WO2005010323A1 - Systeme de fixation des emplantures d'aubes d'une turbomachine - Google Patents

Systeme de fixation des emplantures d'aubes d'une turbomachine Download PDF

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Publication number
WO2005010323A1
WO2005010323A1 PCT/EP2004/051579 EP2004051579W WO2005010323A1 WO 2005010323 A1 WO2005010323 A1 WO 2005010323A1 EP 2004051579 W EP2004051579 W EP 2004051579W WO 2005010323 A1 WO2005010323 A1 WO 2005010323A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
blade root
groove
rotor
recess
Prior art date
Application number
PCT/EP2004/051579
Other languages
German (de)
English (en)
Inventor
René Bachofner
Wolfgang Kappis
Original Assignee
Alstom Technology Ltd
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
Priority claimed from DE10345210A external-priority patent/DE10345210A1/de
Application filed by Alstom Technology Ltd filed Critical Alstom Technology Ltd
Publication of WO2005010323A1 publication Critical patent/WO2005010323A1/fr

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
    • 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
    • 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
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers

Definitions

  • the invention relates to a blade root attachment for a turbomachine, preferably for the rotor of a turbomachine, according to the preamble of the independent claim.
  • Turbomachines essentially comprise a stator and a rotor, which are equipped with rows of guide or rotor blades projecting into a flow channel. Depending on the intended use of the turbomachine, a fluid medium is either compressed or relaxed while working through the flow channel.
  • the guide and rotor blades are equipped with a blade root which has a special anchoring contour, which is fir-tree-shaped, hammer-head-shaped, mushroom-shaped or rhomboid.
  • An anchoring groove is then provided on the respective blade carrier, the stator or rotor, which is equipped with a second anchoring contour which is complementary to the anchoring contour of the blade root.
  • the blade root is inserted through an axially open longitudinal end of the anchoring groove.
  • the complementary anchoring contours advise each other and form a positive connection in a pull-out direction perpendicular to the longitudinal direction of the anchoring groove, through which the blade root is securely anchored in the blade carrier.
  • the blade root attachment is subjected to extreme loads during operation of the turbomachine. For example, the forces that occur can lead to plastic deformations in the anchoring contours, which then have to be removed again at great expense as part of reconditioning.
  • the invention is based on the object of providing a means for a blade root attachment of the type mentioned at the outset which prevents the occurrence of axial forces acting on the blade carrier as a result of the blade being “turned”.
  • the basic idea of the invention is to equip the shovel feet and, if present, the feet of the intermediate pieces with at least one recess in such a way that a circumferential recess is formed in the installed state, and that a strand-like securing means is inserted into this circumferential recess, which means that in the operating state absorbs unscrewing forces emanating from the blade feet and thus reduces or completely eliminates the effect of axial forces on the blade carrier, in particular the rotor.
  • the at least one recess is designed as a groove on the underside of the blade root.
  • this groove has a rectangular cross section.
  • the base of the anchoring groove of the blade carrier corresponding to the groove of the blade root, is likewise equipped with at least one groove which forms a common circumferential recess with the groove on the underside of the blade root, into which the strand-like securing means is inserted.
  • the advantages of the invention can be seen, inter alia, in the fact that in a simple and inexpensive manner, the blades and intermediate pieces are “unscrewed” and thus unscrewing forces to be absorbed by the blade carrier. In this way, it can be reliably avoided that the blades have axial forces in the blade carrier.
  • the introduction of the additional recesses in the blade and, if present, spacer feet and, if necessary, in the base of the anchoring tion groove of the blade carrier and the pulling in of the strand-like securing means only require very little additional effort in the manufacture of the blading.
  • Turbomachines that are already in operation can also be equipped with a blade root attachment according to the invention with little effort, in that in connection with an overhaul, for example of the rotor, the feet of the blades and intermediate pieces are simply provided with a recess and, as part of the installation of the blading, the safety cord is installed.
  • a particularly simple and inexpensive variant has been found to be a groove on the underside of the blade root that is open toward the blade carrier.
  • Figure 1 is a plan view of a rotor blading according to the prior art.
  • 2 shows a plan view of a rotor blading according to the invention; 3 shows a sectional illustration of the rotor blading according to the invention along line III-III in FIG. 2; 4 shows a partial cross section of the rotor blading according to the invention; 5 shows a partial cross section of a supplementary embodiment variant of the rotor blading according to the invention.
  • FIG. 1 schematically shows a part of a rotor 1 of a turbomachine with an anchoring groove 2 and a rotor blading arranged in the anchoring groove 2, comprising rotor blades 3 and intermediate pieces 4.
  • the blades 3 and the intermediate pieces 4 are fixed in the anchoring groove 2 by means of their rhombus foot (not shown) and are inclined therein.
  • the rotational movement of the rotor 1 causes the inclined rotor blades 3, 4 fixed in the anchoring groove 2 to rotate in accordance with the direction of rotation 5.
  • This unscrewing produces between the leading contour of the anchoring groove 2 and the moving blade 8, respectively Adapter leg 14 in the contact areas 6 axial forces on the rotor 1.
  • FIG. 2 to 4 schematically show a first embodiment of a blade root fastening according to the invention on a rotor.
  • the rotor blade 3, consisting of the blade 7, the blade root 8 and the platform 9, is arranged in the anchoring groove 2.
  • two grooves are made on the underside of the blade open to the base 11 of the anchoring groove 2 and oriented parallel to the direction of rotation.
  • blade feet 8 and spacer feet 14 are introduced, they form two groove-shaped recesses 10 which run around the underside of the blade root and are open towards the anchoring groove base 11, the cross section of which, in a preferred embodiment, is rectangular.
  • a strand-shaped securing means 12 which is adapted to the cross section of the recess 10, is now inserted into each of these circumferential recesses 10.
  • This securing means 12 is elastic and essentially of a rod or wire-like structure and has, for example, a rectangular cross section. According to the embodiment variant shown here in FIGS. 2-4, the fuse link 12 is not connected to the rotor.
  • the positive connection between the recess 10 and the securing line 12 prevents the blades 3 and spacers 4 fixed in the anchoring groove 2 from being unscrewed.
  • the unscrewing forces 5 that occur during operation of the turbomachine are no longer introduced as an axial force into the contour of the anchoring groove 2, but by the securing means 12 added.
  • the rotor blades 3 and intermediate pieces 4 can thus only turn up to a very small mass, which is caused by the play between the fuse link 12 and the recess 10, but not to such a mass that axial forces are introduced into the rotor 1. This effectively prevents deformation of the rotor and thus an increased tendency to vibrate during operation.
  • Recesses 10 and fuse lines 12 are matched to one another in shape and dimension.
  • the play between the recess 10 and the fuse link 12 is selected so that the fuse link 12 can be inserted into the circumferential recess 10, but the blades 3 and intermediate pieces 4 are prevented by positive engagement from rotating in such a way that they penetrate into the side walls the anchoring groove 2 introduce considerable axial forces.
  • the two circumferential groove-shaped recesses 10 shown only one or more than two can also be realized.
  • the material of the fuse link or strings 12 is selected so that it is the mechanical, thermal and chemical acting during operation Can withstand stresses, especially the forces and temperatures that occur. In this context, it has proven to be advantageous to manufacture the strand-like securing means 12 from St 12TE or from HZLM 600 134.
  • FIG. 4 and 5 each show a partial cross section through the rotor 1, with a plurality of moving blades 3 and intermediate pieces 4 being arranged in the anchoring groove 2.
  • These blades 3 and intermediate pieces 4 are inserted into the circumferential anchoring groove 2 by means of the blade feet 8 and the intermediate piece feet 14, so that only one space 13 remains free after all the blades 3 and intermediate pieces 4 have been inserted.
  • This intermediate space 13 which is finished in a known manner after the completion of the blade root fastening according to the invention, is used to insert the strand-like securing means 12 into the circumferential recess 10.
  • the securing strands 12 are usually dimensioned such that they extend over the entire circumference of the anchoring groove 2, except the space 13, so that no recesses 10 are incorporated in the end piece.
  • the grooves 10 can alternatively also be arranged in the end piece without running the risk that the securing line 12 can move freely since the blades 3 and intermediate pieces 4 begin to open during operation the groove 10 begins to twist relative to the fuse link 12 and thus fixes the fuse link.
  • 5 shows a development of the invention to the effect that the circumferential recess 10 is not limited to the underside of the blade root, but is supplemented in the base 11 of the anchoring groove 2 in a coaxial groove.
  • the strand-like securing means 12 then lies in a recess 10, which encompasses both the rotor 1 and the blade root 8. It goes without saying that, in addition to the described rectangular cross-sectional shapes, other shapes are also available for the design of the circumferential recesses 10, for example circular ones.
  • circumferential recesses 10 are not arranged as a groove on the underside of the blade root 8, but rather entirely within the base material in the form of through holes of any cross-sectional shape.

Landscapes

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

Abstract

L'invention concerne un système de fixation des emplantures d'aubes destiné à une turbomachine, de préférence à un rotor (1) d'une turbomachine. L'objectif de l'invention est d'améliorer un tel système de sorte qu'il présente un moyen empêchant la formation de forces axiales agissant sur le support d'aubes en raison d'un desserrage des aubes. A cet effet, au moins un évidement (10) est ménagé dans les emplantures (8) des aubes et, le cas échéant, dans les emplantures (14) des pièces intermédiaires (4) de façon à former à l'état monté un évidement (10) périphérique dans lequel est inséré un moyen de blocage (12) en forme de barre, ce moyen absorbant les forces de desserrage partant des emplantures (8) des aubes lors du fonctionnement et, par là même, réduisant ou supprimant totalement l'effet de forces axiales agissant sur le support d'aubes, en particulier sur le rotor (1).
PCT/EP2004/051579 2003-07-26 2004-07-22 Systeme de fixation des emplantures d'aubes d'une turbomachine WO2005010323A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE10334157.9 2003-07-26
DE10334157 2003-07-26
DE10345210A DE10345210A1 (de) 2003-09-29 2003-09-29 Schaufelfussbefestigung für eine Turbomaschine
DE10345210.9 2003-09-29

Publications (1)

Publication Number Publication Date
WO2005010323A1 true WO2005010323A1 (fr) 2005-02-03

Family

ID=34105479

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2004/051579 WO2005010323A1 (fr) 2003-07-26 2004-07-22 Systeme de fixation des emplantures d'aubes d'une turbomachine

Country Status (1)

Country Link
WO (1) WO2005010323A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2562356A1 (fr) * 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Agencement de pales
DE102013223607A1 (de) * 2013-11-19 2015-05-21 MTU Aero Engines AG Rotor einer Strömungsmaschine
EP2918784A1 (fr) * 2014-03-13 2015-09-16 Siemens Aktiengesellschaft Pied d'aube pour une aube de turbine
JP2016519256A (ja) * 2013-05-23 2016-06-30 ゼネラル・エレクトリック・カンパニイ 複合材圧縮機ブレード及びその組立方法

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1606029A (en) * 1926-11-09 Eouse electric
US2410588A (en) * 1942-06-23 1946-11-05 Northrop Aircraft Inc Turbine blade and assembly thereof
GB630732A (en) * 1946-06-21 1949-10-20 Brush Electrical Eng An improved blade fixing for turbines and the like
US4836749A (en) * 1988-02-19 1989-06-06 Westinghouse Electric Corp. Pre-load device for a turbomachine rotor
EP0384166A2 (fr) * 1989-02-21 1990-08-29 Westinghouse Electric Corporation Construction de diaphragme de compresseur
JPH0791206A (ja) * 1993-09-24 1995-04-04 Mitsubishi Heavy Ind Ltd 回転機械動翼のダンパ構造
US20010019697A1 (en) * 2000-03-01 2001-09-06 Michael Mueller Fastening rotor blades in a turbomachine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1606029A (en) * 1926-11-09 Eouse electric
US2410588A (en) * 1942-06-23 1946-11-05 Northrop Aircraft Inc Turbine blade and assembly thereof
GB630732A (en) * 1946-06-21 1949-10-20 Brush Electrical Eng An improved blade fixing for turbines and the like
US4836749A (en) * 1988-02-19 1989-06-06 Westinghouse Electric Corp. Pre-load device for a turbomachine rotor
EP0384166A2 (fr) * 1989-02-21 1990-08-29 Westinghouse Electric Corporation Construction de diaphragme de compresseur
JPH0791206A (ja) * 1993-09-24 1995-04-04 Mitsubishi Heavy Ind Ltd 回転機械動翼のダンパ構造
US20010019697A1 (en) * 2000-03-01 2001-09-06 Michael Mueller Fastening rotor blades in a turbomachine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 1995, no. 07 31 August 1995 (1995-08-31) *

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2603696C2 (ru) * 2011-08-24 2016-11-27 Сименс Акциенгезелльшафт Лопаточный аппарат
EP2562356A1 (fr) * 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Agencement de pales
JP2014527594A (ja) * 2011-08-24 2014-10-16 シーメンス アクティエンゲゼルシャフト 翼構造体
WO2013026735A1 (fr) * 2011-08-24 2013-02-28 Siemens Aktiengesellschaft Agencement d'aubes
CN104053858B (zh) * 2011-08-24 2016-02-17 西门子公司 叶片装置
US9708919B2 (en) 2011-08-24 2017-07-18 Siemens Aktiengesellschaft Blade arrangement
JP2016519256A (ja) * 2013-05-23 2016-06-30 ゼネラル・エレクトリック・カンパニイ 複合材圧縮機ブレード及びその組立方法
DE102013223607A1 (de) * 2013-11-19 2015-05-21 MTU Aero Engines AG Rotor einer Strömungsmaschine
US10066493B2 (en) 2013-11-19 2018-09-04 MTU Aero Engines AG Rotor of a turbomachine
EP2918784A1 (fr) * 2014-03-13 2015-09-16 Siemens Aktiengesellschaft Pied d'aube pour une aube de turbine
CN106103903A (zh) * 2014-03-13 2016-11-09 西门子公司 用于涡轮叶片的叶根
JP2017517666A (ja) * 2014-03-13 2017-06-29 シーメンス アクティエンゲゼルシャフト タービンブレードのためのブレード基部
CN106103903B (zh) * 2014-03-13 2017-11-14 西门子公司 用于涡轮叶片的叶根
WO2015135787A1 (fr) * 2014-03-13 2015-09-17 Siemens Aktiengesellschaft Pied d'aube de turbine

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