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1. 发明授权

EP3093439B1 DAMPER SYSTEM FOR A TURBINE 有权
公开(公告)号：EP3093439B1
公开(公告)日：2024-06-26
申请号：EP16168466.7
申请日：2016-05-05
IPC分类号： F01D5/22
CPC分类号： F05D2250/18220130101 , F05D2250/29420130101 , F05D2240/3020130101 , F01D5/22

2. 发明授权

EP2836682B1 TURBINE BLADE DAMPER SEAL 有权转让
公开(公告)号：EP2836682B1
公开(公告)日：2018-11-14
申请号：EP13775907.2
申请日：2013-01-25
申请人： United Technologies Corporation
发明人： SNYDER, Daniel A. , LANA, Kyle, Charles , SANDOVAL, Jonathan, Perry , VIRKLER, Scott, Daniel , TARASKEVICH, Jaimie , OTERO, Edwin
IPC分类号： F01D5/26 , F01D5/22 , F01D5/30 , F01D11/00
CPC分类号： F01D5/22 , F01D5/3007 , F01D11/006 , Y02T50/673
摘要： A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

3. 发明授权

EP2831376B1 TURBINENSCHAUFEL 有权转让
公开(公告)号：EP2831376B1
公开(公告)日：2018-10-24
申请号：EP13712793.2
申请日：2013-03-27
申请人： Ansaldo Energia IP UK Limited
发明人： BRANDL, Herbert
IPC分类号： F01D5/22 , F01D5/30 , F01D5/32 , F01D11/00 , F01D5/14
CPC分类号： F01D5/22 , F01D5/147 , F01D5/3007 , F01D5/326 , F01D11/008 , F05B2240/57 , F05D2230/50 , F05D2230/51 , F05D2240/55 , F05D2240/57 , F05D2240/80 , F05D2260/30 , F05D2260/31 , F05D2260/36 , F05D2260/96

4. 发明授权

EP1867837B1 Bucket vibration damper system 有权
公开(公告)号：EP1867837B1
公开(公告)日：2018-08-08
申请号：EP07110118.2
申请日：2007-06-12
申请人： GENERAL ELECTRIC COMPANY
发明人： LAGRANGE, Benjamin Arnette , GOOD, Randall Richard , LIOTTA, Gary Charles , DELONG, Jon Robert , COLLIER, Matthew Durham , VEHR, James William , CHIURATO, Anthony Aaron
IPC分类号： F01D5/22
CPC分类号： F01D5/22 , F05D2240/80 , F05D2250/70 , Y10S416/50
摘要： A damping system (100) for a turbine bucket (105). The damping system (100) includes a damper pocket (200) with a variable tangential depth and a damper pin (230) positioned within the damper pocket (200).

5. 发明公开

EP3330489A1 TURBINE WHEELS, TURBINE ENGINES INCLUDING THE SAME, AND METHODS OF FORMING TURBINE WHEELS WITH IMPROVED SEAL PLATE SEALING 审中-实审
公开(公告)号：EP3330489A1
公开(公告)日：2018-06-06
申请号：EP17202660.1
申请日：2017-11-21
申请人： Honeywell International Inc.
发明人： HALFMANN, Steve , CRITES, Daniel C. , KAHRS, Michael , RIAHI, Ardeshir , MILLER, Jude
IPC分类号： F01D5/30
CPC分类号： F01D11/006 , F01D5/081 , F01D5/12 , F01D5/22 , F01D5/3015 , F01D5/3023 , F05D2230/23 , F05D2300/50212
摘要： Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.

6. 发明公开

EP2500520A3 Damper and seal pin arrangement for a turbine blade 有权转让
标题翻译：涡轮叶片的阻尼器和密封销布置
公开(公告)号：EP2500520A3
公开(公告)日：2017-12-27
申请号：EP12158501.2
申请日：2012-03-07
申请人： General Electric Company
发明人： Boyer, Bradley , Collier, Matthew D.
IPC分类号： F01D5/22 , F01D5/26 , F01D11/00
CPC分类号： F01D5/22 , F01D5/26 , F01D11/006 , Y02T50/673 , Y10S416/50
摘要： A bucket (56) for a turbomachine rotor wheel includes an airfoil portion, a shank portion (62) and a dovetail mounting portion, the shank portion (62) including opposite sides (58,60), one of the sides (58) formed with a substantially axially-oriented groove (64) extending between forward and aft ends of the shank portion. The other one of the opposite sides (60) is formed with at least one substantially radially-oriented groove (70). The substantially axially-oriented groove (64) is adapted to receive an elongated damper pin, and the at least one substantially radially-oriented groove (70) is adapted to receive an elongated radial seal pin.
摘要翻译：一种用于涡轮机转子叶轮的桶（56）包括翼型部分，柄部分（62）和燕尾榫安装部分，柄部分（62）包括相对的侧面（58,60），其中一个侧面（58）形成具有在柄部分的前端和后端之间延伸的基本上轴向取向的凹槽（64）。另一个相对侧（60）形成有至少一个基本上径向取向的凹槽（70）。基本上轴向取向的凹槽（64）适于接收细长的阻尼销，并且所述至少一个基本上径向取向的凹槽（70）适于接收细长的径向密封销。

7. 发明公开

EP2570600A3 Turbine rotor blade assembly and method of assembling same 有权
标题翻译：涡轮转子叶片组件及其组装方法
公开(公告)号：EP2570600A3
公开(公告)日：2017-11-15
申请号：EP12182828.9
申请日：2012-09-03
申请人： General Electric Company
发明人： Paige II, Anthony Reid , Verrilli, Michael James , Jamison, Joshua Brian , Noe, Mark Eugene , Izon, Paul , Marusko, Mark Willard
IPC分类号： F01D5/26 , F01D5/28 , F01D5/30 , F01D11/08 , F01D5/22 , F01D11/00
CPC分类号： F01D5/284 , F01D5/22 , F01D5/3007 , F01D11/006 , F01D11/08 , F05D2300/6033 , Y02T50/672 , Y10T29/49321
摘要： A rotor blade assembly (100) for a rotor (30) of a gas turbine engine (10) having an axis of rotation (8) includes a shank portion (106) formed from a ceramic matrix composite (CMC) material. The rotor blade assembly also includes a platform portion (104) formed from a substantially similar CMC material as that of the shank portion. The platform portion is coupled to the shank portion. The platform portion and the shank portion cooperate to at least partially define two opposing side portions (128) of the rotor blade assembly. The opposing side portions are angularly separated with respect to the axis of rotation. The rotor blade assembly further includes a damper retention apparatus (120). At least a portion of the damper retention apparatus is coupled to the shank portion. The damper retention apparatus includes at least one angled bracket apparatus (120) extending toward a circumferentially adjacent rotor blade assembly (100).
摘要翻译：一种用于具有旋转轴线（8）的燃气涡轮发动机（10）的转子（30）的转子叶片组件（100）包括由陶瓷基质复合材料（CMC）材料形成的柄部分（106）。转子叶片组件还包括平台部分（104），该平台部分（104）由与杆部分基本相似的CMC材料形成。平台部分连接到柄部分。平台部分和柄部配合以至少部分地限定转子叶片组件的两个相对的侧部（128）。相对的侧面部分相对于旋转轴线成角度地分开。转子叶片组件还包括阻尼器保持装置（120）。阻尼器保持装置的至少一部分联接到柄部分。阻尼器保持装置包括朝向周向相邻的转子叶片组件（100）延伸的至少一个成角度的支架装置（120）。

8. 发明公开

EP3170974A1 TURBINE BLADE WITH AIRFOIL TIP VORTEX CONTROL 有权转让
标题翻译：涡轮叶片与翼型尖头涡旋控制
公开(公告)号：EP3170974A1
公开(公告)日：2017-05-24
申请号：EP16200356.0
申请日：2016-11-23
申请人： United Technologies Corporation
发明人： LEWIS, Scott D. , LANA, Kyle C. , LILES, Jason David
IPC分类号： F01D5/14 , F01D5/20
CPC分类号： F01D5/145 , F01D5/141 , F01D5/20 , F01D5/22 , F02C3/04 , F05D2220/32 , F05D2240/303 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2240/307 , F05D2250/711 , Y02T50/671 , Y02T50/673
摘要： A rotor blade (32) for a gas turbine engine (10) is provided. The rotor blade having: an attachment (34); an airfoil (36) extending from the attachment to a tip (46); and a squealer pocket (200) located in a surface of the tip, wherein the squealer pocket is at least partially surrounded by a first surface (206) of a wall (202) located between the squealer pocket and a pressure side of the airfoil, wherein the first surface of the wall has a convex configuration with respect to the pressure side of the airfoil as it extends from a leading edge (38) to a trailing edge (40) of the airfoil.
摘要翻译：提供了一种用于燃气涡轮发动机（10）的转子叶片（32）。该转子叶片具有：附件（34）; 从所述附件延伸到尖端（46）的翼型件（36）; 以及位于所述尖端的表面中的鸣声器袋（200），其中所述鸣声器袋至少部分地由位于所述鸣音器袋与所述翼型件的压力侧之间的壁（202）的第一表面（206）围绕，其中当所述壁从所述翼型的前缘（38）延伸到后缘（40）时，所述壁的所述第一表面相对于所述翼型的所述压力侧具有凸起构型。

9. 发明授权

EP2884050B1 Schaufelgitter und zugehöriges Verfahren 有权
标题翻译： Schaufelgitter undzugehörigesVerfahren
公开(公告)号：EP2884050B1
公开(公告)日：2017-03-15
申请号：EP14178015.5
申请日：2014-07-22
申请人： MTU Aero Engines AG
发明人： Hartung, Andreas , Stiehler, Frank , Pernleitner, Martin
IPC分类号： F01D5/22 , F01D5/26 , F01D5/28 , F04D29/02 , F04D29/32 , F04D29/54 , F04D29/66
CPC分类号： F01D5/28 , F01D5/14 , F01D5/22 , F01D5/26 , F04D29/023 , F04D29/324 , F04D29/542 , F04D29/666 , F05D2260/961 , F05D2300/607 , Y02T50/671 , Y10T29/49321

10. 发明公开

EP3139001A1 DAMPER PIN FOR TURBINE BLADES AND CORRESPONDING TURBINE ENGINE 有权转让
标题翻译：用于涡轮叶片和相应的涡轮发动机的阻尼销
公开(公告)号：EP3139001A1
公开(公告)日：2017-03-08
申请号：EP16185251.2
申请日：2016-08-23
申请人： General Electric Company
发明人： KAREFF, Spencer A. , POTTER, Brian Denver , PREPENA JACALA, Ariel Caesar
IPC分类号： F01D5/22
CPC分类号： F01D5/22 , F05D2220/32 , F05D2250/141 , Y02T50/672
摘要： A damper pin 100 for damping adjacent turbine blades 28 coupled to a rotor shaft 22 includes a first end portion 102 that is axially aligned with and axially spaced from a second end portion 104 and a retention pin 116 that is coaxially aligned with and disposed between the first end portion 102 and the second end portion 104. The retention pin 116 couples the first end portion 102 to the second end portion 104. The damper pin 100 further includes a plurality of rings 122 coaxially aligned with and disposed along the retention pin 116 between the first end portion 102 and the second end portion 104. The first end portion 102, the second end portion 104 and the plurality of rings 122 define a generally arcuate outer surface 124 of the damper pin (100) that is configured to contact with a groove defined between the adjacent turbine blades 28.
摘要翻译：用于阻尼连接到转子轴22的相邻涡轮机叶片28的阻尼销100包括第一端部部分102，其与第二端部部分104轴向对齐并且与第二端部部分104和保持销116轴向间隔开，第一端部部分102与第二端部部分104同轴对准并设置在第一端部部分102和第二端部部分104.保持销116将第一端部部分102连接到第二端部部分104.阻尼销100还包括多个环122，其与保持销116同轴对齐并沿着保持销116设置第一端部部分102和第二端部部分104.第一端部部分102，第二端部部分104和多个环122限定了阻尼销（100）的大体上弓形的外表面124，其被构造成与限定在相邻涡轮叶片28之间的凹槽。

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