EP1028231B1 - Fixation d'aubes de rotor d'une turbomachine - Google Patents

Fixation d'aubes de rotor d'une turbomachine Download PDF

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Publication number
EP1028231B1
EP1028231B1 EP99810127A EP99810127A EP1028231B1 EP 1028231 B1 EP1028231 B1 EP 1028231B1 EP 99810127 A EP99810127 A EP 99810127A EP 99810127 A EP99810127 A EP 99810127A EP 1028231 B1 EP1028231 B1 EP 1028231B1
Authority
EP
European Patent Office
Prior art keywords
intermediate pieces
halved
blade
fastening
moving
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
EP99810127A
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German (de)
English (en)
Other versions
EP1028231A1 (fr
Inventor
Siegfried Hohmann
Dieter Freuschle
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 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 Schweiz AG filed Critical Alstom Schweiz AG
Priority to DE59906856T priority Critical patent/DE59906856D1/de
Priority to EP99810127A priority patent/EP1028231B1/fr
Priority to US09/501,998 priority patent/US6299411B1/en
Priority to CN00104177.0A priority patent/CN1263204A/zh
Priority to JP2000035921A priority patent/JP2000234502A/ja
Publication of EP1028231A1 publication Critical patent/EP1028231A1/fr
Application granted granted Critical
Publication of EP1028231B1 publication Critical patent/EP1028231B1/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
    • F01D5/3023—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

Definitions

  • the invention relates to a fastening of turbine blades in one Circumferential groove on the turbine rotor using hammer-head-shaped blade feet.
  • the blades are installed by screwing in the blade feet.
  • the last The blade is installed in a gap along the circumference of the groove.
  • the invention relates to components that are located between the assembled blade roots be inserted and serve to fill up the remaining gap and thereby fixing the blade feet.
  • a known method is to grant an assembly gap that is dimensioned such that the last blade root can just be inserted into the groove. If the blade root has the basic shape of a parallelogram, the mounting gap must be at least equal to the long diagonal of the parallelogram, as shown in FIG. 1a and explained in more detail below.
  • the mounting gap must be at least equal to the long diagonal of the parallelogram, as shown in FIG. 1a and explained in more detail below.
  • the halves of the intermediate pieces are straight and vertical in the middle.
  • the spacers or spacer inserts serve not only to fix the blade feet in the groove, but also to distance the blade feet from one another and to distribute the remaining gap evenly over the circumference of the groove.
  • the intermediate pieces each have the same shape as the shovel feet, which they fix.
  • the blade roots of each row of blades are dimensioned in accordance with the size of the blades of that row of blades.
  • the blade feet of one row of blades differ from those of another row of blades in terms of their width, length and the number of teeth and steps in the T shape or hammer head shape.
  • a gap is again provided which is large enough to fit a halved intermediate piece.
  • This smaller gap is finally filled by means of halved intermediate pieces, as shown in FIG. 2b. (The gap remaining after inserting these half spacers is finally filled by a three-part end piece, after which the blades are sufficiently fixed in the circumferential groove for the operation of the turbine.)
  • the basic shape, or the cross section, of the entire intermediate pieces described here are rectangular, ie the short sides of the intermediate piece, or axial guide surfaces, lie at an angle to the side wall of the circumferential groove.
  • the spacers only touch the side wall of the groove with their corners.
  • the groove and the intermediate pieces are not heavily loaded as a result, since the lateral axial force on the entire intermediate pieces is only very slight.
  • the halved intermediate pieces have a parallelogram-shaped cross section in the fit area, the short sides of the parallelogram standing at an angle different from 90 ° to the long sides. The angle is dimensioned such that the short sides or axial guide surfaces lie flat on the side wall of the circumferential groove.
  • a flat support is necessary because the lateral axial forces that act on the halved intermediate piece are much greater compared to the entire intermediate pieces.
  • the short sides would lie on the side walls of the groove, the halved intermediate pieces would notch in the side wall and damage it.
  • the difference between the axial forces on the halved and the axial forces on the whole spacers is related to the fact that there is a center of gravity in the case of the whole spacers and two centers on which the centrifugal force acts in the case of the halved spacers.
  • the angling of the short sides of the halved spacers prevents damage to the spacers and the groove by notching. However, the production of the angling is expensive.
  • Swiss patent CH 322 010 discloses a blade ring Turbo machine with blade spacers arranged in a circumferential groove between the blade feet.
  • a closing link of the blade ring consists of two parts a and b, according to the composition by means of a screw c in shape and dimension equal to the blade spacers between the blade roots are.
  • US 2,281,318 discloses a device for fastening rotor blades in a circumferential groove, intermediate pieces being arranged between the blade feet are. At least one of the intermediate pieces consists of two parts with straight, sloping sides for the purpose of mounting in a circumferential groove, being for attachment These two parts have other means, such as a wedge.
  • US 3,328,867 discloses a method for mounting blade roots in a Circumferential groove, the blade feet being parallelogram-shaped. For assembly A space is left open for the last blade root, into which the last one Blade root is inserted by a turn, after which the remaining one Free space is filled by means of intermediate wedges 7.
  • FR 363,064 discloses a method for mounting blades in a Circumferential groove by means of shovel feet and spacers, with the purpose of increasing assembly safety, pins are guided through several shovel feet.
  • pins are guided through several shovel feet.
  • For the Attachment of the last shovel uses an intermediate piece that is in two Halves each with oblique, straight sides, which is wedge-like by caulking in the groove can be introduced.
  • a blade attachment according to the generic term of claim 1, in which the halved intermediate pieces, in consideration of the vertical cross section parallel to the long side of the basic form, those sides the halved intermediate pieces, that of the middle of the circumferential groove and the adjacent halved intermediate piece are facing, hook-shaped are.
  • the hook shape of a halved intermediate piece forms that geometric negative of the hook shape of the halved intermediate piece on the right, so that the sides of the two halved spacers into each other fit and interlock positively due to their hook shape to let.
  • the two intermediate pieces are therefore geometrical counterparts from each other.
  • the basic shape or the horizontal cross section of the Halved spacers imposed according to the invention is rectangular educated.
  • the hanging of adjacent, halved intermediate pieces standing next to one another by the hook shape according to the invention has the advantage that the two halved intermediate pieces are now connected to a single piece with a single center of gravity.
  • the result is an intermediate piece which is equivalent in terms of the forces acting on it to an entire intermediate piece on which only small axial forces act.
  • Those axial forces that act on the individual halved intermediate pieces now act on the hook-shaped inner surfaces of the intermediate pieces.
  • the side surfaces of the intermediate pieces, which touch the side walls of the groove, are relieved. This makes it possible to manufacture the short side walls of the intermediate pieces at right angles. Since the axial forces are now lower, there are no notches on the groove wall.
  • the invention therefore has the advantage that the halved intermediate pieces can also be manufactured at right angles and at low cost.
  • the hook-shaped inner surfaces of the halved intermediate pieces according to the invention are produced, for example, by a laser cutting process.
  • FIG. 1 a shows a rotor 1 in which a circumferential groove 2 with useful jaws 3 is arranged.
  • blades 4 are inserted, which are marked with 1., 2. etc. to n-1 and n.
  • the blade roots 5 of the rotor blades 3 have a parallelogram-shaped basic shape which is adapted to the width of the circumferential groove, so that the sides of the blade roots 5 lie flat on the sides of the groove.
  • the blade feet are basically T-shaped, which means that they can be anchored in the useful jaws 3.
  • the parallelograms of the blade roots are also dimensioned in their length along the circumferential direction so that after anchoring n-1 blade roots, a gap remains in the groove which is the same as the long diagonal of a blade root rhombus. This gap thus allows the assembly of the last, nth blade without a side installation opening. After the last blade has been installed, a residual gap 6 remains as shown in FIG. 1b.
  • Figure 1c shows the filling of the remaining gap 6 by means of spacer inserts or spacers 7, 7a, 7b. These are inserted between the blade feet 5 and anchored in the useful jaw 3 in the same way as the blade feet themselves. For this purpose, the intermediate pieces 7, 7a, 7b are of the same shape as the blade feet which fix them.
  • FIG. 2a Most of the intermediate pieces are so-called whole intermediate pieces 7 as in FIG. 2a, the remaining intermediate pieces are halved intermediate pieces 7a, 7b as shown in FIG. 2b.
  • the halved spacers 7a, 7b are used when the gap has become too narrow for the installation of the whole spacers.
  • FIG. 3a to c show several variants of halved spacers 7a and 7b, which are shaped and hung together according to the invention.
  • the hook shape 9 according to the invention of the inner sides 8 of the intermediate pieces is rectangular in a first embodiment, as in FIG.
  • the half-piece 7a is the geometric negative of the half-piece 7b, so that the two half-pieces fit into one another as shown and can be hung together.
  • the axial forces that act on the side walls of the rotor groove in the case of a pair of spacers so imposed are the same as those axial forces that act on a whole spacer.
  • the horizontal cross section of the connected intermediate pieces is also shown, the short sides no longer being beveled with respect to the long sides, but rather being at right angles to them. This form is easier and cheaper to manufacture.
  • the point of engagement of the toothing forces in the suspension as indicated by arrows, lies on the longitudinal axis 11 of the halved intermediate piece, shown in broken lines.
  • the position of the hooking or toothing of the half pieces 7a and 7b is chosen as far away as possible with respect to the useful neck support points 10. The purpose of this is that the smallest possible connection forces arise during operation. The point of engagement of the toothing forces is therefore preferably in the upper fifth of the total height H of the component of the intermediate piece.
  • Figure 3b halved intermediate pieces are shown with a wedge-shaped hook shape 9, which are hung together in a similar manner as in Figure 3a. The imposition in turn causes similar axial forces, so that the basic shape is the same as in Figure 3a.
  • FIG. 3c shows a further embodiment with a zigzag-shaped hook shape 9. Further hook shapes with, for example, curved shapes can also be implemented.

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

Claims (5)

  1. Agencement de fixation d'aubes mobiles (4) dans un rotor (1) d'une turbomachine au moyen de bases d'aubes (5), les aubes mobiles (4) d'une rangée d'aubes mobiles étant à chaque fois disposées dans une encoche périphérique (2) sur le rotor (1) et après le montage de la dernière aube mobile (4) d'une rangée d'aubes mobiles, un interstice résiduel (6) étant présent, lequel est rempli par des pièces intermédiaires (7), les pièces intermédiaires (7) étant disposées entre les bases des aubes (5), plusieurs pièces intermédiaires (7) étant des pièces intermédiaires entières (7) et les pièces intermédiaires restantes (7) étant des pièces intermédiaires partagées en deux avec une première et une deuxième moitié (7a, 7b) et le parois extérieures de toutes les pièces intermédiaires entières et partagées en deux (7, 7a, 7b) contactant les parois latérales axiales de l'encoche périphérique (2),
    caractérisé en ce que
    les premières et deuxièmes moitiés (7a, 7b) des pièces intermédiaires partagées en deux présentent chacune une forme de crochet (9) sur leurs faces intérieures (8) qui sont tournées vers le centre de l'encoche périphérique (2), la face intérieure (8) de la première moitié (7a) étant la négative géométrique de la face intérieure (8) de la deuxième moitié adjacente (7b) et les premières et deuxièmes moitiés (7a, 7b) étant raccordées les unes aux autres par engagement positif, et des forces d'engrenage agissant sur les formes de crochets engagées mutuellement (9).
  2. Agencement de fixation d'aubes mobiles (4) selon la revendication 1,
    caractérisé en ce que
    la section transversale horizontale des pièces intermédiaires entières et partagées en deux (7, 7a, 7b) est rectangulaire.
  3. Agencement de fixation d'aubes mobiles (4) selon la revendication 2,
    caractérisé en ce que
    la forme de crochet (9) sur les faces intérieures (8) des pièces intermédiaires partagées en deux (7a, 7b) est rectangulaire, en forme de clavette, ou en forme de zig-zag.
  4. Agencement de fixation d'aubes mobiles (4) selon la revendication 3,
    caractérisé en ce que
    le point d'attaque (10) des forces d'engrenage sur les formes de crochet (9) des pièces intermédiaires partagées en deux (7a, 7b) se trouve dans le cinquième supérieur de la hauteur totale (H) des pièces intermédiaires (7a, 7b).
  5. Agencement de fixation d'aubes mobiles (4) selon la revendication 4,
    caractérisé en ce que
    le point d'attaque (10) des forces d'engrenage sur les formes de crochet (9) des pièces intermédiaires partagées en deux (7a, 7b) se trouve sur l'axe longitudinal (11) des pièces intermédiaires partagées en deux.
EP99810127A 1999-02-12 1999-02-12 Fixation d'aubes de rotor d'une turbomachine Expired - Lifetime EP1028231B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
DE59906856T DE59906856D1 (de) 1999-02-12 1999-02-12 Befestigung von Laufschaufeln einer Strömungsmachine
EP99810127A EP1028231B1 (fr) 1999-02-12 1999-02-12 Fixation d'aubes de rotor d'une turbomachine
US09/501,998 US6299411B1 (en) 1999-02-12 2000-02-11 Fastening of moving blades of a fluid-flow machine
CN00104177.0A CN1263204A (zh) 1999-02-12 2000-02-12 液流机械中转动叶片的固定件
JP2000035921A JP2000234502A (ja) 1999-02-12 2000-02-14 流体流れ機械の動翼の取付け

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP99810127A EP1028231B1 (fr) 1999-02-12 1999-02-12 Fixation d'aubes de rotor d'une turbomachine

Publications (2)

Publication Number Publication Date
EP1028231A1 EP1028231A1 (fr) 2000-08-16
EP1028231B1 true EP1028231B1 (fr) 2003-09-03

Family

ID=8242674

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99810127A Expired - Lifetime EP1028231B1 (fr) 1999-02-12 1999-02-12 Fixation d'aubes de rotor d'une turbomachine

Country Status (5)

Country Link
US (1) US6299411B1 (fr)
EP (1) EP1028231B1 (fr)
JP (1) JP2000234502A (fr)
CN (1) CN1263204A (fr)
DE (1) DE59906856D1 (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10310431A1 (de) * 2003-03-11 2004-09-23 Alstom Technology Ltd Rotor-Schluss
DE102004011508A1 (de) * 2004-03-08 2005-09-29 Alstom Technology Ltd Rotor-Schluss
GB0422507D0 (en) * 2004-10-11 2004-11-10 Alstom Technology Ltd Turbine blade and turbine rotor assembly
EP1698758B1 (fr) 2005-02-23 2015-11-11 Alstom Technology Ltd Fermeture de rotor à fente axiale
DE102005030516A1 (de) * 2005-06-28 2007-01-04 Man Turbo Ag Rotor für eine Turbine sowie Verfahren und Vorrichtung zur Herstellung des Rotors
US7507075B2 (en) † 2005-08-15 2009-03-24 United Technologies Corporation Mistake proof identification feature for turbine blades
EP1803899A1 (fr) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Ensemble de verrouillage d'aube pour une turbomachine
DE102008057245A1 (de) * 2008-04-22 2009-10-29 Friatec Aktiengesellschaft Modular aufgebauter Sondenfuß und seine Komponenten
DE102010053141B4 (de) * 2009-12-07 2018-10-11 General Electric Technology Gmbh Turbinenaggregat mit möglicher Überdrehung des Fußes einer Schaufel bis zum Einbau einer letzten Schaufel
US20110255978A1 (en) * 2010-04-16 2011-10-20 Brian Denver Potter Locking Assembly For Circumferential Attachments
JP6190622B2 (ja) * 2013-05-15 2017-08-30 三菱日立パワーシステムズ株式会社 タービン
EP2918784A1 (fr) * 2014-03-13 2015-09-16 Siemens Aktiengesellschaft Pied d'aube pour une aube de turbine
CN109931112A (zh) * 2019-04-28 2019-06-25 杭州汽轮机股份有限公司 一种汽轮机自由叶片结构及其装配方法

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Also Published As

Publication number Publication date
US6299411B1 (en) 2001-10-09
EP1028231A1 (fr) 2000-08-16
CN1263204A (zh) 2000-08-16
JP2000234502A (ja) 2000-08-29
DE59906856D1 (de) 2003-10-09

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