+

EP1266129A1 - Fixation d'aubes sur une turbomachine - Google Patents

Fixation d'aubes sur une turbomachine

Info

Publication number
EP1266129A1
EP1266129A1 EP01914106A EP01914106A EP1266129A1 EP 1266129 A1 EP1266129 A1 EP 1266129A1 EP 01914106 A EP01914106 A EP 01914106A EP 01914106 A EP01914106 A EP 01914106A EP 1266129 A1 EP1266129 A1 EP 1266129A1
Authority
EP
European Patent Office
Prior art keywords
blades
blade
rotor
stator
cover plate
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
EP01914106A
Other languages
German (de)
English (en)
Other versions
EP1266129B1 (fr
Inventor
Eduard GÖTZFRIED
Helmut Wendler
Heinz May
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Alstom Schweiz 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 Alstom Technology AG, Alstom Schweiz AG filed Critical Alstom Technology AG
Publication of EP1266129A1 publication Critical patent/EP1266129A1/fr
Application granted granted Critical
Publication of EP1266129B1 publication Critical patent/EP1266129B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to fastening or anchoring blades of a turbomachine by means of blade feet on the rotor or stator of the turbomachine.
  • Such blade attachments are generally found in the rotors of compressors or thermal turbomachines. Many of them are known from the prior art.
  • the blades are inserted into a groove on the rotor with the blade root.
  • the blade root is used to transmit force and torque to the rotor.
  • Cover plates are often attached to the tip of the airfoil or support wings within the airfoil to dampen vibrations. This is described, for example, in German patent specification DE 1, 159.965.
  • Austrian patent specification AT 254.227 also discloses a cover plate of a turbine or compressor blade ring in which the cover plates are pressed against one another by the action of a force.
  • the arrangement leads to an elastic prestressing of the airfoil. This torsional preload of the airfoil takes place between the cover plate and the airfoil, but this leads to an additional load on the airfoil and the rotor. Since the resulting forces not only have to be absorbed by the airfoil, but also by the airfoil and the rotor, they are designed to be correspondingly more solid.
  • Spacers are often arranged between the individual blade feet of the turbine blades, which take up the forces and are also intended to dampen vibrations. This is known for example from the patents US 2,916,257 or also from US 3,734,645. Another blade attachment is also known from European laid-open publication EP-A1 -520,258. To limit circumferential forces due to thermal expansion, longitudinal webs are provided between the blades.
  • a disadvantage of such prior art is that the load is generally transferred to the rotor via the blade root. This applies in particular to the torsional moments mentioned above.
  • the more solid design of the rotor and the blade roots has negative effects in particular on the width of the blade and the blade root and the wheel disc and thus also on the entire length of the rotor. Due to the higher foot load, cheaper foot designs (e.g. hammer head foot, rider blade foot) had to be dispensed with and instead more stable, expensive foot shapes (such as plug-in foot) had to be used.
  • the aim of the invention is to avoid the disadvantages mentioned.
  • the invention is based on the object of providing a fastening for blades of a flow machine on a rotor or stator, with which the torsional moments can be absorbed by the blade root or the base plate of the blade, while at the same time Relief of the rotor / stator and the blade root
  • the total length of the rotor / stator should be shortened or, for the same length, the number of rows of blades should be increased and / or the use of inexpensive foot connections should be possible
  • the object is achieved by fastening blades in accordance with the preamble of claim 1 in that, after the installation of all the blades, the blades on the rotor or stator on the base plate and / or on the blade base adjoin one another in whole or in part without play or with a pretension thus mutually support against torsional moments, the torsional moments acting on the base plates and / or on the blade roots being opposite to the torsional moments acting on the cover plate or on the support wing
  • An advantage of this embodiment is that torsional moments are no longer or only marginally absorbed by the rotor, but rather by the adjoining base plates and / or blade roots, since rotation of these two components is prevented.
  • This measure enables the blade base and also the rotor (or Stator) can be dimensioned correspondingly smaller, since no larger forces have to be absorbed at the contact surface of the rotor (stator) / blade root. Overall, the length of the rotor can therefore be reduced. It is the number of rows of blades with the same length of the rotor (stator) and therefore also to increase the efficiency
  • the base plate and possibly also the blade root have a bevel, which advantageously adjoins a bevel of an adjacent rotor blade and so torsional moments are mutually absorbed at this point.
  • Pj. -J show a turbine blade of a steam turbine with a single prong
  • Blade root and cover plate / support wing Fig. 2 e ⁇ ne turbine blade of a steam turbine with a support plate
  • FIG. 3 shows a plan view of an exemplary embodiment according to the invention with the cover plates of the turbine blades and
  • FIG. 4 shows a section through an exemplary embodiment according to the invention of turbine blades which are in a groove on the rotor or
  • the stator of the turbomachine are arranged, the
  • FIG. 1 shows a blade 1 of a turbomachine, that is to say, for example, a steam turbine or a compressor.
  • the blade 1 which can be a moving blade or a guide blade, consists of a blade root 4, of a blade root 4 adjoining the blade root 4 Base plate 3, from a cover plate 2 or a support wing or a support plate, and from an airfoil 5 located between the base plate 3 and the cover plate 2.
  • the blade base 4 is designed in FIG. 1 as a single-pronged plug-in base 4a. It is used to fasten the blade 1 to the rotor 6 (not shown in FIG. 1) or to a stator. Both the base 3 and the cover plate 2 of the blade 1 are equipped with a bevel 9.
  • the bevel 9 is located on one side of the cover plate 2 or base plate 3, ie the bevel 9 is to be understood with regard to the top view of the two plates 2, 3, as is also evident in FIGS. 3 and 4. It is also possible that a bevel 9 is also attached to the blade root 4.
  • the blade 1 can also be a blade with a multi-pronged plug-in foot.
  • the cover plate 2 can be attached to the airfoil 5 between the blade tip 14 and the base plate 3. This generally applies to all usable blade types.
  • FIG. 4 shows a section through a row of blades, the base plates 3 of the blades ' ⁇ v ' ⁇ 2 ⁇ ⁇ z n being visible in this figure. Again, adjacent foot plates 3 meet directly and without play at the contact points 7. The contact points 7 between adjacent plates 3 are in the region of the bevels 9. In the other part of the foot plates 3, a gap 10 is formed.
  • the torsional moments 12 acting on the foot plates 3 are opposite to the torsional moments 13 shown in FIG Bevels 9 are arranged at a corresponding other end of the respective plate 2, 3. According to the invention, it is also possible to provide a prestress between the individual foot plates 3.
  • the contact point 7 can also refer overall to the adjacent foot plates 3 without a gap 10 forming.
  • the bevels 9, as already shown in FIG. 1, can also relate to areas of the blade root 4. However, this is not shown in more detail in FIG. 4.
  • the blades 1 - ,, 1 2 , 1 3> 1 n support each other. Twisting does not take place, or only to a very small extent, so that the force is absorbed by the rotor blades 1 l F 1 2 , 1 3 , 1 n itself and no longer by the rotor 6 (or the stator) or by the groove 8 Need to become.
  • the load of the rotor 6 is formed by this type of arrangement of the blades 1. ,, 1 2, 1 3, 1 n advantageously reduced. This takes place in the first line through the play-free or prestressed mounting on the base plates 3 and / or on the blade feet 4.
  • the bevel 9 must of course then also be present on the blade base 4 in order to take account of the present effect.
  • the single-pronged plug-in foot which is shown in FIG. 1, is only selected, for example.
  • Various types known per se from the prior art for example a hammer foot or rider foot, can be used as the blade root 4.
  • blade roots 4 can now also be used which previously could not be used or could only be used under difficult conditions. This is possible due to the reduced power transmission from the blade root 4 to the rotor 6 or to the stator. Since the blade roots 4 and also the rotor 6 or the stator can be dimensioned smaller (for example in width), the total length of the rotor 6 can be shortened or, with the same length of the rotor 6 (stator), the efficiency of the turbomachine can be increased by additional rows of blades.

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

Les aubes (1, 11, 12, 13, 13, 1n) d'une turbine ou d'un compresseur sont fixées à l'intérieur d'une rainure (8) prévue dans le rotor (6) ou le stator de la turbine ou du compresseur par l'intermédiaire d'emplantures d'aubes (4), aucun jeu, ni aucune précontrainte n'étant ménagé entre la plaque de base (3) et/ou l'emplanture, les aubes adjacentes (1, 11, 12, 13, 1n) étant ainsi supportées mutuellement vis-à-vis des couples de torsion et non pas, ou seulement de manière négligeable, sur le rotor (6) ou le stator. Ceci est rendu possible, par exemple, au moyen d'un chanfreinage (9).
EP01914106A 2000-03-23 2001-03-22 Fixation d'aubes sur une turbomachine Expired - Lifetime EP1266129B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10014189A DE10014189A1 (de) 2000-03-23 2000-03-23 Befestigung der Beschaufelung einer Strömungsmaschine
DE10014189 2000-03-23
PCT/IB2001/000441 WO2001071165A1 (fr) 2000-03-23 2001-03-22 Fixation d'aubes sur une turbomachine

Publications (2)

Publication Number Publication Date
EP1266129A1 true EP1266129A1 (fr) 2002-12-18
EP1266129B1 EP1266129B1 (fr) 2004-12-22

Family

ID=7635889

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01914106A Expired - Lifetime EP1266129B1 (fr) 2000-03-23 2001-03-22 Fixation d'aubes sur une turbomachine

Country Status (11)

Country Link
US (1) US6830435B2 (fr)
EP (1) EP1266129B1 (fr)
CN (1) CN1313708C (fr)
AU (1) AU3948501A (fr)
CZ (1) CZ298200B6 (fr)
DE (2) DE10014189A1 (fr)
EE (1) EE04689B1 (fr)
PL (1) PL199066B1 (fr)
RU (1) RU2311537C2 (fr)
UA (1) UA73765C2 (fr)
WO (1) WO2001071165A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5839823A (en) * 1996-03-26 1998-11-24 Alliedsignal Inc. Back-coupled illumination system with light recycling

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4673732B2 (ja) * 2005-12-01 2011-04-20 株式会社東芝 タービン動翼および蒸気タービン
FR2903921B1 (fr) * 2006-07-19 2009-06-05 Snecma Sa Procede de fabrication d'un disque aubage monobloc et moule pour la mise en oeuvre du procede
DE112008000140B4 (de) 2007-01-12 2019-08-14 General Electric Technology Gmbh Leitapparat für Turbomaschinen und Herstellungsverfahren
GB0700633D0 (en) * 2007-01-12 2007-02-21 Alstom Technology Ltd Turbomachine
US8262359B2 (en) 2007-01-12 2012-09-11 Alstom Technology Ltd. Diaphragm for turbomachines and method of manufacture
EP1961918A1 (fr) * 2007-02-21 2008-08-27 ABB Turbo Systems AG Roue de turbine
DE102008031780A1 (de) * 2008-07-04 2010-01-07 Man Turbo Ag Laufschaufel und Strömungsmaschine mit Laufschaufel
US8277189B2 (en) * 2009-11-12 2012-10-02 General Electric Company Turbine blade and rotor
US9840917B2 (en) * 2011-12-13 2017-12-12 United Technologies Corporation Stator vane shroud having an offset
RU2530198C1 (ru) * 2013-02-28 2014-10-10 Общество с ограниченной ответственностью "Владимирский инновационно-технологический центр" Способ крепления лопастей к ступице колеса
CN103362565B (zh) * 2013-07-04 2015-01-21 西安交通大学 一种汽轮机叶片阶梯状叶根结构及其与隔叶块配合结构
GB2547273A (en) * 2016-02-15 2017-08-16 Rolls Royce Plc Stator vane
GB201717577D0 (en) * 2017-10-26 2017-12-13 Rolls Royce Plc A casing assembly and method of manufacturing a casing assembly for a gas trubine engine
CN113931872B (zh) * 2021-12-15 2022-03-18 成都中科翼能科技有限公司 一种燃气轮机压气机的双层鼓筒加强型转子结构

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2421890A (en) * 1944-11-27 1947-06-10 Goetaverken Ab Turbine blade
US2916257A (en) * 1953-12-30 1959-12-08 Gen Electric Damping turbine buckets
DE1159965B (de) 1961-08-10 1963-12-27 Bbc Brown Boveri & Cie Einrichtung zur Schwingungsdaempfung an einem Turbinen- oder Verdichter-Schaufelkranz
DE1299004B (de) * 1965-01-19 1969-07-10 Bbc Brown Boveri & Cie Einrichtung zur Schwingungsdaempfung an einem Turbinen-oder Verdichterschaufelkranz
BE634692A (fr) * 1962-07-11 1963-11-18
GB1119617A (en) * 1966-05-17 1968-07-10 Rolls Royce Compressor blade for a gas turbine engine
CH516731A (de) 1969-12-12 1971-12-15 Bbc Sulzer Turbomaschinen Schaufelkranz für Turbomaschinen
GB2072760A (en) * 1980-03-29 1981-10-07 Rolls Royce Shrouded turbine rotor blade
US4815938A (en) * 1987-12-24 1989-03-28 Westinghouse Electric Corp. Shroud gap control for integral shrouded blades
US4878811A (en) * 1988-11-14 1989-11-07 United Technologies Corporation Axial compressor blade assembly
GB2251034B (en) * 1990-12-20 1995-05-17 Rolls Royce Plc Shrouded aerofoils
EP0520258B1 (fr) 1991-06-28 1994-09-14 Asea Brown Boveri Ag Dispositif de fixation d'aubes de rotor
JP3178327B2 (ja) * 1996-01-31 2001-06-18 株式会社日立製作所 蒸気タービン
JP4058906B2 (ja) * 1997-09-05 2008-03-12 株式会社日立製作所 蒸気タービン
US6030178A (en) * 1998-09-14 2000-02-29 General Electric Co. Axial entry dovetail segment for securing a closure bucket to a turbine wheel and methods of installation
DE10108005A1 (de) * 2001-02-20 2002-08-22 Alstom Switzerland Ltd Bindung der Beschaufelung einer Strömungsmaschine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO0171165A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5839823A (en) * 1996-03-26 1998-11-24 Alliedsignal Inc. Back-coupled illumination system with light recycling

Also Published As

Publication number Publication date
CZ20023152A3 (cs) 2003-06-18
EE200200542A (et) 2004-04-15
DE10014189A1 (de) 2001-09-27
WO2001071165A1 (fr) 2001-09-27
EE04689B1 (et) 2006-08-15
CN1313708C (zh) 2007-05-02
CZ298200B6 (cs) 2007-07-18
CN1423725A (zh) 2003-06-11
DE50104883D1 (de) 2005-01-27
UA73765C2 (en) 2005-09-15
EP1266129B1 (fr) 2004-12-22
PL199066B1 (pl) 2008-08-29
PL357310A1 (en) 2004-07-26
RU2311537C2 (ru) 2007-11-27
US6830435B2 (en) 2004-12-14
US20030143077A1 (en) 2003-07-31
AU3948501A (en) 2001-10-03

Similar Documents

Publication Publication Date Title
EP1266129A1 (fr) Fixation d'aubes sur une turbomachine
EP1000243B1 (fr) Raccordement de la pale de rotor d'une eolienne a un moyeu de rotor
EP2867478B1 (fr) Couronne d'aubes pour turbomachine
EP1597477B1 (fr) Procede de montage de pales de rotor
EP2384392B2 (fr) Élément structural refroidi pour turbine à gaz
DE1601565A1 (de) Stuetzkonstruktion zum Befestigen von Turbinen-Laufschaufeln an einem Laeufer
DE10324166B4 (de) Rotorblattanschluss
DE69820293T2 (de) Deckplatte für einen gasturbinenrotor
EP1512838A2 (fr) Rotor pour turbine à vapeur ou à gaz
DE10022244A1 (de) Schaufelanordnung mit Dämpfungselementen
WO2006066686A1 (fr) Eolienne comprenant un dispositif de maintien pour un arbre de rotor
EP0821161A1 (fr) Eolienne
WO2002008575A1 (fr) Dispositif pour fixer un turbocompresseur
DE2832098C2 (de) Anordnung zur Zug- bzw. Längskrafteinleitung bei einem Bauteil in Sandwichbauweise
DE1576955A1 (de) Schnellaufender Laeufer fuer Axial-Turbomaschinen
DE10120532A1 (de) Vorrichtung und Verfahren zur Befestigung einer Laufschaufel längs einer innerhalb eines Rotors einer axial durchströmten Turbomaschine verlaufenden Umfangsnut
DE3522917A1 (de) Lageranordnung fuer turbomaschinen, insbesondere dampfturbinen
CH647301A5 (de) Laeuferrad einer turbine mit daran befestigten laufschaufeln.
DE3544814C2 (fr)
DE2247970A1 (de) Einrichtung zur halterung von laufschaufeln
DE10108005A1 (de) Bindung der Beschaufelung einer Strömungsmaschine
DE2062619B2 (de) Laufschaufelbefestigung für Strömungsmaschinen
DE10150527A1 (de) Stützfuss für einen Turbolader
EP3230559A1 (fr) Ensemble de fermeture pour fermer une couronne d'aubes, support d'aubes associé, turbomachine et procédé d'insertion d'un ensemble de fermeture
WO2005010323A1 (fr) Systeme de fixation des emplantures d'aubes d'une turbomachine

Legal Events

Date Code Title Description
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

17P Request for examination filed

Effective date: 20020907

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR

AX Request for extension of the european patent

Free format text: AL;LT PAYMENT 20020907;LV PAYMENT 20020907;MK;RO PAYMENT 20020907;SI

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ALSTOM TECHNOLOGY LTD

RBV Designated contracting states (corrected)

Designated state(s): DE FR GB IE IT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IE IT

AX Request for extension of the european patent

Extension state: LT LV RO

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: GERMAN

REF Corresponds to:

Ref document number: 50104883

Country of ref document: DE

Date of ref document: 20050127

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20050318

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20050923

ET Fr: translation filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20080320

Year of fee payment: 8

Ref country code: IE

Payment date: 20080321

Year of fee payment: 8

Ref country code: IT

Payment date: 20080326

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20080314

Year of fee payment: 8

Ref country code: DE

Payment date: 20080321

Year of fee payment: 8

LTLA Lt: lapse of european patent or patent extension

Effective date: 20090322

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20090322

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20091130

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090323

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20091001

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090322

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20091123

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090322

点击 这是indexloc提供的php浏览器服务，不要输入任何密码和下载