公开(公告)号：EP4006305A2

公开(公告)日：2022-06-01

申请号：EP21203837.6

申请日：2021-10-21

申请人： Solar Turbines Incorporated

发明人： Duong, Loc Quang ,  Lamicq, Oliver

IPC分类号： F01D5/26 ,  F01D5/24 ,  F01D25/06 ,  F01D5/22

摘要： During operation, a bladed rotor disk typically experiences out-of-plane vibration which can result in deterioration and/or cracking at the interface between adjacent shrouds of the turbine blades. In an embodiment, slots are formed at the end of a labyrinth seal segment of each shroud. Preloaded spring strips are inserted through the slots to couple adjacent shrouds while preventing the natural frequency of the turbine blades from drifting to the operating speed range and/or providing vibration damping to the untuned blade mode.

公开(公告)号：EP3179032A1

公开(公告)日：2017-06-14

申请号：EP16200716.5

申请日：2016-11-25

申请人： General Electric Company

发明人： WILLETT, Fred Thomas ,  ROUSH, Eric David

IPC分类号： F01D5/08 ,  F01D5/24 ,  F01D5/30 ,  F01D11/00

CPC分类号： F01D5/082 ,  F01D5/081 ,  F01D5/147 ,  F01D5/24 ,  F01D5/3015 ,  F01D11/003 ,  F01D11/006 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2240/81 ,  F05D2260/20 ,  Y02T50/676

摘要： A turbomachine blade may include an airfoil (122) and a shank (124) coupled to the airfoil. The shank may include a cover plate (132) having a first circumferential face and a second, opposing circumferential face. A radial cooling groove (250) is positioned in the first circumferential face and is configured to allow a cooling fluid to pass from a first radial position to a second, different radial position relative to the platform. The radial cooling groove (250) provides cover plate and shank cooling. In addition, the radial cooling groove may deliver fluid for purging gaps between blade platforms and cover plates, which prevents the ingestion of hot gas from the turbine flowpath.

摘要翻译： 涡轮机叶片可以包括翼型件（122）和联接到翼型件的杆（124）。 柄可以包括具有第一圆周面和第二相对圆周面的盖板（132）。 径向冷却凹槽（250）位于第一圆周面中，并构造成允许冷却流体相对于平台从第一径向位置传递到第二不同径向位置。 径向冷却槽（250）提供盖板和柄冷却。 另外，径向冷却槽可以输送流体以清除叶片平台和盖板之间的间隙，这防止了从涡轮流道摄入热气。

公开(公告)号：EP2436878A3

公开(公告)日：2016-06-22

申请号：EP11180377.1

申请日：2011-09-07

申请人： Siemens Aktiengesellschaft

发明人： Scheunert, Norbert

IPC分类号： F01D5/00 ,  F01D5/24

CPC分类号： F01D5/22 ,  F01D5/24 ,  F05D2230/64 ,  F05D2250/232 ,  F05D2260/30 ,  F05D2300/603

摘要： Die Erfindung betrifft einen Koppelbolzen (1) zum Koppeln von zwei oder mehreren Turbinenschaufeln (2), wobei die Koppelbolzen (1) zumindest teilweise aus Faserverbundwerkstoff bestehen. Durch die zumindest teilweise Ausbildung aus Faserverbundwerkstoff kann das Gewicht der Koppelbolzen (1) gegenüber im Stand der Technik deutlich herabgesetzt werden.

公开(公告)号：EP2997229A1

公开(公告)日：2016-03-23

申请号：EP14718358.6

申请日：2014-04-04

申请人： Siemens Aktiengesellschaft

发明人： BATT, Stephen ,  MCKENNA, Mike

IPC分类号： F01D5/22 ,  F01D5/24 ,  F01D11/00

CPC分类号： F01D5/16 ,  F01D5/147 ,  F01D5/225 ,  F01D5/24 ,  F01D11/006 ,  Y02T50/673

摘要： Blade system for a gas turbine, the blade system comprising a blade device (100) and a further blade device (300), the blade device comprising a shroud (110), an airfoil (105) extending from the shroud (110) along the radial direction (103), wherein the shroud (110) comprises at a circumferential end (111) a wedge face (201), wherein the wedge face (201) comprises a recess (202) extending with a component along the axial direction (102), and a damping wire (401), wherein the damping wire (401) is arranged within the recess (202) such that the damping wire (401) is adapted for contacting the shroud (110) and a further wedge face (403) of a further shroud (310) of a further blade device (300) which is arranged adjacent to the shroud (110) along the circumferential direction (104), wherein the recess (202) comprises an inclining side surface (402) which comprises a normal (n) which is non-parallel with the radial direction (103), wherein the further wedge face (403) comprises a plane surface onto which the damping wire (401) is abuttable. A corresponding method of manufacturing a blade system is also provided.

公开(公告)号：EP2980358A1

公开(公告)日：2016-02-03

申请号：EP15178880.9

申请日：2015-07-29

申请人： United Technologies Corporation

发明人： HILL, James ,  MERRY, Brian ,  SUCIU, Gabriel

IPC分类号： F01D5/22 ,  F01D11/00 ,  F01D5/06 ,  F01D5/24

CPC分类号： F01D11/04 ,  F01D5/06 ,  F01D5/18 ,  F01D5/225 ,  F01D5/24 ,  F01D11/001 ,  F01D11/005 ,  F01D11/006 ,  F05D2240/55 ,  Y02T50/673

摘要： A gas turbine engine (10) including an axial high pressure compressor having expansion slots (112) in an outer rim (116) of a rotor section. The expansion slots (112) may be positioned between blades (110) of a rotor segment (102, 104). The fore end of the slots (112) may have an axial seal (130) which is coupled to the inner surface (108) of the outer rim (116) in a first rotor segment (102), and may comprise a fin configuration. The axial seal (130) may be integral to the inner surface (108) of the outer rim (116). The compressor may comprise a plurality of expansion slots (112) and axial seals (130), including in a plurality of rotor segments (102, 104).

摘要翻译： 一种燃气涡轮发动机（10），包括轴向高压压缩机，其在转子部分的外缘（116）中具有膨胀槽（112）。 膨胀槽（112）可以位于转子段（102,104）的叶片（110）之间。 槽112的前端可以具有轴向密封件130，该轴向密封件130在第一转子段102中连接到外轮缘116的内表面108，并且可以包括翅片配置。 轴向密封件（130）可以与外边缘（116）的内表面（108）成一体。 压缩机可以包括多个膨胀槽（112）和轴向密封件（130），其包括在多个转子段（102,104）中。

公开(公告)号：EP2372090A3

公开(公告)日：2014-10-22

申请号：EP11158418.1

申请日：2011-03-16

申请人： General Electric Company

发明人： Johnson, David Martin

IPC分类号： F01D5/18 ,  F01D25/12 ,  F01D5/26 ,  F01D5/12 ,  F01D11/00 ,  F01D5/22 ,  F01D5/30 ,  F01D5/24

CPC分类号： F01D5/186 ,  F01D5/12 ,  F01D5/18 ,  F01D5/181 ,  F01D5/22 ,  F01D5/24 ,  F01D5/26 ,  F01D5/30 ,  F01D11/006 ,  F01D25/12 ,  F05D2260/202

摘要： A bucket assembly (30) cooling apparatus is provided. The bucket assembly (30) includes a platform (32), an airfoil (34), and a shank (36). The airfoil (34) may extend radially outward from the platform (32). The shank (36) may extend radially inward from the platform (32). The shank (36) may include a pressure side sidewall (42), a suction side sidewall (44), an upstream sidewall (46), and a downstream sidewall (48). The sidewalls (42, 44, 46, 48) may at least partially define a cooling circuit (90). The cooling circuit (90) may be configured to receive a cooling medium (95) and provide the cooling medium (95) to the airfoil (34). The upstream sidewall (46) may at least partially define an interior cooling passage (80) and at least partially define an exterior ingestion zone (70). The cooling passage (80) may be configured to provide a portion of the cooling medium (95) from the cooling circuit (90) to the ingestion zone (70) of an adjacent bucket assembly (30).

公开(公告)号：EP1163426A1

公开(公告)日：2001-12-19

申请号：EP00908907.9

申请日：2000-03-23

申请人： ABB Turbo Systems AG

发明人： PHILLIPSEN, Bent ,  MAMAEV, Boris ,  RYABOV, Evgeny

IPC分类号： F01D5/22 ,  F01D5/14 ,  F01D5/24

CPC分类号： F01D5/22 ,  F01D5/147 ,  F01D5/24 ,  Y10S416/50

摘要： The invention has the aim of improving the efficiency of a turbomachine blade fitted with a reinforced hole for receiving a damping element. To this end, the raised end faces (12, 13) of the edge area (11) of the blade (4), which is reinforced in the direction of the hole (10), is configured with an acute angle α that is open relative to the input edge (5) of the blade and/or with an acute angle β that is open relative to the tip (9) of the blade.

摘要翻译： 本发明的目的在于提高配备有用于接收阻尼元件的加强孔的涡轮机叶片的效率。 为此，在孔（10）的方向上加强的叶片（4）的边缘区域（11）的升高的端面（12,13）构造成具有打开的锐角α 相对于叶片的输入边缘（5）和/或具有相对于叶片的尖端（9）打开的锐角β。

公开(公告)号：EP0881361A3

公开(公告)日：1999-12-08

申请号：EP98109379.2

申请日：1998-05-22

申请人： Ishikawajima-Harima Heavy Industries Co., Ltd.

发明人： Tsukamoto, Minoru ,  Mitsubori, Ken

IPC分类号： F01D5/24

CPC分类号： F01D5/24 ,  Y10S416/50

摘要： An arrangement for attenuating vibrations of blades (2) attached to a peripheral surface (6) of a rotor (1) of an axial turbine.
   A through hole (10) is formed in each rotor blade (2) in a generally thickness direction of the blade (2) so that the through holes (10) in combination define a single annular passage near a rotor surface (6) when all of the rotor blades (2) are attached to the rotor (1). A wire (11) is provided to extend through the aligned through holes (10). Thus, the wire (11) frictionally contacts the through holes (10) when the blades (2) are caused to vibrate due to a gas pressure and a centrifugal force generated upon operation of the axial turbine.
Friction contact between the wire (11) and the through holes (10) attenuates vibrations of the blades (2).

公开(公告)号：EP0622526B1

公开(公告)日：1997-09-17

申请号：EP94300924.1

申请日：1994-02-08

申请人： TELEFLEX INCORPORATED

发明人： Roberts, William B.

IPC分类号： F01D5/14 ,  F01D5/24 ,  F02C7/04

CPC分类号： F01D5/20 ,  F01D5/143 ,  F01D5/22 ,  F01D11/12 ,  F05D2220/327 ,  Y02T50/673 ,  Y10S415/914

公开(公告)号：EP2799477B1

公开(公告)日：2019-05-08

申请号：EP14162570.7

申请日：2014-03-31

申请人： Rolls-Royce plc

发明人： Zizzo, Claudio

IPC分类号： C08K3/04 ,  C08K7/06 ,  F02C7/00 ,  F02C7/20 ,  H01B1/24 ,  C08J5/24 ,  F01D5/24 ,  F01D5/28