurality of spherical balls are positioned within the space. The plurality of spherical balls has a preestablished rate of thermal expansion being equal to the preestablished rate of thermal expansion of the turbine blade.
摘要翻译：具有预先建立的热膨胀速率的涡轮机叶片被附接到具有预先建立的热膨胀率大于涡轮叶片的预先建立的热膨胀速率并形成涡轮机组件的涡轮盘。涡轮机叶片具有限定一对侧面的根部，在其中具有一对凹槽。涡轮组件包括一对凸缘，涡轮叶片在其之间定位。一对凸缘中的每一个具有限定在其中的多个凹槽。一对凸缘内的凹槽与叶片中的槽对准，并且在其间形成一个空间。多个球形球定位在该空间内。多个球形球具有预先设定的热膨胀率等于涡轮叶片的预先设定的热膨胀速率。

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