EP3650652B1 - Fixation à un rotor de turbine d'une aube rotorique de turbine avec pied de sapin par une cale déformable et un élément de fixation - Google Patents

Fixation à un rotor de turbine d'une aube rotorique de turbine avec pied de sapin par une cale déformable et un élément de fixation Download PDF

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Publication number
EP3650652B1
EP3650652B1 EP18205174.8A EP18205174A EP3650652B1 EP 3650652 B1 EP3650652 B1 EP 3650652B1 EP 18205174 A EP18205174 A EP 18205174A EP 3650652 B1 EP3650652 B1 EP 3650652B1
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EP
European Patent Office
Prior art keywords
rotor
turbine
root
groove
turbine 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.)
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Application number
EP18205174.8A
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German (de)
English (en)
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EP3650652A1 (fr
Inventor
Tomas Misek
Miloslav Bily
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.)
Doosan Skoda Power sro
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Doosan Skoda Power sro
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Publication date
Application filed by Doosan Skoda Power sro filed Critical Doosan Skoda Power sro
Priority to PL18205174T priority Critical patent/PL3650652T3/pl
Priority to EP18205174.8A priority patent/EP3650652B1/fr
Publication of EP3650652A1 publication Critical patent/EP3650652A1/fr
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Publication of EP3650652B1 publication Critical patent/EP3650652B1/fr
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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
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection

Definitions

  • the invention relates to an arrangement of a turbine blade with a straight or circular tree-shaped root in a groove in a rotor of a turbine, in particular a steam or gas turbine.
  • the invention also relates to a turbine, in particular a steam or gas turbine, in which at least some of the turbine blades are arranged in this manner.
  • EP 1643082 describes an arrangement of a turbine blade with a circular tree-shaped root, in which a widening longitudinal groove is provided at the tip of a blade root.
  • a wedge-shaped bent spring which is mounted with its end folds in radial grooves in a rotor, whereas its straight ends rest against the faces of the blade root, by which means it prevents the turbine blade from undesirable movement in the direction of the axis of the turbine rotor.
  • the disadvantage of this solution is the limited capability of cushioning some of the forces acting on the blade, which may cause unwanted displacement of the blade in the groove.
  • a further disadvantage is the fact that it is quite difficult to predefine the compressive force applied to each turbine blade and to make sure that the same compressive force is applied to all the turbine blades.
  • Document EP2299060 discloses a securing device for axially and radially securing turbine blade to a rotor, wherein the rotor comprises a blade groove and the turbine blade comprises a turbine blade root, wherein the blade groove and the turbine blade root are designed such that the turbine blade root is adapted in the blade groove, wherein the securing device essentially comprises three components - a shear pin, a clamping piece and securing element.
  • the shear pin is introduced into a bore in the blade root and rests against an edge/face of the rotor.
  • the securing element is designed as locking plate having a projection resting in a corresponding groove and an end piece, which is bent perpendicularly in relation to a main piece and prevents clamping piece from falling out of the groove. Clamping piece having an upper leg and lower leg is pushed into the groove in such a way that the shear pin rests on its lower leg.
  • the clamping device which is pushed in the groove in rotor of the turbine is secured against axial displacement outwardly from the groove by means of securing element, and at the same time supports, without contact with the rotor the shear pin, positioned in a bore in the blade root and resting against an edge/face of the rotor and thus securing the blade root against axial movement.
  • Document US 2012/177498 discloses an axial retention device for a turbine system, the axial retention device comprising a pocket defined in a mating surface of one of a turbine component (e.g. blade) and a support structure (e.g. rotor).
  • the pocket includes a first axial load surface and a latch comprising a base member and a pivotal member, the base member being associated with a mating surface of the other of the turbine component and the support structure, the pivotal member being configured to engage the pocket and including a first mating axial load surface.
  • Engagement of the pivotal member and the pocket allows the first axial load surface and the first mating axial load surface to interact, preventing axial movement of the turbine component with respect to the support structure in at least one direction.
  • the pocket may be defined in one of the turbine component and the support structure, and the base member of the latch may be associated with the other of the turbine component and the support structure.
  • the pocket may be associated with the support structure and the base member may be defined in the turbine component or vice versa.
  • an arrangement of a turbine blade is known from practice in which a wedge is arranged in the bottom of a groove in a rotor to secure the turbine blade.
  • a metal hook is arranged on the wedge towards the tip of the turbine blade root, whereby the opposite ends of the hook are curved to opposite sides, one of them being mounted in a transverse groove formed at the tip of the blade root, the other constituting a support surface for the outer face of the wedge.
  • the drawback of this solution is a low level of cushioning some components of forces acting on the blade, which may cause unwanted displacement of the blade in the groove.
  • the aim of the invention is to provide an arrangement of a turbine blade with a straight or circular tree-shaped root in a groove in a turbine rotor, which would not suffer from the drawbacks of the types of arrangement which have been used so far.
  • the aim of the invention is a turbine in which at least some of the turbine blades are arranged in this manner.
  • the aim of the invention is achieved by an arrangement of a turbine blade with a straight or circular tree-shaped according to claim 1.
  • a locking wedge deformed in a controlled manner is inserted with an overlap in the radial direction, whereby the locking wedge is on its inner side over its entire width provided with a deformation groove and is in contact with the face of the recess at the tip of the root of the turbine blade and from the outer side is secured against axial displacement outwardly from the groove in the rotor by means of a securing element arranged demountably in the groove in the rotor or extending to the groove in the rotor.
  • the securing element is formed by a securing pin arranged in a radial aperture in the bottom of the groove in the rotor.
  • the locking wedge is provided with a means which extends to the space between the pin and the tip of the root of the turbine blade and secures the securing pin against unwanted movement in the radial direction, such a means being a pair of lamellas, which, after installation, are bent to the space above the top of the securing pin.
  • the locking wedge is provided with an elevated bearing surface on its lower and/or upper surface, whereby the radial overlap of its mounting in the space between the tip of the root of the turbine blade and the bottom of the rotor groove is realized only in the space of the bearing surface/surfaces.
  • the aim of the invention is also achieved by a turbine, especially a steam or gas turbine, having turbine blades with a straight or circular tree-shaped root mounted in a groove in the turbine rotor, whose principle consists in that at least some turbine blades are arranged in the manner according to the invention.
  • Fig.1 schematically shows a part of a sectional view of a steam turbine rotor with turbine blades arranged in exemplary embodiment of the arrangement of the turbine blade according to the invention with a locking wedge and a securing pin
  • Fig. 2 schematically shows a detail of this embodiment of the arrangement of the turbine blade
  • Fig. 3 schematically shows a view of the locking wedge and the securing pin of Figure 2 in the direction of the axis of the turbine rotor.
  • the turbine blade 1 of the turbine is provided in its lower part with a well-known tree-shaped root 10 with conical contact surfaces 100 .
  • the tree-shaped root 10 is arranged in a groove 20 of a corresponding shape in the turbine rotor 2 .
  • recesses 110 are formed from the outer side on both sides of the tip 11 of the tree-shaped root 10 , that is, from the side of the inlet and outlet, and within the space of these recesses 110 between the tip 11 of the root 10 of the turbine blade 1 and the bottom 21 of the groove 20 in the rotor 2 locking wedges 3 deformed in a controlled manner are inserted, with overlap in the radial direction.
  • These locking wedges 3 are on their inner side along their entire width provided with a deformation groove 30 , which increases their deformability.
  • the locking wedges 3 are in contact with the faces 111 of the recesses 110 .
  • the deformation grooves 30 are widening continuously towards the end of the locking wedges 3 .
  • the locking wedges 3 are secured against unwanted movement in the direction of the axis of the turbine rotor 2 by a securing element demountably arranged in the groove 20 in the rotor 2 or extending to the groove 20 in the rotor 2 .
  • the securing element is a securing pin 4 arranged in a radial aperture 40 formed in the bottom 21 of the groove 20 in the rotor 2 .
  • the locking wedge 3 is on the outer side against which rests the securing pin 4 provided with a suitably shaped bearing surface, which is rounded in the shown variant of embodiment.
  • a means which extends to the space between the securing pin 4 and the surface of the recess 110 and secures the securing pin 4 against undesirable movement in the radial direction (arrow B).
  • this means is formed by a pair of lamellas 31 arranged on the outer side of the locking wedge 3 . Between the lamellas 31 , there is sufficient space for insertion of the securing pin 4 into the radial aperture 40 in the bottom 21 of the groove 20 in the rotor 2 .
  • the locking wedge 3 is provided with an elevated contact surface 32 on its upper surface, whereby radial overlap in the arrangement of the locking wedge 3 in the space between the tip 11 of the root 10 of the turbine blade 1 and the bottom 21 of the groove 20 in the rotor 2 only occurs on this contact surface 32 .
  • this embodiment is not a necessary condition and the elevated contact surface 32 can be formed in other variants of embodiment also or only on the lower surface of the locking wedge 3 .
  • the contact surface 32 is formed by the entire upper and/or by the lower surface of the locking wedge 3 .
  • a recess 210 is provided in the bottom 21 of the groove 20 in the rotor 2 with a bearing surface for the locking wedge 3 .
  • the locking wedge 3 is on its inner side, on the upper and lower surfaces, provided with a chamfer 33 , which facilitates the insertion of the locking wedge 3 into the space between the tip 11 of the root 10 of the turbine blade 1 and the bottom 21 of the groove 20 in the rotor 2 .
  • the chamfer 33 may be formed only on one surface of the locking wedge 3 , or it may be formed on at least one side surface of the locking wedge 3 , or it does not have to be formed at all.
  • the locking wedge 3 cushions components of forces acting on the turbine blade 1 on its surface which is in contact with the face 111 of the recess 110 and reliably prevents displacement of the turbine blade 1 in the direction of the axis of the turbine rotor 2 . Moreover, due to its controlled deformation, occurring during insertion, the locking wedge 3 pushes the contact surfaces 100 of the root 10 of the turbine blade 1 into contact with the respective surfaces of the groove 20 in the rotor 2 , thereby fixing the turbine blade 1 also in the radial direction. Compared to the known method of securing, this radial compressive force is lower and the turbine blade 1 is not inserted in the rotor 2 on tight.
  • the arrangement and securing of the turbine blades 1 is then performed in a position with the paddle of the turbine blade 1 directed downwards, whereby each turbine blade is inserted into the respective groove 20 in the rotor 2 and aligned radially according to the blading plan.
  • the locking wedge 3 is inserted into the space between the tip 11 of the root 10 of the turbine blade 1 and the bottom 21 of the groove 20 in the rotor 2 , until it contacts the face 111 of the recess 110 .
  • the securing element is arranged and, if necessary, it is secured against unwanted movement in the radial direction - in the illustrated variant of embodiment, by bending the lamellas 31 on the outer side of the locking wedge 3 above it, etc.
  • the described method of the arrangement and securing of a turbine blade 1 can be combined with other well-known methods, when, for example, on the opposite sides of one turbine blade 1 different methods are used.

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

Claims (4)

  1. Agencement d'une lame orbitale (1) avec charnière arborescente droite ou circulaire (10) comprenant :
    - une lame orbitale (1) avec charnière arborescente droite ou circulaire (10), où la charnière (10) dispose d'un sommet (11) ;
    - un rotor (2) de turbine qui comprend une rainure (20) avec un fond ;
    - une cale d'immobilisation (3) qui est, sur le côté intérieur et sur toute sa largeur, équipée d'une rainure de déformation (30) ; et
    - un élément de sécurité ;
    - où la lame orbitale (1) est disposée à l'aide de sa charnière (10) dans la rainure (20) du rotor (2) ;
    - où un évidement (110) est formé au sommet (11) de la charnière (10) de la lame orbitale (1) sur au moins un côté de la lame orbitale (1) de l'extérieur ; et
    - dans l'espace de cet évidement est disposée, entre le sommet (11) de la charnière (10) de la lame orbitale (1) et le fond de la rainure (20) dans le rotor (2), avec un chevauchement dans la direction radiale, une cale d'immobilisation (3) à déformation contrôlée,
    - la cale d'immobilisation (3) est en contact avec la face (111) de l'évidement (110) au sommet (11) de la charnière (10) de la lame orbitale (1) ; et
    - la cale est sécurisée de l'extérieur contre un déplacement axial vers l'extérieur de la rainure (20) dans le rotor (2) à l'aide de l'élément de fixation, disposé de manière démontable dans la rainure (20) dans le rotor (2) ou étendu jusqu'à la rainure (20) dans le rotor (2) ;
    - l'élément de fixation comprend une broche de fixation (4) disposée dans l'ouverture radiale (40) dans le fond (21) de la rainure (20) dans le rotor (2), et
    - la cale d'immobilisation (3) est munie d'un outil qui s'étend dans l'espace entre l'élément de fixation (4) et le sommet (11) de la charnière (10) de la lame orbitale (2) et protège l'élément de fixation contre tout mouvement dans la direction radiale.
  2. Agencement selon la revendication 1, caractérisé en ce que l'outil qui s'étend dans l'espace entre la broche de fixation (4) et le sommet (11) de la charnière (10) de la lame orbitale (1) pour le protéger contre un mouvement radial, est une paire de lamelles (31) disposées sur le côté extérieur de la cale d'immobilisation (3).
  3. Agencement selon la revendication 1 ou 2, caractérisé en ce que la cale d'immobilisation (3) est pourvue, sur sa surface extérieure inférieure et/ou supérieure, d'une surface d'appui surélevée (32), où le chevauchement radial de son agencement dans l'espace entre le sommet (11) de la charnière (10) de la lame orbitale (1) et le fond (21) de la rainure (20) du rotor (2) est réalisé uniquement dans l'espace de cette/ces surface/s d'appui (32).
  4. Turbine, notamment à vapeur ou à gaz, comportant des lames orbitales (1) avec charnière arborescente (10) droite ou circulaire, montée dans les rainures (20) du rotor (2) de la turbine de la manière selon les revendications 1 à 3.
EP18205174.8A 2018-11-08 2018-11-08 Fixation à un rotor de turbine d'une aube rotorique de turbine avec pied de sapin par une cale déformable et un élément de fixation Active EP3650652B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PL18205174T PL3650652T3 (pl) 2018-11-08 2018-11-08 Mocowanie łopatki turbiny z prostą lub okrągłą stopką jodełkową w rowku wirnika turbiny, w szczególności turbiny parowej lub turbiny gazowej, oraz turbina, w szczególności turbina parowa lub turbina gazowa, w której przynajmniej pewne łopatki turbiny są rozmieszczone w ten sposób
EP18205174.8A EP3650652B1 (fr) 2018-11-08 2018-11-08 Fixation à un rotor de turbine d'une aube rotorique de turbine avec pied de sapin par une cale déformable et un élément de fixation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18205174.8A EP3650652B1 (fr) 2018-11-08 2018-11-08 Fixation à un rotor de turbine d'une aube rotorique de turbine avec pied de sapin par une cale déformable et un élément de fixation

Publications (2)

Publication Number Publication Date
EP3650652A1 EP3650652A1 (fr) 2020-05-13
EP3650652B1 true EP3650652B1 (fr) 2022-01-12

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Application Number Title Priority Date Filing Date
EP18205174.8A Active EP3650652B1 (fr) 2018-11-08 2018-11-08 Fixation à un rotor de turbine d'une aube rotorique de turbine avec pied de sapin par une cale déformable et un élément de fixation

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EP (1) EP3650652B1 (fr)
PL (1) PL3650652T3 (fr)

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4265595A (en) * 1979-01-02 1981-05-05 General Electric Company Turbomachinery blade retaining assembly
JPH0786678B2 (ja) 1985-07-25 1995-09-20 富士写真フイルム株式会社 ハロゲン化銀写真材料
EP1643082A1 (fr) 2004-09-30 2006-04-05 Siemens Aktiengesellschaft Fixation d'aubes de turbine
EP1860280A1 (fr) * 2006-04-07 2007-11-28 Siemens Aktiengesellschaft Dispositif de verrouillage d'une aube de turbine comprenant un élément de verrouillage
EP2299060A1 (fr) * 2009-09-17 2011-03-23 Siemens Aktiengesellschaft Fixation des aubes avec dispositif de verrouillage pour aubes de turbines
US20120177498A1 (en) * 2011-01-07 2012-07-12 General Electric Company Axial retention device for turbine system
US9103221B2 (en) * 2012-02-16 2015-08-11 Alstom Technology Ltd System and method for blade retention

Also Published As

Publication number Publication date
EP3650652A1 (fr) 2020-05-13
PL3650652T3 (pl) 2022-05-02

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