EP2386721A1 - Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication - Google Patents

Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication Download PDF

Info

Publication number
EP2386721A1
EP2386721A1 EP10005079A EP10005079A EP2386721A1 EP 2386721 A1 EP2386721 A1 EP 2386721A1 EP 10005079 A EP10005079 A EP 10005079A EP 10005079 A EP10005079 A EP 10005079A EP 2386721 A1 EP2386721 A1 EP 2386721A1
Authority
EP
European Patent Office
Prior art keywords
groove
blade
fastening arrangement
retaining
blade carrier
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP10005079A
Other languages
German (de)
English (en)
Inventor
Patrick Bullinger
Marco Link
Nicolas Savilius
Uwe Sieber
Hubertus Michael Dr. Wigger
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP10005079A priority Critical patent/EP2386721A1/fr
Priority to EP11723334.6A priority patent/EP2569514B1/fr
Priority to PCT/EP2011/057628 priority patent/WO2011141514A1/fr
Priority to US13/696,618 priority patent/US20130101422A1/en
Priority to CN2011800240739A priority patent/CN102906375A/zh
Priority to JP2013509563A priority patent/JP5596223B2/ja
Priority to RU2012154199/06A priority patent/RU2012154199A/ru
Publication of EP2386721A1 publication Critical patent/EP2386721A1/fr
Withdrawn legal-status Critical Current

Links

Images

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 fastening arrangement.
  • 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 circumferential groove.
  • rotating systems it is known that blades are inserted into a respectively associated, extending in the axial direction groove.
  • the object directed to the mounting arrangement is achieved by one which is designed according to the features of claim 1.
  • the object directed to the manufacturing method is achieved both by a method according to claim 11 as well as with a method according to claim 13.
  • the mounting arrangement according to the invention for blades of axially permeable turbomachinery comprises a blade carrier having a central axis and a concentric lateral surface, in which distributed along the circumference retaining grooves are provided with axial extension and blades whose blade roots are inserted into these retaining grooves, each retaining groove has a groove bottom which is opposite to an underside of the respective blade root, and in each case a resilient clamping element arranged between each groove base and the underside thereof, which prestresses on the relevant underside and on the relevant groove base, wherein in each case a groove is provided in the undersides of the blades, in which the relevant clamping element surface, ie along its longitudinal extent.
  • 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.
  • a gutter is 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 that happens Inserting a blade into its associated retaining groove. Subsequently, the blade is temporarily fixed in the retaining groove. This is followed by the pairwise, ie simultaneous production of the two opposing grooves by a single drilling operation.
  • the bore extends along the bottom groove bottom plane and cuts in half in the blade root 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 can be produced simultaneously in a relatively simple manner and without unduly great expense. Since 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 the corresponding channels. 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 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 bores are respectively placed so that later in the production of one of the retaining grooves only a part of the surrounding hole in question material is removed. Subsequently, the retaining grooves are made in the blade carrier, wherein in each case during which only a part of the material surrounding the hole in question is removed, so that the remaining part of the material surrounding the hole in question forms the nutground worne groove. Subsequently, the insertion of blades takes place, in each case with the gutter already present on the underside and the insertion of the tensioning element into the space delimited by the opposing gutters.
  • This manufacturing method has the advantage that the channel arranged in the blade carrier can be prepared comparatively easily and without any special effort, in particular if the longitudinal directions of the channel and retaining groove are different.
  • both grooves extend parallel to the longitudinal extension of the retaining groove.
  • the grooves extend obliquely to the longitudinal extent of the retaining groove.
  • the latter variant has the particular advantage that due to the mutually inclined direction of displacement of blades (along the retaining) and clamping element (along the channel) a positive connection between the blade root and groove by means of the clamping element is brought about, which at the same time as axial securing against displacement of the blades along the holding groove serves.
  • the clamping element is at the same time the Axialverschiebungs Klisfunktion.
  • the shearing forces acting on the clamping elements by the blades prevent the latter from being released from the channels.
  • the longitudinal extension of the retaining grooves is inclined relative to the central axis and the grooves extend parallel to the central axis.
  • the groove-base channel opens in at least one of the two end faces of the blade carrier, which adjoin the lateral surface. And / or the bottom channel opens into at least one of the two end faces of the blade root, which adjoin the bottom. Accordingly, from a lateral accessibility of the grooves for mounting the clamping element, which is preferably designed as a dowel pin, are assumed.
  • the end opening of one or more grooves is caulked.
  • the proposed mounting arrangement is applicable to both rotating and static systems.
  • the blade is formed as a blade with axial feet and the blade carrier as the rotor element, wherein at least a portion of the radially outer 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 guide vane with axial feet and the blade carrier as an annular vane support member, wherein at least a portion of the radially inner circumferential surface of the vane support forms the respective lateral surface of the blade carrier.
  • FIG. 1 shows a perspective view of a compressor blade formed as a blade 10.
  • the compressor blade includes a rudimentary only illustrated blade 12, to which a blade root 14 connects.
  • the blade root 14 has an outer contour which is dovetail-shaped, in order in an in FIG. 1 not shown blade carrier to be held positively.
  • the blade root 14 has an underside 16, in which a channel 18 is arranged.
  • the channel 18 will also be referred to below as the bottom channel 18.
  • the underside channel 18 extends over the entire longitudinal extension of the blade root 14, so that it ends at the end-side, dovetail-shaped contoured end faces of the blade root 14.
  • the channel 18 is in U-shape, thus groove-shaped with a semicircular basic contour and formed so deep that it can accommodate a trained as a clamping pin, not shown clamping element almost, but not completely. This makes it possible to fasten the blade 10 biased by means of the clamping pin in a holding groove, which has no groove-side groove.
  • FIG. 2 shows in perspective view 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.
  • groove base 24 of the retaining groove 22 is a groove-side groove 26 is provided.
  • blade 10 differs from the in FIG. 1 illustrated blade 10 in that the groove 18 is not U-shaped, but only in is designed approximately semicircular.
  • the openings of both channels 18, 26 face each other. Viewed in cross section, both channels 18, 26 form an approximately circular contour. 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.
  • clamping pin 28 arranged on the blade root 14 supporting flanks 30 are pressed against each forming an undercut flanks 32 of the retaining groove 22, whereby the blade 10 is intended radially held.
  • Both channels 18, 26 extend over the entire axial extent of the retaining groove 22, so that the clamping element 28 is used frontally ( FIG. 3 ). It should be noted that the clamping element 28 in FIG. 3 is shown only schematically by the cross section is shown rotated at 90 °.
  • the blade carrier 20 in FIG. 5 and the blade root 14 in FIG. 4 are schematically shown, the grooves 18, 26 extend transversely, ie obliquely to the longitudinal extent of the retaining groove 22.
  • the lower-side groove 18 now not frontally opens in the blade root 14, but the trailing edge side ( FIG. 4 ).
  • 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 in FIG. 5 shown.
  • the mouth 34 of the nut brieflyen groove 26 outside the mouth 38 of the retaining groove 22.
  • the longitudinal displacement of the blade 10 along the retaining groove 22 is prevented in that the clamping element 28 on the one hand in a form-fitting manner in the bore or groove 26 and on the other hand also engages in the lower side groove 18 of the blade root 14. Due to the different displacement directions of the blade 10 - along the retaining groove 22 - and the clamping element 28 - along the grooves 18, 26 - the blade 10 is secured against displacement along the retaining groove 22 simultaneously with the insertion of the clamping element.
  • the invention provides a fastening arrangement 8 for blades 10 of axially flow-through turbomachinery, preferably compressors, comprising a blade carrier 20 with a lateral surface in which along the circumference distributed retaining grooves 22 are provided and in which blades 10 are inserted, wherein between each groove bottom 24 and the opposite this bottom 16 of the respective blade root 14, a resilient clamping element 28 is provided, which is biasedly supported on the relevant bottom 16 and the relevant groove base 24, wherein both in the groove base 24 and in the bottom 16 each have a groove 18, 26 is provided is, 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)
EP10005079A 2010-05-14 2010-05-14 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication Withdrawn EP2386721A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP10005079A EP2386721A1 (fr) 2010-05-14 2010-05-14 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication
EP11723334.6A EP2569514B1 (fr) 2010-05-14 2011-05-11 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication
PCT/EP2011/057628 WO2011141514A1 (fr) 2010-05-14 2011-05-11 Agencement de fixation pour aubes de turbomachines à circulation axiale et procédé de fabrication d'un tel agencement
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
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

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10005079A EP2386721A1 (fr) 2010-05-14 2010-05-14 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication

Publications (1)

Publication Number Publication Date
EP2386721A1 true EP2386721A1 (fr) 2011-11-16

Family

ID=43017149

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10005079A Withdrawn EP2386721A1 (fr) 2010-05-14 2010-05-14 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication
EP11723334.6A Not-in-force EP2569514B1 (fr) 2010-05-14 2011-05-11 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP11723334.6A Not-in-force EP2569514B1 (fr) 2010-05-14 2011-05-11 Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication

Country Status (6)

Country Link
US (1) US20130101422A1 (fr)
EP (2) EP2386721A1 (fr)
JP (1) JP5596223B2 (fr)
CN (1) CN102906375A (fr)
RU (1) RU2012154199A (fr)
WO (1) WO2011141514A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2990462A1 (fr) * 2012-05-14 2013-11-15 Snecma Dispositif d'attache d'aubes sur un disque de rotor de turbomachine
WO2014022358A1 (fr) * 2012-08-01 2014-02-06 General Electric Company Jointure de boucle pour un carénage divisé d'un moteur à turbine à gaz
US20140072419A1 (en) * 2012-09-13 2014-03-13 Manish Joshi Rotary machines and methods of assembling
WO2014204542A3 (fr) * 2013-04-01 2015-03-05 United Technologies Corporation Aube légère destinée à un moteur à turbine à gaz
EP2617946A3 (fr) * 2012-01-23 2017-07-26 MTU Aero Engines AG Système pour prédéterminer la position de montage d'aubes mobiles, élément de sécurisation, aube directrice, turbomachine et procédé
EP3228825A1 (fr) * 2016-04-06 2017-10-11 General Electric Company Aubes de guidage de turbine à vapeur présentant un élément d'alignement et turbine à vapeur

Families Citing this family (10)

* Cited by examiner, † Cited by third party
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
JP6118104B2 (ja) * 2012-12-26 2017-04-19 川崎重工業株式会社 プロペラ翼固定機構
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
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
CN110439858B (zh) * 2019-09-09 2024-10-18 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

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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 (fr) * 2006-04-07 2007-11-28 Siemens Aktiengesellschaft Dispositif de verrouillage d'une aube de turbine comprenant un élément de verrouillage

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US5236309A (en) * 1991-04-29 1993-08-17 Westinghouse Electric Corp. Turbine blade assembly
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
JP2004076648A (ja) * 2002-08-19 2004-03-11 Toshiba Corp ガスタービンのギヤ交換支援装置
JP4352757B2 (ja) * 2003-05-14 2009-10-28 株式会社Ｉｈｉ ジェットエンジン用ファン及びファンスペーサ
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
CN101258305B (zh) * 2005-09-07 2011-06-15 西门子公司 用于对转子中的动叶片进行轴向固定的装置、用于一种这样的装置的密封件以及一种这样的装置的应用
DE102008013118B4 (de) * 2008-03-07 2014-03-27 Man Diesel & Turbo Se Anordnung zum Befestigen von Turbinenschaufeln

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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 (fr) * 2006-04-07 2007-11-28 Siemens Aktiengesellschaft Dispositif de verrouillage d'une aube de turbine comprenant un élément de verrouillage

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2617946A3 (fr) * 2012-01-23 2017-07-26 MTU Aero Engines AG Système pour prédéterminer la position de montage d'aubes mobiles, élément de sécurisation, aube directrice, turbomachine et procédé
FR2990462A1 (fr) * 2012-05-14 2013-11-15 Snecma Dispositif d'attache d'aubes sur un disque de rotor de turbomachine
US9518470B2 (en) 2012-05-14 2016-12-13 Snecma Device for attaching blades to a turbine engine rotor disk
WO2014022358A1 (fr) * 2012-08-01 2014-02-06 General Electric Company Jointure de boucle pour un carénage divisé d'un moteur à turbine à gaz
CN104508250A (zh) * 2012-08-01 2015-04-08 通用电气公司 用于燃气涡轮发动机的分开式整流片的扣接头
CN104508250B (zh) * 2012-08-01 2017-06-09 通用电气公司 用于燃气涡轮发动机中的支柱的整流片
US20140072419A1 (en) * 2012-09-13 2014-03-13 Manish Joshi Rotary machines and methods of assembling
WO2014204542A3 (fr) * 2013-04-01 2015-03-05 United Technologies Corporation Aube légère destinée à un moteur à turbine à gaz
EP3228825A1 (fr) * 2016-04-06 2017-10-11 General Electric Company Aubes de guidage de turbine à vapeur présentant un élément d'alignement et turbine à vapeur
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

Also Published As

Publication number Publication date
JP5596223B2 (ja) 2014-09-24
US20130101422A1 (en) 2013-04-25
EP2569514A1 (fr) 2013-03-20
JP2013526667A (ja) 2013-06-24
RU2012154199A (ru) 2014-06-20
EP2569514B1 (fr) 2014-04-02
CN102906375A (zh) 2013-01-30
WO2011141514A1 (fr) 2011-11-17

Similar Documents

Publication Publication Date Title
EP2569514B1 (fr) Dispositif de fixation pour pales de turbomachines pouvant s'écouler axialement et son procédé de fabrication
EP2426315B1 (fr) Section de rotor pour un rotor d'une turbomachine
EP2295724B1 (fr) Aube statorique pour une turbomachine à flux axial et agencement associé d'aubes statoriques
EP1944471B1 (fr) Partie axiale d'une rotor de turbine
DE102009003714B4 (de) Turbinenstatorschaufelhaltesystem und -verfahren
DE19507673C2 (de) Leitrad für Turbomaschinen
EP2084369B1 (fr) Dispositif de guidage d'une turbomachine et aube directrice pour un dispositif de guidage de ce type
EP2806107B1 (fr) Bague intérieure séparée
DE19547653A1 (de) Leitvorrichtung für eine Turbine mit einem Leitschaufelträger und Verfahren zur Herstellung dieser Leitvorrichtung
EP2238374B1 (fr) Assemblage avec joint brosse et procédé de montage d'un joint brosse
DE102004057025B4 (de) Verfahren zum Installieren von ortsfesten Schaufeln einer Turbine und Turbinenstruktur mit einem radialen Spannstift
DE10101539A1 (de) Verfahren zur Herstellung einer gebauten Welle
EP2591213B1 (fr) Compresseur et turbine à gaz associée
EP3203035A1 (fr) Système d'aube directrice d'une turbomachine
EP1733124A1 (fr) Turbomachine et rotor pour turbomachine
DE10331601B4 (de) Dichtungsanordnung und Verfahren zur Herstellung derselben
EP1570196B1 (fr) Joint brosse destine a rendre etanche une fente entre un rotor et un stator
EP2149677A1 (fr) Dispositif de fixation destiné à la fixation d'une pale de rotor sur une turbomachine
EP1552149A1 (fr) Stator pour pompe a vis sans fin excentrique
EP2636849B1 (fr) Compresseur
EP3075961A1 (fr) Ensemble d'aube directrice
EP3599388B1 (fr) Dispositif de chargement
EP1724495A1 (fr) Transmission à courroie crantée et procédé de fabrication d'un poulie pour transmission à courroie crantée
DE102019116250A1 (de) Schwenkwiegenlagerung und Verfahren zur Herstellung einer Schwenkwiegenlagerung
DE102013017713A1 (de) Turbomaschine

Legal Events

Date Code Title Description
AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME RS

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20120517