EP2238314A1 - Dispositif de fixation axiale d aubes mobiles dans le rotor d une turbine à gaz - Google Patents

Dispositif de fixation axiale d aubes mobiles dans le rotor d une turbine à gaz

Info

Publication number
EP2238314A1
EP2238314A1 EP09707238A EP09707238A EP2238314A1 EP 2238314 A1 EP2238314 A1 EP 2238314A1 EP 09707238 A EP09707238 A EP 09707238A EP 09707238 A EP09707238 A EP 09707238A EP 2238314 A1 EP2238314 A1 EP 2238314A1
Authority
EP
European Patent Office
Prior art keywords
metal strip
rotor
sealing element
arrangement
geometry
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.)
Granted
Application number
EP09707238A
Other languages
German (de)
English (en)
Other versions
EP2238314B1 (fr
Inventor
Reimund Schlosser
Adam Zimmermann
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
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP09707238A priority Critical patent/EP2238314B1/fr
Publication of EP2238314A1 publication Critical patent/EP2238314A1/fr
Application granted granted Critical
Publication of EP2238314B1 publication Critical patent/EP2238314B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/505—Shape memory behaviour

Definitions

  • the invention relates to an arrangement for axial securing of rotor blades in a rotor of a gas turbine according to the features of the preamble of claim 1.
  • the assembly 10 comprises a shaft collar 21 formed by a rotor disk 19, which shaft collar 21 is part of the rotor 23 of a gas turbine.
  • the blade feet 54 of the respective rotor 14 are inserted, which are secured against displacement along the groove 12.
  • sealing elements 16 are provided, which cover the end-side opening of the respective groove 12 at least partially and the assembled form a frontal sealing ring.
  • an annular groove 20 is provided in which sit in the substantially rectangular sealing elements 16.
  • the sealing elements 16 lie in grooves 24 which are provided on the undersides 26 of the platforms 28 of the rotor 14.
  • at least one of the sealing elements 16 comprises a metal strip 30 secured thereto with a leg 64, which leg 64 either on the rotor blade 14 or its platforms 28 (FIG. 1) or on the rotor disk 19 (FIG 2) itself positively abuts.
  • the sealing elements 16 also have the task of guiding a cooling air flow along the end face of the rotor disk 19.
  • the integrity of the sealing element and the metal strip can be adversely affected by the unintentional plastic deformation. Another disadvantage is the slight springing back of the metal strip after the bending process due to its elasticity.
  • the object of the invention is therefore to provide an arrangement for axial securing of blades in a rotor of a gas turbine, in which the sealing elements are particularly reliable mountable and disassembled.
  • the material of the metal strip is a shape memory alloy.
  • the shape memory alloy as the material for the metal strip, both the assembly and the functional reliability of the metal strip can be increased.
  • the metal strip rests without play or under a bias on the sealing element. As a result, unintentional wandering of the sealing element in the circumferential direction can be reliably avoided.
  • the safe avoidance is due to the fact that now no gap between the sealing element and
  • Sheet metal strip is present and so the metal strip from the adjacent machine component - ie the platform of the blade or the cam of the rotor disc - is securely blocked.
  • a gap between the sealing element and the metal strip could at worst - depending on its size - a relative movement between the sealing element and machine component occur, in which the machine component would insert into the gap.
  • the latter is prevented with the invention, so that a particularly reliable securing of the sealing element against a circumferential displacement can be achieved.
  • Made of shape memory alloys components are characterized by the fact that they can permanently change their outer shape while maintaining high strength by the action of temperature. These components can therefore have a first geometry ie shape, contour and a second geometry.
  • the components can be re-deformed from the second geometry to the first geometry solely by a heat treatment.
  • the geometry which the metal strip assumes after heat treatment is also referred to below as functional geometry.
  • the second geometry can be almost arbitrary and can be specified during manufacture of the component.
  • the sheet metal strip is produced in such a form as it should later secure the position of the sealing elements when installed.
  • This preliminary shape corresponds to the first geometry.
  • Even before installation of the sheet metal strip is then deformed in a suitable manner in the second geometry, so that it can be attached to the sealing element.
  • the sealing element is mounted on the shaft collar.
  • a temperature treatment whereby the metal strip tries to reform into its first geometry.
  • the temperature treatment can either be done before starting the gas turbine by heating by means of an external heat source. Or the first operation of the gas turbine, in which high temperatures occur, can trigger the deformation of the sheet metal strip. It is also possible that both temperature treatments are used to achieve a final deformation of the sheet metal strip. chen.
  • the metal strip After the temperature treatment, the metal strip has assumed its functional geometry and secures the sealing element both against loss from a shift in the circumferential direction. If the functional geometry and the first geometry deviate from each other, a prestressed fastening of the sealing element resp. Sheet metal strips are achieved.
  • the material has a one-way effect. This means that a single change in shape takes place when the metal strip, which has previously been deformed pseudoplastic in the martensitic state, is heated up. Cooling after heating up no longer causes any change in shape.
  • the metal strip remains in its first geometry or functional geometry.
  • the embodiments known from the prior art can be developed in this way.
  • the bias generated by the metal strip according to the invention then acts namely between the blade and sealing element, that the seated in the groove outer end of the sealing element due to the bias against a side wall of the groove, which is arranged in the bottom of the platform of the blade can be pressed flat.
  • the flat pressing leads to a particularly dense concern of the sealing element in the outer groove.
  • 1, 2 show two arrangements of axial securing of moving blades.
  • FIGS. 3 to 7 show further different constructions of the fastening of the sealing element known from the prior art with a sheet metal strip according to the invention made of a shape memory alloy in a purely schematic representation.
  • the sheet metal strip 30 shown there may be according to the invention of a shape memory alloy.
  • the geometry of the sheet metal strip 30 shown in FIG. 1 and FIG. 2 represents the first geometry.
  • this must be deformed beforehand into the second geometry, so that the sealing element 16 can be inserted into an annular groove 20.
  • After assembly of the sealing element 16 can then deform the metal strip 30 by a heat treatment in the functional geometry and produce the positive connection between itself and the platforms 28 (FIG 1) or the rotor disk 19 (FIG 2). If the functional geometry corresponds to the first geometry, the sheet-metal strip 30 and thus the sealing element 16 sits unrestrained or with play on the rotor 23.
  • embodiment of the inventively designed metal strip 30, which has a functional geometry that differs at least slightly from the first geometry, so as to a bias between blade 14, respectively.
  • a preload is achieved when the first geometry of the sheet metal strip 30 is chosen so that it can not be achieved despite the heat treatment due to a mechanical blockage by other machine components.
  • the metal strip 30 remains in the functional geometry and biased against the blocking machine component.
  • the blocking machine component may be formed by the groove 24, the annular groove 20, the platform 28 of the blade 14 or by the shaft collar 21.
  • the sealing element 16 can be sealed radially outwardly against the side wall of the groove 24 located in the underside 26 of the platform 28 and / or radially inwardly against a side wall of the annular groove 20 be pressed, whereby a leakage of the sealing element guided cooling air can be reduced and possibly even avoided.
  • FIGS. 3 to 7 different configurations with different metal strips 30 are shown in FIGS. 3 to 7. All metal strips 30 shown therein have in common that they are suitably attached to a sealing element 16 are attached.
  • FIGS. 3-7 contains three partial representations which have either the suffix a, b or c.
  • the partial representations according to suffix a show the sheet-metal strip 30 according to the invention in its original geometry, ie first geometry, wherein the sheet-metal strip 30 is fastened to the sealing element 16 with suitable means but not further illustrated.
  • the metal strips 30 are transferred by a pseudoplastic deformation in the second geometry.
  • the partial representations according to suffix b show the respective metal strip 30 having the second geometry in the installation or assembly situation.
  • the metal strips 30 are each shown in their functional geometry, which you reach after a single successful heating and which they then permanently maintained with high strength.
  • closure element 40 is shown, with which the metal strip 30 can be brought into positive engagement.
  • the sheet metal strip 30 is merely subjected to the heat treatment, so that it tries to get out of the second geometry into the first geometry.
  • the closure element 40 can have any desired configuration and, in FIGS. 3 to 7, represents in an abstract manner either the pocket arranged on the shaft collar 21 or the tapered recess between the platforms 26 of adjacent rotor blades 14.
  • the sheet-metal strip 30 which is made of a shape-memory alloy and secured against circumferential displacement in the circumferential direction, has a first geometry which is L-shaped in cross-section.
  • the sheet metal strip comprises two legs 62, 64.
  • the leg 62 of the sheet metal strip 30 may be soldered to the sealing element 16.
  • the other leg 64 then serves for the positive fastening of the sealing element 16 and des Sheet metal strip 30 in a recess 38.
  • the recess 38 may also alternatively, as shown in FIG 1, tapered between the platforms 28 of two immediately adjacent blades 14 may be arranged.
  • the recess 38 can be formed by two teeth 68 arranged on the rotor disk 19 (FIG. 2).
  • FIG. 4 An alternative embodiment of the sheet-metal strip 30 to FIG. 3 is shown in FIG. 4.
  • the sheet-metal strip 30 in the first geometry according to FIGS. 4a, 4c comprises a bead-like end 65, which can be converted into a second geometry by a pseudoplastic deformation.
  • the end 65 is plate-shaped, which allows the assembly of the sealing element in the arrangement.
  • FIG. 3 and FIG. 4 have in common that the functional geometry and the second geometry coincide and accordingly the sealing element 16 can be fastened with clearance in the recess 38.
  • FIG. 5 and FIG. 6 show embodiments of a closure element 40 and of a sheet-metal strip 30, in which the geometry of the closure element 40 and the first geometry of the sheet-metal strip are selected so that a biasing force of sheet-metal strips 30 can act on the closure element 40.
  • a biasing force By means of the biasing force is a play-free attachment of metal strips 30 respectively.
  • Sealing element 16 is achieved on the closure element 40.
  • the function geometry differs from the first geometry.
  • the achievement of the first geometry of the shape memory alloy existing metal strip 30 during the heat treatment is prevented due to the selected shape of the closure member 40 by the complete recovery of the metal strip 30 is at least partially blocked by the closure member 40.
  • a play-free and prestressed attachment of sealing element 16 and closure element 40 can be achieved. Consequently differentiates the embodiment according to FIG 5 of FIG 3 only in the form and contour of the closure element.
  • FIG. 7 shows a further developed construction according to FIG. 3.
  • the "movable" second leg 64 is another
  • the element 60 may be designed as a pin-shaped. After the heat treatment, the element 60 is in a recess 70, whereby the metal strip 30 respectively. the sealing element 16 is positively locked against movement relative to the closure element 40.
  • the invention provides an arrangement for the axial securing of rotor blades of a gas turbine, which comprises a sealing element arranged on the end face of the rotor, which can be fastened particularly reliably by means of a sheet metal strip consisting of a shape memory alloy.

Landscapes

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

Abstract

La présente invention concerne un dispositif (10) de fixation axiale d'aubes mobiles (14) d'un rotor (23) de turbine à gaz. Le dispositif comprend un élément d'étanchéité (16) disposé sur la surface avant du rotor (23), l'élément d'étanchéité pouvant être fixé de manière particulièrement fiable sur le rotor (23) au moyen d'une bande de tôle fabriquée dans un alliage à mémoire de forme.
EP09707238A 2008-02-08 2009-01-14 Dispositif de fixation axiale d aubes mobiles dans le rotor d une turbine à gaz Not-in-force EP2238314B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09707238A EP2238314B1 (fr) 2008-02-08 2009-01-14 Dispositif de fixation axiale d aubes mobiles dans le rotor d une turbine à gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08002388A EP2088287A1 (fr) 2008-02-08 2008-02-08 Dispositif de sécurité axiale sur aubes mobiles d'un rotor d'une turbine à gaz
EP09707238A EP2238314B1 (fr) 2008-02-08 2009-01-14 Dispositif de fixation axiale d aubes mobiles dans le rotor d une turbine à gaz
PCT/EP2009/050363 WO2009098111A1 (fr) 2008-02-08 2009-01-14 Dispositif de fixation axiale d’aubes mobiles dans le rotor d’une turbine à gaz

Publications (2)

Publication Number Publication Date
EP2238314A1 true EP2238314A1 (fr) 2010-10-13
EP2238314B1 EP2238314B1 (fr) 2012-05-23

Family

ID=39800566

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08002388A Withdrawn EP2088287A1 (fr) 2008-02-08 2008-02-08 Dispositif de sécurité axiale sur aubes mobiles d'un rotor d'une turbine à gaz
EP09707238A Not-in-force EP2238314B1 (fr) 2008-02-08 2009-01-14 Dispositif de fixation axiale d aubes mobiles dans le rotor d une turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08002388A Withdrawn EP2088287A1 (fr) 2008-02-08 2008-02-08 Dispositif de sécurité axiale sur aubes mobiles d'un rotor d'une turbine à gaz

Country Status (5)

Country Link
US (1) US8535012B2 (fr)
EP (2) EP2088287A1 (fr)
JP (1) JP5002063B2 (fr)
CN (1) CN101939509B (fr)
WO (1) WO2009098111A1 (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2372095A1 (fr) * 2010-03-26 2011-10-05 Siemens Aktiengesellschaft Procédé et dispositif de fixation d'une aube à un rotor par un élément à mémoire de forme
CH704526A1 (de) 2011-02-28 2012-08-31 Alstom Technology Ltd Dichtungsanordnung für eine thermische Maschine.
US9017013B2 (en) 2012-02-07 2015-04-28 Siemens Aktiengesellschaft Gas turbine engine with improved cooling between turbine rotor disk elements
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
EP2860350A1 (fr) * 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Aube de turbine et turbine à gaz
EP2896792A1 (fr) * 2014-01-21 2015-07-22 Alstom Technology Ltd Système de fixation mécanique pour composants fixes ou rotatifs
CN106678137A (zh) * 2015-11-06 2017-05-17 宏碁股份有限公司 卡合机构及其组装方法
GB2587281B (en) 2018-07-19 2022-11-23 Halliburton Energy Services Inc Techniques to improve wireless communications for in-situ wellbore devices
NO20210649A1 (en) 2018-12-26 2021-05-20 Halliburton Energy Services Inc Method and system for creating metal-to-metal seal
CN112302766B (zh) * 2020-10-15 2022-02-25 羽源洋(宁波)科技有限公司 具有尾气能量回收功能的三元催化装置
CN113217533A (zh) * 2021-05-18 2021-08-06 人本股份有限公司 新型密封球轴承
CN113494522A (zh) * 2021-07-20 2021-10-12 人本股份有限公司 自行消除安装倾角的滚动轴承
CN113653737B (zh) * 2021-07-28 2022-10-21 人本股份有限公司 防密封圈脱落式轴承

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US2641443A (en) * 1951-03-17 1953-06-09 A V Roe Canada Ltd Rotor blade locking
JPS61129405A (ja) 1984-11-28 1986-06-17 Hitachi Ltd タ−ビン動翼固定方法
DE3629910A1 (de) * 1986-09-03 1988-03-17 Mtu Muenchen Gmbh Metallisches hohlbauteil mit einem metallischen einsatz, insbesondere turbinenschaufel mit kuehleinsatz
JPS6469702A (en) * 1987-09-09 1989-03-15 Hitachi Ltd Fixation of movable blade of axial flow rotary machine
FR2715968B1 (fr) * 1994-02-10 1996-03-29 Snecma Rotor à plates-formes rapportées entre les aubes.
US5518369A (en) * 1994-12-15 1996-05-21 Pratt & Whitney Canada Inc. Gas turbine blade retention
DE10108956A1 (de) * 2001-02-23 2002-09-12 Siemens Ag Montageelement zum Verbinden zweier Gegenstände, insbesondere zweier Geräteteile
DE102004030965A1 (de) * 2004-06-26 2006-02-09 Fag Kugelfischer Ag & Co. Ohg Sicherungsscheibe, insbesondere zum Sichern einer Wellenmutter auf einem Wellengewinde gegen selbsttätiges Losdrehen
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
JP2007120460A (ja) 2005-10-31 2007-05-17 Toshiba Corp タービン翼の固定・着脱方法および装置

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Also Published As

Publication number Publication date
JP2011514467A (ja) 2011-05-06
US20110020125A1 (en) 2011-01-27
EP2238314B1 (fr) 2012-05-23
CN101939509A (zh) 2011-01-05
CN101939509B (zh) 2013-12-11
WO2009098111A1 (fr) 2009-08-13
JP5002063B2 (ja) 2012-08-15
US8535012B2 (en) 2013-09-17
EP2088287A1 (fr) 2009-08-12

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