WO2011141514A1 - Befestigungsanordnung für schaufeln von axial durchströmten turbomaschinen sowie verfahren zum herstellen einer solchen - Google Patents
Befestigungsanordnung für schaufeln von axial durchströmten turbomaschinen sowie verfahren zum herstellen einer solchen Download PDFInfo
- Publication number
- WO2011141514A1 WO2011141514A1 PCT/EP2011/057628 EP2011057628W WO2011141514A1 WO 2011141514 A1 WO2011141514 A1 WO 2011141514A1 EP 2011057628 W EP2011057628 W EP 2011057628W WO 2011141514 A1 WO2011141514 A1 WO 2011141514A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- groove
- blade
- retaining
- fastening arrangement
- grooves
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/322—Blade mountings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/90—Mounting on supporting structures or systems
- F05B2240/94—Mounting on supporting structures or systems on a movable wheeled structure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/70—Disassembly methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/90—Mounting on supporting structures or systems
- F05D2240/91—Mounting on supporting structures or systems on a stationary structure
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
Definitions
- the invention relates to a fastening arrangement according to the preamble of claim 1. Furthermore, the invention relates to a method for producing such a Befest Trentsanord- tion.
- the present invention relates to the mechanical connection of stationary or rotating blades of the flow path of an axial-flow turbomachine. These are vanes which are fastened to the housing or to a corresponding guide blade carrier or to rotor blades which are arranged on the rotor of the turbomachine.
- vanes of a blade ring are mounted in a circumferentially extending groove.
- rotor blades are inserted into a respectively associated ⁇ impaired, axially extending groove.
- a resilient Be ⁇ fastening of moving blades in a circumferential groove of the turbine rotor is known from US 6,761,538 B2, which are pressed by means of a both lekssgeschlitz ⁇ th and quergeschlitzten tubular spring element on the known hammer-shaped interlocking.
- US Pat. No. 2,753,149 discloses a further type of fastening of compressor rotor blades to a rotor disk.
- a double-headed bolt connection is provided between the groove base of the axial groove and the blade root underside. Nevertheless, a slight movement of the
- the object relating to the fastening arrangement object is achieved by one which is designed according to the features of the on ⁇ claim 1.
- the manufacturing method of the ge ⁇ addressed object is solved both by a method according to claim 11 and by a method according to claim. 13
- the mounting arrangement according to the invention for blades of axial throughflow turbomachine comprises a blade carrier having a central axis and a concentric jacket surface, in which along the circumference distributed holding grooves with an axial extension are provided and blades whose blade roots are inserted in these retaining slots where ⁇ at each Holding groove has a groove bottom, which is opposite to a lower ⁇ side of the respective blade root, and depending Weil ⁇ a resilient, arranged between each groove base and the underside of this opposite clamping element, wel ⁇ Ches is biased on the respective bottom and the respective groove base, wherein in the undersides of the blades are each provided with a groove, in which the relevant clamping element surface, that is applied along its longitudinal ⁇ extension.
- a suitable groove for guiding the clamping element is arranged in the groove base.
- the invention is based on the finding that an improved contact pressure of the blade in the retaining groove can be achieved if at least on the blade root underside a channel is provided, in which the clamping element rests positively over its entire length. For a over the length of the undercut Verhakungs Kunststoffs gleichmä ⁇ ssige contact pressure of the blade is achieved, which is not the case with the closest prior art. At the same time an increased process quality is achieved during assembly of the blade in the retaining, since an individual adjustment of blades for pressing and fixing is not required.
- gutters are provided both in the blade root underside and in the groove bottom, these gutters can be produced particularly easily with the aid of the following methods.
- the blades and the blade carrier are made including all retaining grooves. Then the insertion of a blade takes place in the associated retaining groove. At ⁇ closing the blade is temporarily xed fi in the holding. This is followed by the pairs, ie simultaneous Her provide ⁇ of the two opposite grooves by a single drilling operation.
- the bore extends along the underside-groove bottom plane and cuts in half in the Schau ⁇ felfuß and in the blade carrier. Subsequently, the insertion of the clamping element takes place in the bore. It is preferably provided that the temporary fixation is released again before or after insertion of the tensioning element.
- both channels are produced in only one drilling operation, it can be assumed that their position is very high in accuracy with respect to both channels, which results in a particularly reliable seating of the spring element in FIG causes the corresponding grooves. This has the consequence that with predetermined clamping forces the blade can be pressed in its retaining groove to the undercuts, in particular over the entire length of the undercuts.
- a second method according to the invention comprises the following steps: first, the blade carrier is produced, but without the associated retaining grooves. Subsequently, a drilling of the blade carrier, wherein the holes are each placed in such a way that later in the manufacture of one of the
- This production process has the advantage that the arranged in the shop ⁇ felabo channel can be preliminarily prepared relatively easily and without any special effort, in particular if the longitudinal directions of the channel and hold ⁇ are nut different.
- both grooves extend parallel to the longitudinal extension of the retaining groove.
- the grooves extend obliquely to the longitudinal extension of the retaining groove.
- the last-mentioned variant has the particular advantage that due to the mutually inclined displacement direction of blades (along the retaining groove) and clamping element (along the channel) a positive connection between the blade root and groove by means of Clamping element is brought about, which also serves as axial securing against displacement of the blades along the retaining groove.
- the clamping element is at the same time the Axialverschiebungs Anlagensfunktion.
- the shearing forces acting on the clamping elements by the blades prevent the latter from being released from the channels.
- the Lekserstre- ckung of the retaining grooves relative to the central axis is inclined and the grooves extend parallel to the central axis.
- the groove-side channel opens into at least one of the two end faces of the
- Blade carrier which adjoin the lateral surface.
- each blade is designed as a blade with axial feet and the blade carrier as a rotor element, wherein at least a portion of the radially outer shell ⁇ surface of the rotor element forms the respective lateral surface of the blade carrier with the corresponding retaining grooves.
- each blade is formed as a vane with axial feet and the blade carrier as an annular vane support member, wherein at least a portion of the radially inner surface of the vane support forms the respective lateral surface of the blade carrier.
- FIG. 2 shows a perspective view of a portion of the fastening arrangement according to the invention with a holding groove and a blade seated therein
- FIG. 4 shows a blade according to a second embodiment
- FIG. 5 shows a blade carrier according to a second embodiment, suitable for receiving the blade shown in FIG.
- FIG. 1 shows, in a perspective view, a blade 10 designed as a compressor blade.
- the compressor blade comprises an airfoil 12 which is only partially shown, to which a blade root 14 adjoins.
- the blade ⁇ foot 14 has an outer contour which swallowtail mig is adapted to be held in a blade carrier in FIG 1, not shown, form-fitting manner.
- the Schaufeififuß 14 has an underside 16, in which a
- the channel 18 is arranged.
- the channel 18 will also be referred to below as the bottom channel 18.
- the lower side groove 18 extends over the entire longitudinal extent of the Blade root 14, so that it ends at the front side, dovetail-shaped contoured end surfaces of the blade root 14.
- the channel 18 is configured in a U-shape, that is to say in the shape of a groove with a semicircular basic contour, and is formed so deep that it can almost, but not completely, receive a clamping element, not shown, in the form of a tensioning pin. This makes it possible, the blade 10 by means of the clamping pin biased in a holding groove to tes ⁇ term, which has no groove-side groove.
- FIG. 2 shows a perspective representation of a blade carrier 20 of a fastening arrangement 8.
- a retaining groove 22 is provided, which has a contour corresponding to the blade root 14 of the blade 10.
- the contour of the retaining groove 22 is not blade-footed but modified.
- Nut ⁇ reason 24 of the retaining groove 22 is a groove-side groove 26 is provided.
- the blade 10 shown in FIG 2 under failed ⁇ det thereby from the position shown in FIG 1 the blade 10 is that the channel 18 is not U-shaped, but merely configured semi-circular.
- the openings of both channels 18, 26 face each other. Viewed in cross section, form both channels 18, 26 an approximately circular Kon ⁇ structure . They are also along their longitudinal extent always opposite each other and are thus suitable for receiving a clamping ⁇ element 28, which is usually designed as a dowel pin.
- FIG 3 It should be noted that the clamping element 28 is shown only schematically in FIG 3, by the cross section is shown rotated in 90 °. According to an alternative fastening arrangement 8, whose
- Shovel carrier 20 in FIG 5 and the blade root 14 are shown schematically in Figure 4, the grooves 18, 26 extend transversely, ie obliquely to the longitudinal extent of the holding 22. This has the consequence that the bottom channel 18 now not frontally opens in the blade root 14 but on the wing side (FIG. 4). Further, the groove-side groove 26 opens now not in the contour of the retaining groove 22, but outside of which as a bore opening. This is Darge provides ⁇ in FIG. 5 There, the mouth 34 of the nutground remedy groove 26 outside the mouth 38 of the retaining groove 22.
- a mounting assembly 8 for blades 10 of axial throughflow turbomachines, preferably compressors is specified with the invention
- a blade ⁇ carrier 20 are provided with a circumferential surface, in which along the environmental distributed fangs retaining grooves 22 and comprising in which Blades 10 are used, wherein between each groove bottom 24 and the opposite bottom 16 of the respective blade root 14, a resilient clamping element 28 is provided, which is biased on the respective bottom 16 and the respective groove bottom 24, where ⁇ both in the groove base 24 and in the bottom 16 each have a groove 18, 26 is provided, in which the clamping element 28 abuts.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP11723334.6A EP2569514B1 (de) | 2010-05-14 | 2011-05-11 | Befestigungsanordnung für schaufeln von axial durchströmten turbomaschinen sowie verfahren zum herstellen einer solchen |
RU2012154199/06A RU2012154199A (ru) | 2010-05-14 | 2011-05-11 | Система крепления лопаток турбомашин с осевым перемещением рабочего тела, а также способ изготовления такой системы |
US13/696,618 US20130101422A1 (en) | 2010-05-14 | 2011-05-11 | Fastening assembly for blades of turbomachines having axial flow and method for producing such an assembly |
CN2011800240739A CN102906375A (zh) | 2010-05-14 | 2011-05-11 | 用于轴流式涡轮机的叶片的固定装置及其制造方法 |
JP2013509563A JP5596223B2 (ja) | 2010-05-14 | 2011-05-11 | 軸流型ターボ機械のブレード用の固定アセンブリおよびそうしたアセンブリを製造するための方法 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10005079.8 | 2010-05-14 | ||
EP10005079A EP2386721A1 (de) | 2010-05-14 | 2010-05-14 | Befestigungsanordnung für Schaufeln von axial durchströmbaren Turbomaschinen sowie Verfahren zum Herstellen einer solchen |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011141514A1 true WO2011141514A1 (de) | 2011-11-17 |
Family
ID=43017149
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2011/057628 WO2011141514A1 (de) | 2010-05-14 | 2011-05-11 | Befestigungsanordnung für schaufeln von axial durchströmten turbomaschinen sowie verfahren zum herstellen einer solchen |
Country Status (6)
Country | Link |
---|---|
US (1) | US20130101422A1 (de) |
EP (2) | EP2386721A1 (de) |
JP (1) | JP5596223B2 (de) |
CN (1) | CN102906375A (de) |
RU (1) | RU2012154199A (de) |
WO (1) | WO2011141514A1 (de) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130333173A1 (en) * | 2012-06-15 | 2013-12-19 | Mitsubishi Heavy Industries, Ltd. | Blade root spring insertion jig and insertion method of blade root spring |
JP2014125047A (ja) * | 2012-12-26 | 2014-07-07 | Kawasaki Heavy Ind Ltd | プロペラ翼固定機構 |
JP2015524533A (ja) * | 2012-08-01 | 2015-08-24 | ゼネラル・エレクトリック・カンパニイ | ガスタービンエンジンの分割フェアリング用のバックル接合部 |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102012200891A1 (de) * | 2012-01-23 | 2013-07-25 | Mtu Aero Engines Gmbh | System zur Vorgabe einer Einbauposition von Laufschaufeln, Sicherungselement, Laufschaufel, Turbomaschine sowie Verfahren |
FR2990462B1 (fr) | 2012-05-14 | 2014-05-30 | Snecma | Dispositif d'attache d'aubes sur un disque de rotor de turbomachine |
US20140072419A1 (en) * | 2012-09-13 | 2014-03-13 | Manish Joshi | Rotary machines and methods of assembling |
WO2014204542A2 (en) * | 2013-04-01 | 2014-12-24 | United Technologies Corporation | Lightweight blade for gas turbine engine |
US10400784B2 (en) | 2015-05-27 | 2019-09-03 | United Technologies Corporation | Fan blade attachment root with improved strain response |
US10309240B2 (en) | 2015-07-24 | 2019-06-04 | General Electric Company | Method and system for interfacing a ceramic matrix composite component to a metallic component |
US10287903B2 (en) * | 2016-04-06 | 2019-05-14 | General Electric Company | Steam turbine drum nozzle having alignment feature, related assembly, steam turbine and storage medium |
CN108050101A (zh) * | 2017-12-19 | 2018-05-18 | 哈尔滨广瀚燃气轮机有限公司 | 一种舰船燃气轮机高压比压气机叶片连接外环 |
KR101950922B1 (ko) * | 2018-09-06 | 2019-02-21 | 터보파워텍(주) | 가스터빈용 베인조립체 |
CN110397625A (zh) * | 2019-08-15 | 2019-11-01 | 上海电气燃气轮机有限公司 | 一种新型叶片锁紧装置 |
CN110439858A (zh) * | 2019-09-09 | 2019-11-12 | 上海电气燃气轮机有限公司 | 一种具有减振效果的叶片锁紧结构 |
KR102355521B1 (ko) * | 2020-08-19 | 2022-01-24 | 두산중공업 주식회사 | 압축기 블레이드의 조립구조와 이를 포함하는 가스 터빈 및 압축기 블레이드의 조립방법 |
CN112128040B (zh) * | 2020-09-23 | 2022-05-24 | 国家电网有限公司 | 立轴混流式水轮机上下止漏环检查工法 |
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US2753149A (en) | 1951-03-30 | 1956-07-03 | United Aircraft Corp | Blade lock |
US2801074A (en) * | 1952-10-01 | 1957-07-30 | United Aircraft Corp | Blade retaining means |
US4778342A (en) * | 1985-07-24 | 1988-10-18 | Imo Delaval, Inc. | Turbine blade retainer |
US4836749A (en) | 1988-02-19 | 1989-06-06 | Westinghouse Electric Corp. | Pre-load device for a turbomachine rotor |
US6761538B2 (en) | 2002-10-31 | 2004-07-13 | General Electric Company | Continual radial loading device for steam turbine reaction type buckets and related method |
GB2406144A (en) * | 2003-09-19 | 2005-03-23 | Rolls Royce Plc | Gas turbine engine blade retention system using a key |
EP1860280A1 (de) * | 2006-04-07 | 2007-11-28 | Siemens Aktiengesellschaft | Verriegelungsvorrichtung einer Turbinenschaufel mit einem Sperrelement |
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US1619133A (en) * | 1922-01-07 | 1927-03-01 | Westinghouse Electric & Mfg Co | Blade fastening |
US2847187A (en) * | 1955-01-21 | 1958-08-12 | United Aircraft Corp | Blade locking means |
US3070351A (en) * | 1959-02-06 | 1962-12-25 | Gen Motors Corp | Blade retention |
US3326523A (en) * | 1965-12-06 | 1967-06-20 | Gen Electric | Stator vane assembly having composite sectors |
US3479009A (en) * | 1968-05-15 | 1969-11-18 | Gen Electric | Blade retainer |
US3572970A (en) * | 1969-01-23 | 1971-03-30 | Gen Electric | Turbomachinery blade spacer |
US4022545A (en) * | 1974-09-11 | 1977-05-10 | Avco Corporation | Rooted aerodynamic blade and elastic roll pin damper construction |
JPS5918160Y2 (ja) * | 1978-03-31 | 1984-05-25 | 川崎重工業株式会社 | 回転機械の翼車装置 |
US4725200A (en) * | 1987-02-24 | 1988-02-16 | Westinghouse Electric Corp. | Apparatus and method for reducing relative motion between blade and rotor in steam turbine |
JP2500245Y2 (ja) * | 1991-04-12 | 1996-06-05 | 川崎重工業株式会社 | 動翼固定装置 |
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FR2807096B1 (fr) * | 2000-03-30 | 2002-05-31 | Abb Alstom Power Nv | Disque rotorique de turbine equipe d'ailettes a pied de sapin et procede de montage d'une ailette sur un disque |
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FR2881174B1 (fr) * | 2005-01-27 | 2010-08-20 | Snecma Moteurs | Dispositif de positionnement d'une aube et disque aubage comportant un tel dispositif |
DE102005024932A1 (de) * | 2005-05-31 | 2006-12-07 | Rolls-Royce Deutschland Ltd & Co Kg | Turbinenschaufelaxialsperre |
US8105041B2 (en) * | 2005-09-07 | 2012-01-31 | Siemens Aktiengesellschaft | Arrangement for axially securing rotating blades in a rotor, sealing element for such an arrangement, and use of such an arrangement |
DE102008013118B4 (de) * | 2008-03-07 | 2014-03-27 | Man Diesel & Turbo Se | Anordnung zum Befestigen von Turbinenschaufeln |
-
2010
- 2010-05-14 EP EP10005079A patent/EP2386721A1/de not_active Withdrawn
-
2011
- 2011-05-11 EP EP11723334.6A patent/EP2569514B1/de not_active Not-in-force
- 2011-05-11 RU RU2012154199/06A patent/RU2012154199A/ru not_active Application Discontinuation
- 2011-05-11 US US13/696,618 patent/US20130101422A1/en not_active Abandoned
- 2011-05-11 CN CN2011800240739A patent/CN102906375A/zh active Pending
- 2011-05-11 JP JP2013509563A patent/JP5596223B2/ja not_active Expired - Fee Related
- 2011-05-11 WO PCT/EP2011/057628 patent/WO2011141514A1/de active Application Filing
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
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US2753149A (en) | 1951-03-30 | 1956-07-03 | United Aircraft Corp | Blade lock |
US2801074A (en) * | 1952-10-01 | 1957-07-30 | United Aircraft Corp | Blade retaining means |
US4778342A (en) * | 1985-07-24 | 1988-10-18 | Imo Delaval, Inc. | Turbine blade retainer |
US4836749A (en) | 1988-02-19 | 1989-06-06 | Westinghouse Electric Corp. | Pre-load device for a turbomachine rotor |
US6761538B2 (en) | 2002-10-31 | 2004-07-13 | General Electric Company | Continual radial loading device for steam turbine reaction type buckets and related method |
GB2406144A (en) * | 2003-09-19 | 2005-03-23 | Rolls Royce Plc | Gas turbine engine blade retention system using a key |
EP1860280A1 (de) * | 2006-04-07 | 2007-11-28 | Siemens Aktiengesellschaft | Verriegelungsvorrichtung einer Turbinenschaufel mit einem Sperrelement |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US20130333173A1 (en) * | 2012-06-15 | 2013-12-19 | Mitsubishi Heavy Industries, Ltd. | Blade root spring insertion jig and insertion method of blade root spring |
JP2015524533A (ja) * | 2012-08-01 | 2015-08-24 | ゼネラル・エレクトリック・カンパニイ | ガスタービンエンジンの分割フェアリング用のバックル接合部 |
JP2014125047A (ja) * | 2012-12-26 | 2014-07-07 | Kawasaki Heavy Ind Ltd | プロペラ翼固定機構 |
Also Published As
Publication number | Publication date |
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EP2569514B1 (de) | 2014-04-02 |
RU2012154199A (ru) | 2014-06-20 |
JP5596223B2 (ja) | 2014-09-24 |
CN102906375A (zh) | 2013-01-30 |
EP2569514A1 (de) | 2013-03-20 |
US20130101422A1 (en) | 2013-04-25 |
EP2386721A1 (de) | 2011-11-16 |
JP2013526667A (ja) | 2013-06-24 |
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