公开(公告)号：US08066489B2

公开(公告)日：2011-11-29

申请号：US12010064

申请日：2008-01-18

申请人： Martin D. Holmes

发明人： Martin D. Holmes

IPC分类号： F01D5/32

CPC分类号： F01D5/26 ,  F01D5/22 ,  F01D5/3007 ,  F01D11/006 ,  F05D2230/60 ,  F05D2250/12 ,  F05D2250/181 ,  F05D2250/30 ,  F05D2250/70 ,  F05D2260/30 ,  Y10S416/50 ,  Y10T29/49316 ,  Y10T29/49321

摘要： An aerofoil assembly includes a plurality of rotatable blades. A damping member is disposed between at least two of the blades, each of the at least two blades having an aerofoil portion, a stem portion and a root portion. A recess is provided on two cooperating stem portions with a first shelf extending from a first end of each recess, and a second shelf extending from a second end of each recess to define a compartment. When the blades are aligned the damping member is held on one side of the shelves within the compartment. The damping member is provided with a projection at one corner and a projection on a diagonally opposite corner, the longitudinal distance between ends of the projections being greater than the distance between edges of the first and second shelf.

摘要翻译： 机翼组件包括多个可旋转叶片。 阻尼构件设置在至少两个叶片之间，所述至少两个叶片中的每一个具有机翼部分，杆部分和根部分。 在两个配合的杆部分上设有凹槽，其中第一搁板从每个凹部的第一端延伸，以及从每个凹部的第二端延伸以限定隔室的第二搁架。 当叶片对准时，阻尼构件被保持在隔室内的搁板的一侧。 阻尼构件在一个角部设置有突起，在对角相对的角上设置有突起，突起的端部之间的纵向距离大于第一和第二搁架的边缘之间的距离。

公开(公告)号：US20110014050A1

公开(公告)日：2011-01-20

申请号：US12739283

申请日：2008-09-16

申请人： Peter Lake ,  Rene James Webb

发明人： Peter Lake ,  Rene James Webb

IPC分类号： F01D5/32 ,  F01D11/00

CPC分类号： F16J15/0887 ,  F01D11/006 ,  F05D2250/70

摘要： A turbine blade assembly, in particular for a gas turbine, is provided. The turbine blade assembly includes a disc with a rotation axis, turbine blades, each turbine blade including an airfoil, a blade root and a platform between the airfoil and the blade root by which it may be fixed to the disc, locking plates and bent seal strips. The turbine blades are arranged adjacent to each other on the disc, such that gaps are present between the platforms of adjacent turbine blades and root cavities are present between the portions of the roots of adjacent turbine blades. The turbine blades are secured axially to the disc by the locking plates. The seal strips are arranged in the gaps between the platforms of neighbouring turbine blades to seal the gap and protrude axially over the blade root and over the locking plate.

摘要翻译： 提供了一种涡轮叶片组件，特别是用于燃气轮机。 涡轮叶片组件包括具有旋转轴线的圆盘，涡轮机叶片，每个涡轮叶片包括翼型件，叶片根部和在翼型件和叶片根部之间的平台，通过该平台可将其固定到盘，锁定板和弯曲密封 带子。 涡轮机叶片在盘上彼此相邻设置，使得在相邻涡轮机叶片的平台之间存在间隙，并且根空腔存在于相邻涡轮叶片的根部的部分之间。 涡轮机叶片通过锁定板轴向固定在盘上。 密封条布置在相邻涡轮机叶片的平台之间的间隙中以密封间隙并且轴向地突出在叶片根部上方并在锁定板上方。

公开(公告)号：US20110002787A1

公开(公告)日：2011-01-06

申请号：US12644101

申请日：2009-12-22

申请人： Enrique Penalver Castro ,  Yves Culot

发明人： Enrique Penalver Castro ,  Yves Culot

IPC分类号： F01D5/32 ,  B23P11/00

CPC分类号： F01D9/042 ,  F01D21/045 ,  F01D25/246

摘要： A rectifier stage of an axial turbine engine compressor is placed directly downstream of the input blower of a turbo-reactor or turboshaft engine compressor. The blade roots of the rectifier stage are housed inside the inner shroud by insertion into respective slots. The blade roots include at least one opening protruding from the slot of the shroud, so as to receive a spiral ring having at least two loops so as to prevent the blade roots from escaping from the respective slots of the inner shroud, and so as to form a connection between the blade roots. A method for retaining blades of a rectifier stage of an axial turbine engine compressor on an inner shroud, in particular a rectifier stage placed directly downstream of the input blower of a turbo-reactor or turboshaft engine compressor, includes positioning a spiral ring having at least two loops inside the openings of the blade roots by threading one end of the ring successively into the openings until all of the spirals of the ring are housed inside the openings.

摘要翻译： 轴流涡轮发动机压缩机的整流器级直接放置在涡轮反应器或涡轮轴发动机压缩机的输入鼓风机的下游。 整流台的叶片根部通过插入相应的槽而容纳在内罩内。 叶片根部包括从护罩的狭槽突出的至少一个开口，以便容纳具有至少两个环的螺旋环，以防止叶片根部从内护罩的相应狭槽逸出，从而 形成叶片根部之间的连接。 用于将轴向涡轮发动机压缩机的整流器级的叶片保持在内护罩上，特别是放置在涡轮反应器或涡轮轴发动机压缩机的输入鼓风机的下游的整流器级的方法包括定位至少具有至少 通过将环的一端连续地插入到开口中，直到所有环的螺旋被容纳在开口内，在叶片根部的开口内的两个环。

公开(公告)号：US20100329873A1

公开(公告)日：2010-12-30

申请号：US12491276

申请日：2009-06-25

申请人： Daniel Ruba ,  Matthew Scott ,  Thomas Bowman

发明人： Daniel Ruba ,  Matthew Scott ,  Thomas Bowman

IPC分类号： F01D5/32 ,  B23P15/04

CPC分类号： F01D5/3015 ,  Y10T29/49321

摘要： A fan blade retaining and sealing ring assembly for an aft side of a bladed disk assembly is disclosed herein. The ring assembly includes an inner ring operable to prevent aft movement of a fan blade positioned in a slot formed in the blade disk. The ring assembly also includes an outer ring operable to seal against a platform of the fan blade. The inner ring and the outer ring are formed from different materials.

摘要翻译： 本文公开了一种用于叶片盘组件的后侧的风扇叶片保持和密封环组件。 环组件包括可操作以防止位于形成在叶片盘中的槽中的风扇叶片的后运动的内环。 环组件还包括可操作以密封风扇叶片的平台的外环。 内环和外环由不同的材料形成。

公开(公告)号：US20100284814A1

公开(公告)日：2010-11-11

申请号：US12007509

申请日：2008-01-10

申请人： Stephen R. Prince ,  Thomas R. Tipton ,  Michael E. Friedman ,  Mark Newton ,  Dale R. Lombardo

发明人： Stephen R. Prince ,  Thomas R. Tipton ,  Michael E. Friedman ,  Mark Newton ,  Dale R. Lombardo

IPC分类号： F01D5/32

CPC分类号： F01D5/323

摘要： An axial retention system for restraining axial movement of a first machine component having a dovetail within a complimentary-shaped dovetail slot in a second machine component that includes a first curved groove formed in a bottom surface of the dovetail slot and a second curved groove formed in a bottom surface of the dovetail. The first and second grooves are in alignment when the dovetail is located within the dovetail slot to thereby form a closed periphery aperture. A curved locking clip is received within the closed periphery aperture. An optional cover plate may be placed over the ends of the locking clip, with ends of the locking clip deformed by, for example, swaging.

摘要翻译： 一种轴向保持系统，用于在第二机器部件中限制具有燕尾形的第一机器部件在互补形状的燕尾槽内的轴向运动，所述第二机器部件包括形成在所述燕尾槽的底表面中的第一弯曲槽和形成在所述第二弯曲槽中的第二弯曲槽 燕尾榫的底面。 当燕尾座位于燕尾槽内时，第一和第二槽对准，从而形成封闭的外围孔。 弯曲的锁定夹被接收在封闭的外围孔内。 可选的盖板可以放置在锁定夹的端部之上，锁定夹的端部通过例如模锻而变形。

公开(公告)号：US20100047073A1

公开(公告)日：2010-02-25

申请号：US12312048

申请日：2007-08-31

申请人： Richard Bluck ,  Scott Charlton

发明人： Richard Bluck ,  Scott Charlton

IPC分类号： F01D5/32

CPC分类号： F01D5/3015 ,  F05D2250/182 ,  F05D2250/70 ,  F05D2260/30

摘要： A turbine blade assembly, in particular of a gas turbine, is provided. The turbine blade assembly includes a turbine disc with rotor blades inserted into notches of the turbine disc and locking plates that are placed inside circular grooves with rims in the turbine disc and in the rotor blade. The edges of the locking plates that are oriented towards the center of the turbine disc are castellated by providing teeth and accordingly a part of the rim of the circular groove of the turbine disc is also castellated by providing gaps and whereby the gaps of the rim match the teeth of the locking plates. The locking plates have a spring-back force to provide both locking and sealing capabilities during engine operation.

摘要翻译： 提供了一种涡轮叶片组件，特别是一种燃气轮机。 涡轮机叶片组件包括涡轮盘，其具有插入到涡轮盘的凹口中的转子叶片和锁定板，所述锁定板放置在具有轮缘在涡轮盘和转子叶片中的圆形槽内。 通过提供齿，锁定板的朝向涡轮盘的中心的边缘被铸造，因此，涡轮盘的圆形槽的边缘的一部分也通过提供间隙而被浇注，由此轮缘的间隙匹配 锁板的齿。 锁定板具有回弹力，以在发动机操作期间提供锁定和密封能力。

公开(公告)号：US20090252610A1

公开(公告)日：2009-10-08

申请号：US12078757

申请日：2008-04-04

申请人： Stephen P. Wassynger ,  Nick Martin ,  Steven E. Tomberg

发明人： Stephen P. Wassynger ,  Nick Martin ,  Steven E. Tomberg

IPC分类号： F01D5/32

CPC分类号： F01D9/042

摘要： A retention system retains a turbine blade dovetail in a retention ring dovetail slot. The retention system includes a retention opening formed in the blade dovetail. A through hole is formed in the retention ring, wherein the through hole is positioned such that it is aligned with the retention opening when the dovetail is assembled in the dovetail slot. A connector is disposed in the through hole and engages the retention opening. In this manner, undesirable relative movement of parts can be reduced or eliminated, thereby preventing excessive wear.

摘要翻译： 保持系统将涡轮叶片燕尾榫保持在保持环燕尾槽中。 保持系统包括形成在叶片燕尾榫中的保持开口。 在保持环中形成通孔，其中通孔定位成使得当燕尾形成在燕尾槽中时，该通孔与保持开口对准。 连接器设置在通孔中并与保持开口接合。 以这种方式，可以减少或消除部件的不期望的相对运动，从而防止过度磨损。

公开(公告)号：US07517195B2

公开(公告)日：2009-04-14

申请号：US11380049

申请日：2006-04-25

申请人： David Alan Caruso ,  John Cleland Lavash

发明人： David Alan Caruso ,  John Cleland Lavash

IPC分类号： F01D5/32

CPC分类号： F01D5/3046 ,  F01D5/3053 ,  F05D2220/31 ,  F05D2230/60 ,  F05D2260/30

摘要： A closure bucket group for mounting on a dovetail of a turbine wheel. The closure bucket group may include a leading bucket with a leading bucket rear side, a closure bucket with a closure bucket front side and a closure bucket rear side, and a trailing bucket with a trailing bucket front side. The leading bucket rear side and the closure bucket front side define a first enclosed keyway and the closure bucket rear side and the trailing bucket front side define a second enclosed keyway. A number of keys may be positioned within the first enclosed keyway and the second enclosed keyway so as to support the closure bucket.

摘要翻译： 一种用于安装在涡轮机叶轮的燕尾的封闭桶组。 封闭桶组可以包括具有前铲斗后侧的前斗，具有封闭铲斗前侧的封闭铲斗和封闭铲斗后侧，以及具有后铲斗前侧的后铲斗。 前排斗后侧和封闭桶前侧限定第一封闭键槽，封闭桶后侧和后铲斗前侧限定第二封闭键槽。 多个键可以定位在第一封闭键槽和第二封闭键槽内，以便支撑封闭桶。

公开(公告)号：US07500832B2

公开(公告)日：2009-03-10

申请号：US11481722

申请日：2006-07-06

申请人： Thomas W. Zagar ,  Rafael A. De Cardenas

发明人： Thomas W. Zagar ,  Rafael A. De Cardenas

IPC分类号： F01D5/32

CPC分类号： F01D5/3015

摘要： A seal plate system (24) for a rotor in a turbine engine. The rotor includes a rotor disc (10) for supporting a plurality of blades (16), and an annular groove (32) provided in the disc (10) adjacent at least one end (30) of the disc (10). A plurality of plate structures (60) are provided supported between the annular groove (32) of the disc (10) and a groove (56) formed in a platform (26) of the blade (16) adjacent an end (30) of the disc (10). The plate structure (60) includes a plate (64) and an elongated resilient locking pointer (66) extending from the plate (64) for engaging in a lock notch (98) formed in an outer wall (38) of the annular groove (32). The locking pointer (66) forms a self-locking feature that is biased into the lock notch (98) as the plate structure (60) is moved into position on the disc (10).

摘要翻译： 一种用于涡轮发动机中的转子的密封板系统（24）。 转子包括用于支撑多个叶片（16）的转子盘（10）和与盘（10）的至少一个端部（30）相邻设置在盘（10）中的环形槽（32）。 多个板结构（60）被设置为支撑在盘（10）的环形槽（32）和形成在叶片（16）的平台（26）中的槽（56）相邻的端部（30）之间的凹槽（56） 盘（10）。 板结构（60）包括板（64）和从板（64）延伸的细长弹性锁定指针（66），用于接合形成在环形槽的外壁（38）中的锁定凹口（98） 32）。 锁定指针（66）形成当板结构（60）移动到盘（10）上的位置时被偏压到锁定凹口（98）中的自锁特征。

公开(公告)号：US07309215B2

公开(公告)日：2007-12-18

申请号：US11443475

申请日：2006-05-31

申请人： Joana Negulescu

发明人： Joana Negulescu

IPC分类号： F01D5/32

CPC分类号： F01D5/326 ,  F05D2250/241

摘要： A turbine blade locking device for axial retention of a turbine blade (1) having a blade root (3) inserted in an axially extending profiled lobe slot (5) of a turbine disk (4), wherein, a sealing fin of a blade platform (10) includes, over part of its axial length, a retaining groove (6) featuring a semicircular cross-section, a disk lobe (7) of the turbine disk (4) is provided with a semi-spherical recess (8), and a ball (2) is fitted into the recess (8) and the retaining groove (6).

摘要翻译： 一种用于轴向保持涡轮叶片（1）的涡轮机叶片锁定装置，其具有插入在涡轮盘（4）的轴向延伸的异形叶片槽（5）中的叶片根部（3），其中，叶片平台的密封翅片 （10）在其轴向长度的一部分上包括具有半圆形横截面的保持槽（6），所述涡轮盘（4）的盘形叶片（7）设置有半球形凹部（8）， 并且将球（2）装配到凹部（8）和保持槽（6）中。