EP0699824B1 - Dispositif pour le verrouillage d'aubes de rotor et pour l'élimination du déséquilibre du rotor de compresseurs ou turbines de turbines à gaz - Google Patents

Dispositif pour le verrouillage d'aubes de rotor et pour l'élimination du déséquilibre du rotor de compresseurs ou turbines de turbines à gaz Download PDF

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Publication number
EP0699824B1
EP0699824B1 EP95112351A EP95112351A EP0699824B1 EP 0699824 B1 EP0699824 B1 EP 0699824B1 EP 95112351 A EP95112351 A EP 95112351A EP 95112351 A EP95112351 A EP 95112351A EP 0699824 B1 EP0699824 B1 EP 0699824B1
Authority
EP
European Patent Office
Prior art keywords
axial
shaped
retaining element
wedge
blade
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.)
Expired - Lifetime
Application number
EP95112351A
Other languages
German (de)
English (en)
Other versions
EP0699824A1 (fr
Inventor
Günter Schmidt
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.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0699824A1 publication Critical patent/EP0699824A1/fr
Application granted granted Critical
Publication of EP0699824B1 publication Critical patent/EP0699824B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/662—Balancing of rotors

Definitions

  • the invention relates to a device for blade fixing and to eliminate rotor imbalances in case of axial flow Compressors or turbines of gas turbine engines according to the generic term of claim 1.
  • a device is from DE-PS 4,300,773 known.
  • the known case deals with the simultaneous one axial securing of the blades and filler pieces a locking plate, the filler pieces radially below the Lock washer in the axial gap between the foot end and groove base axially are set.
  • a filler is required for each axial groove, where appropriate, one or more filler pieces if necessary in one Filler piece exchangeable with a specifically balanced balancing mass are.
  • Rivet locks already proposed for the rotor blades on the impeller are also affected by the aforementioned problem. They have furthermore the disadvantage of a high assembly and disassembly effort. In addition there is a risk of local damage to the blade feet and the Wheel disc, especially when loosening the rivet. Such are also Riveting often with structural changes in particular linked to the wheel disc or on the axial grooves, which in turn causes problems with regard to the component strength of the wheel disc, which is extremely heavily loaded on the radially outer circumference.
  • the invention has for its object a device according to the Specify the above-mentioned and known type that when assembled Bucket ensures that the blades fit practically without play on the wheel disc with a simple and easy-to-install design and at the same time the simplest possible removal of disc or. Rotor unbalance enabled.
  • the task is with the characteristics of the labeling part of claim 1 according to the invention.
  • each blade is free of play with its foot-side contact or support surfaces against corresponding support surfaces the axial groove in the wheel rim of the wheel disc concerned. All blades are practically in one uniform static support and installation condition, so that a possibly unbalance or residual unbalance still present on the disc is clearly definable and compensable. If there is a disc imbalance is available, the relevant weight-specifically matched Balancing mass reliable against the fuse element in of the relevant recess on the blade root. By comparison simple assembly and disassembly options are the Blades and the securing element in the axial direction on the Wheel disc secured.
  • the radial gap height can at least in the direction of a wheel rim or. Be so large that the balancing mass initially over the a larger lateral gap opening into the recess can be used on the blade root and the securing element is wedged thereon becomes.
  • the wedge-like jamming can at least in the sense the features of claim 2 or 3 are performed.
  • An intense one and along the blade root as large and uniform as possible Surface pressure can be achieved in particular according to claim 4, after which the axial gap and the securing element with respect to the axially changing gap height course essentially wedge-shaped on each other are coordinated.
  • each one-sided bevel relative to the axially parallel end face of the Be won for good reason.
  • the axial groove, and thus the wheel disc thus do not need to be structurally related to the implementation of the invention to be changed.
  • the securing element can be comparatively weight easily be manufactured.
  • the securing element provides good support and holding properties according to claim 7 and 8.
  • the support sections can a certain elastic deformation can be attributed to an axial as possible Surface pressure prevailing uniformly on the blade root with regard to to ensure shape tolerances.
  • an axial gap S left Between the foot end E, radially inside, and the groove base G of the axial groove 3 is an axial gap S left, the installation height - from the left according to Fig. 1 seen to the right - increasingly uniformly widening approximately wedge-shaped is trained.
  • the wedge-shaped course of the axial gap S in the present case is e.g. by the angle of inclination ⁇ characterized, namely between the groove base parallel to the disk G and the tapered, radially inner end E of the Blade base 2.
  • the beveled end E of the blade base 2 can e.g. be provided by a bevel cut.
  • the securing element 6 bridges with a radially outer wall section a recess contained in the blade root 2, open on one side 7, to accommodate a specific weight-balanced balancing mass 8 is formed.
  • the securing element 6 is at least one sectionally wedge-shaped deformed sheet metal strips.
  • This Securing element can e.g. manufactured by punching or embossing processes will. The latter applies in particular to the creation of a Sheet metal bead 9, which essentially provides the required wedge shape, so that the axial gap S and the securing element 6 with respect to the gap height curve that changes axially on one side is essentially wedge-shaped are coordinated.
  • the securing element 6 sits with the side straight-walled sections on groove base G. From the straight-walled Starting sections, the securing element 6 is Sheet metal bead 9 deformed, so that - according to FIG. 2 - one opposite the groove base G partly trapezoidal cross-section open on one side is formed on the locally available end contour of the axial groove 3 is designed to match the axial gap S.
  • the securing element 6 can have end regions on both sides of the axial gap S have support sections St.
  • the support sections St between which the sheet metal bead 9 extends from bent at an angle to the straight-walled sections Sheet metal sections are provided.
  • the invention can also be carried out without said support sections St, namely in combination of the wedge-shaped bead 9 with the tab-like bendable end parts E1, E2.
  • the securing element 6 ' has one on the radially inner one Axial groove contour rounded, coordinated contour.
  • the securing element 6 is the self-contained hollow profile contour of the securing element 6 "e.g. seen from top to bottom, wedge-shaped tapered to the radially inner axial groove contour at gap S. designed.
  • FIGS. 1 to 4 in a modification of FIGS. 1 to 4 can according to the invention in the fuse elements at least to provide the respective wedge shape solid profiles are used at the axial gap S, e.g. by Rolling, forging or pressing processes are produced.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Installation pour bloquer les aubes et pour éliminer les balourds de rotor dans les compresseurs ou turbines à flux axial de turbines à gaz,
    selon lequel les aubes (1) sont accrochées par des talons (2) profilés en forme de dent dans des rainures axiales (3), évidés de manière correspondante dans le disque de rotor (5), et chaque fois entre une extrémité de talon et le fond de la rainure axiale (3), on laisse un intervalle axial (S) recevant un élément de blocage (6) qui est replié aux deux extrémités (E1, E2) dépassant de l'intervalle, vers les faces frontales opposées du disque de rotor (5) et d'un pied de rotor (2),
    caractérisée en ce que
    chaque élément de blocage (6) est coincé dans un intervalle axial (S) entre le fond (G) de la rainure et le talon de l'aube, à la manière d'un coin et déborde ainsi d'une cavité (7) réalisée dans le talon (2) de l'aube pour recevoir une masse d'équilibrage (8).
  2. Installation selon la revendication 1,
    caractérisée en ce que
    l'élément de blocage (6) est en forme de coin, dont la section va en s'augmentant dans la direction axiale.
  3. Installation selon les revendications 1 et 2,
    caractérisée en ce que
    l'intervalle axial (S) est réalisé avec une hauteur de construction, augmentant en continu dans sa direction axiale par rapport à des surfaces d'extrémité inclinées l'une vers l'autre d'un pied de rotor (2) et le fond de la rainure (G) est réalisé en forme de coin.
  4. Installation selon une ou plusieurs des revendications 1 à 3,
    caractérisée en ce que
    l'intervalle axial (S) et l'élément de blocage (6) sont formés essentiellement en forme de coin, formes adaptées l'une à l'autre pour le tracé en hauteur de l'intervalle qui varie axialement d'un côté.
  5. Installation selon la revendication 3,
    caractérisée en ce que
    le tracé en forme de coin de l'intervalle axial (S) est réalisé chaque fois entre une surface d'extrémité d'axe parallèle au fond (G) de la rainure et la surface d'extrémité (E), en biais par rapport à celle-ci et appartenant à un talon (2).
  6. Installation selon l'une ou plusieurs des revendications 1 à 5,
    caractérisée en ce que
    l'élément de blocage (6) est réalisé à partir d'une bande de tôle mise en forme de coin par segments.
  7. Installation selon la revendication 6,
    caractérisée en ce que
    l'élément de blocage (6) est réalisé principalement avec une forme de coin par une moulure (9) qui, partant des segments de la paroi extérieure, est formée en coin en direction d'une extrémité de talon (E), l'élément de blocage (6) s'appuyant avec les segments de paroi droite contre le fond de la rainure.
  8. Installation selon les revendications 6 ou 7,
    caractérisée en ce que
    l'élément de blocage (6) est muni dans la zone d'extrémité des deux côtés de l'intervalle axial (S), en concordance avec la hauteur de montage localement indispensable, et présentant des segments d'appui (St) pour le talon (2) de l'aube, qui se poursuivent chacun par des extrémités repliées en forme de patte grâce à des intervalles de séparation (E1, E2) pour l'élément de blocage (6).
  9. Installation selon une ou plusieurs des revendications 1 à 6,
    caractérisée en ce que
    l'élément de blocage (6, 6', 6'') présente pour la plus grande partie respective de l'extension longitudinale dans l'intervalle axial (S), comme profil creux ou comme profil plein pour le contour localement prédéterminé de la rainure axiale (3) en fonction du jeu axial (S).
EP95112351A 1994-08-29 1995-08-05 Dispositif pour le verrouillage d'aubes de rotor et pour l'élimination du déséquilibre du rotor de compresseurs ou turbines de turbines à gaz Expired - Lifetime EP0699824B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4430636A DE4430636C2 (de) 1994-08-29 1994-08-29 Einrichtung zur Laufschaufelfixierung und zur Beseitigung von Rotorunwuchten bei axial durchströmten Verdichtern oder Turbinen von Gasturbinentriebwerken
DE4430636 1994-08-29

Publications (2)

Publication Number Publication Date
EP0699824A1 EP0699824A1 (fr) 1996-03-06
EP0699824B1 true EP0699824B1 (fr) 1998-01-21

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP95112351A Expired - Lifetime EP0699824B1 (fr) 1994-08-29 1995-08-05 Dispositif pour le verrouillage d'aubes de rotor et pour l'élimination du déséquilibre du rotor de compresseurs ou turbines de turbines à gaz

Country Status (3)

Country Link
US (1) US5584659A (fr)
EP (1) EP0699824B1 (fr)
DE (2) DE4430636C2 (fr)

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US6984241B2 (en) * 1996-09-13 2006-01-10 Tendon Technology, Ltd. Apparatus and methods for tendon or ligament repair
DE19823157A1 (de) * 1998-05-23 1999-11-25 Asea Brown Boveri Einrichtung zur Befestigung der Laufschaufeln axial durchströmter Turbomaschinen
ITMI991210A1 (it) * 1999-05-31 2000-12-01 Nuovo Pignone Spa Dispositivo di fissaggio per palette per turbine a gas
DE19945581B4 (de) * 1999-09-23 2014-04-03 Alstom Technology Ltd. Turbomaschine
US6619924B2 (en) 2001-09-13 2003-09-16 General Electric Company Method and system for replacing a compressor blade
US6908279B2 (en) * 2003-11-25 2005-06-21 General Electric Company Method of installing stationary blades of a turbine and turbine structure having a radial loading pin
JP2005273646A (ja) * 2004-02-25 2005-10-06 Mitsubishi Heavy Ind Ltd 動翼体及びこの動翼体を有する回転機械
EP1643082A1 (fr) * 2004-09-30 2006-04-05 Siemens Aktiengesellschaft Fixation d'aubes de turbine
FR2918129B1 (fr) * 2007-06-26 2009-10-30 Snecma Sa Perfectionnement a une cale intercalee entre un pied d'aube et le fond de l'alveole du disque dans laquelle il est monte
KR200445274Y1 (ko) 2007-07-30 2009-07-14 두산중공업(주) 터빈의 핑거형 버켓의 고정장치
US7862296B2 (en) * 2007-08-24 2011-01-04 Siemens Energy, Inc. Turbine vane securing mechanism
US20090060746A1 (en) * 2007-08-30 2009-03-05 Honeywell International, Inc. Blade retaining clip
US8182229B2 (en) * 2008-01-14 2012-05-22 General Electric Company Methods and apparatus to repair a rotor disk for a gas turbine
ES2620424T3 (es) 2010-11-15 2017-06-28 Mtu Aero Engines Gmbh Turbomáquina con unos medios de sujeción para la sujeción axial de una raíz de álabe
DE102010053123A1 (de) 2010-12-01 2012-06-06 Mtu Aero Engines Gmbh Verfahren zur Herstellung eines Wuchtgewichtes, Wuchtgewicht und Rotorgrundkörper
IT1403416B1 (it) * 2010-12-21 2013-10-17 Avio Spa Rotore palettato di una turbina a gas per motori aeronautici e metodo per il raffreddamento di detto rotore palettato
FR2975428B1 (fr) * 2011-05-17 2015-11-20 Snecma Roue a aubes de turbomachine
GB2491121B (en) * 2011-05-23 2014-10-01 Rolls Royce Plc Balancing of rotatable components
US8764402B2 (en) * 2011-06-09 2014-07-01 General Electric Company Turbomachine blade locking system
CN102943695B (zh) * 2012-08-30 2014-11-26 哈尔滨汽轮机厂有限责任公司 一种菌型叶根叶片成圈的平衡方法
US20140199172A1 (en) * 2013-01-11 2014-07-17 General Electric Company Turbomachine and method of handling turbomachine components
EP2789800B1 (fr) * 2013-04-09 2017-06-14 MTU Aero Engines AG Assortiment des tôles de serrage, moteur à turbine à gaz et procédé de montage associés
US9624775B2 (en) 2014-05-30 2017-04-18 Rolls-Royce Plc Developments in or relating to rotor balancing
US10436224B2 (en) 2016-04-01 2019-10-08 General Electric Company Method and apparatus for balancing a rotor
US11339674B2 (en) 2018-08-14 2022-05-24 Rolls-Royce North American Technologies Inc. Blade retainer for gas turbine engine
KR102261099B1 (ko) * 2020-01-31 2021-06-04 두산중공업 주식회사 블레이드 결합구조 및 이를 포함하는 터빈장치
KR102454379B1 (ko) * 2020-09-08 2022-10-14 두산에너빌리티 주식회사 로터 및 이를 포함하는 터보머신

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FR2535794A1 (fr) * 1982-11-08 1984-05-11 Snecma Dispositif de retenue axiale et radiale d'aubes de soufflante
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Also Published As

Publication number Publication date
DE4430636C2 (de) 1997-01-23
US5584659A (en) 1996-12-17
EP0699824A1 (fr) 1996-03-06
DE4430636A1 (de) 1996-03-14
DE59501325D1 (de) 1998-02-26

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