EP1402152B1 - Systeme de retenue pour des aubes mobiles de turbomachines a ecoulement axial - Google Patents

Systeme de retenue pour des aubes mobiles de turbomachines a ecoulement axial Download PDF

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Publication number
EP1402152B1
EP1402152B1 EP02737718A EP02737718A EP1402152B1 EP 1402152 B1 EP1402152 B1 EP 1402152B1 EP 02737718 A EP02737718 A EP 02737718A EP 02737718 A EP02737718 A EP 02737718A EP 1402152 B1 EP1402152 B1 EP 1402152B1
Authority
EP
European Patent Office
Prior art keywords
locking
blade
axial
blade carrier
securing
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
EP02737718A
Other languages
German (de)
English (en)
Other versions
EP1402152A1 (fr
Inventor
Wolfgang Diebold
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.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems 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 ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Publication of EP1402152A1 publication Critical patent/EP1402152A1/fr
Application granted granted Critical
Publication of EP1402152B1 publication Critical patent/EP1402152B1/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
    • 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
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • the invention relates to an axial securing system for blades axially flowed turbomachinery according to the preamble of claim 1 and a fuse body for the security system according to the preamble of claim 8.
  • centrifugal forces act on the blades of axially turbomachines. These forces are usually absorbed by a fir-tree or dovetail-shaped, radially arranged and axially occidentalende groove-spring connection between the blade and blade carrier. The axial forces occurring through the axial flow direction of the flow medium, however, must be absorbed by means of a separate safety device.
  • securing bodies which extend from the downstream end only over part of the radially arranged axial groove, as is known, for example, from the patent US Pat. No. 2,641,443.
  • fuse bodies generally have an upstream projection which engages in an associated groove of the blade root.
  • the downstream end region projects beyond the Axialnut and is bent to axially secure the blade so that it engages behind the downstream rear side of the blade carrier.
  • a projection on the blade root engages the pressure side of the blade carrier at the opposite end of the blade root.
  • the securing system for each blade has a radially arranged axial groove in the blade carrier, into which the blade can be inserted with its counter-shaped blade root.
  • a fuse body is arranged, which engages with its first end region of the engaging axial force opposite the rear side of the blade carrier.
  • a securing element which is formed integrally with the blade carrier, is arranged axially adjacent to the first end region of the securing body and forms an axial stop for the latter. The first end portion of the fuse body comes to lie in a circumferential groove between stop and blade carrier.
  • the stop prevents the securing body from being displaced axially out of its position by the forces which occur or the end area being able to be bent, as a result of which the blade root and with it the blade are held in their exact position. Due to the one-piece design of the fuse element with the blade carrier manufacturing and assembly are particularly simple and inexpensive.
  • the force acting on the end region is distributed over a larger area. This leads to a more favorable ratio of force per surface also with respect to the stop formed by the securing element and associated with the end region.
  • the end regions of the securing body are wider than the base part and also wider than the axial groove, it is very advantageous if the end regions of the securing body protrude radially outward from the base part in the installed state and engage behind the end faces of the blade root and the end faces of the blade carrier. If this is the case, you need no additional tongue and no projection that engages in a matching groove of the blade root to make the connection between the blade root and fuse body. This simplifies both the manufacture of the blade root and that of the fuse body.
  • a fuse body according to the invention can be used not only in connection with the fuse system according to the invention but also in place of known fuse bodies without the fuse element.
  • the securing element is produced as a separate securing disk or as a securing ring, which is then welded or adhesively bonded to a body integral with the blade carrier, then existing turbomachines can be retrofitted with the securing system.
  • FIG. 1 and 3 each show a blade 10, which is fixed with its 12 in a radially disposed axial groove 14 of a blade carrier 16.
  • the blade root 12 is formed as a fir tree root and the axial groove 14 as the opposite groove, so that the blade root 12 is anchored radially and in the circumferential direction in the groove 14 against displacement.
  • a securing body 22 is arranged between a blade root 12 belonging to the blade root 12 and an axial groove 14 radially inwardly delimiting Axialnutêt 15, the two end portions 26, 26 'protrude in the axial direction over the axial groove 14.
  • the two end regions 26, 26 ' are each wider than a base part 28 of the securing body 22 connecting them.
  • the end regions 26, 26' each project radially outward from the base part 28 and each engage behind an end face 38 ', 40' of the blade root 12 and a portion of the end faces 38, 40 of the blade carrier 16. Because the end portions 26, 26 'of the fuse body 22 are wider than the base portion 28 and wider than the axial grooves 14, they still engage behind Parts of the end faces 38, 40 of the blade carrier 16 when they project radially outward from the base part 28.
  • the first end face 38 of the blade carrier 16 forms the pressure side of the blade carrier 16. Due to the flow direction A (see arrow), a very large axial force acts on this side. Via the blade root 12, this axially acting force is also transmitted to the first end region 26 of the securing body 22, which engages behind the opposite end face 40 of the blade carrier - also called the rear side 40. In order to prevent bending of the first end region 26, a securing element 24 is arranged on the rear side 40 of the blade carrier 16 which forms a stop 34 for the first end region 26 in the axial direction downstream so that the first end region 26 can no longer be bent open.
  • the securing element 24 forms, together with the securing body 22, the axial groove 14 and the blade root 12, a securing system 20 which connects the moving blade 10 to the blade carrier 16 in a positionally reliable manner, even in the axial, radial and circumferential directions, even at very high rotational speeds.
  • the fuse body 22 is formed of sheet metal and both end portions 26, 26 'are brought by bending in their position radially outwardly projecting from the base part 28.
  • the first end portion 38 which engages behind the rear side 40 of the blade carrier but also be formed as a solid projection and only the second end portion 26 'are brought into position by bending.
  • FIGS. 3 and 4 show the securing element 24 formed in one piece with the blade carrier 16.
  • the axial grooves 14 are first milled or cleared in the main body of the blade carrier 16. Then, on the rear side 40 of the blade carrier 16, a strip which measures approximately twice the thickness of the securing body 22 is turned off, namely radially inward, such that the stationary shoulder radially projects slightly further outward of the axial groove bottom 15 than the first radially outwardly protruding first Finally, on the axial grooves 14 facing side of the existing shoulder by turning a circumferential groove 42 is created, which extends radially inwardly slightly beyond the Axialnutêt 15 addition and whose width is such that they with little clearance the first End portion 26 of the fuse body 22 can accommodate.
  • the circumferential groove 42 can also be formed by grinding. By doing so, recesses and intervening elements left from the originally rotated shoulder are left downstream of the circumferential groove 42 by milling the axial grooves 14. The remaining elements now each form an axial stop 34 for the first end portion 26 of the fuse body 22, which indeed projects beyond the axial groove 14 and thus also the incision in the circumferential direction due to its width, so that the stopper can exert its effect.
  • each blade root 12 and the base part 28 of each securing body 22 corresponds to the axial extent of the axial grooves 14 remaining after rotation, so that after assembly no blade root 12 and no part of a base part 28 projects into the circumferential groove 42 or over the pressure side 38 of the Shovel stands out.
  • the securing element 24 can be combined with any desired securing bodies and then forms a security system 20 according to the invention.
  • Corresponding adaptations of the circumferential groove 42 are not a problem in this case.
  • the securing element 24 can also, as shown in FIG. 1, be designed as a separate securing disk 32, which, for example, be connected to the blade carrier 16 by means of a welded connection 30 to form an integral body.
  • the securing disk 32 has on its side facing the blade carrier 16 a shoulder which is configured in such a way that when connecting to the blade carrier 16 there is a circumferential groove 42 in which the respectively first end regions 26 of the securing body 22 reach into the rotor blades 10.
  • the securing element 24 can also be designed as a securing ring. Instead of using a welded joint 30, it is also conceivable to connect the securing element 24 by means of an adhesive bond with the blade carrier 16 to form a one-piece body.
  • An advantage of the separate configuration of the fuse element 24 is that existing blade carrier 16 can be retrofitted with axial groove / fuse body connections with this fuse element 24 and connected to the fuse element to one-piece bodies. In this way, a security system according to the invention can be retrofitted. This is possible regardless of the configuration of the fuse body. Because the security system 20 also works with other security bodies, as they are known for example from the aforementioned patents. For this purpose, the securing element 24 may then have to be adapted according to the configuration of the circumferential groove 42 or the stop 34.
  • the securing body 22 is inserted into the axial groove 14, in such a way that the first end region 26, which is already radially from the base part 28 protrudes, is received by the circumferential groove 42.
  • the first end portion 26 is then inserted with a small clearance between the stop 34 of the fuse element 32 and the corresponding parts of the end face 40 of the blade carrier 16.
  • the blade with its blade root 14 from the pressure side 38 forth on the fuse body 22 in the axial groove 14 of the blade carrier 16 inserted.
  • the second end region 26 'of the securing body 22 is bent radially outwards, so that the blade root 12 is axially fixed with the aid of the two end regions 26, 26'.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un système de retenue pour des aubes mobiles (10) de turbomachines à écoulement axial dans lesquelles les aubes mobiles (10) sont fixées radialement et dans le sens de la périphérie au moyen d'une emplanture d'aube (12) insérée dans une rainure axiale (14) disposée radialement d'un porte-aubes (16). L'aube mobile (10) est fixée axialement à l'aide d'un corps de retenue (22) qui est placé entre l'extrémité d'emplanture d'aube (13) et le fond (15) de la rainure axiale et dont la première zone d'extrémité (26) s'accroche par derrière à la face arrière (40), opposée à la force axiale appliquée, du porte-aubes (16). Outre ces organes de retenue axiaux et radiaux, le système de retenue (20) selon l'invention comprend un élément de retenue (24) qui est adjacent axialement à la première zone d'extrémité (26) du corps de retenue (22) et qui forme une butée axiale (34) pour ce corps de retenue. L'invention concerne également un corps de retenue pour ce système de retenue, dont les zones d'extrémité (26, 26') sont plus larges que la rainure axiale (14) et qui, à l'état monté, font uniquement saillie radialement vers l'extérieur à partir d'une partie de base (28) les reliant.

Claims (10)

  1. Système de fixation pour des aubes mobiles (10) de turbomachines à écoulement axial, dans lesquelles chaque aube mobile (10) présente une base d'aube (12) qui est enfoncée dans une rainure axiale (14) d'un support d'aubes (16), de sorte que l'aube mobile (10) soit fixée dans la direction radiale et périphérique, avec des corps de fixation (22) disposés dans les rainures axiales (14) entre les bases d'aubes (12) et le support d'aubes (16), lesquels viennent en prise par l'arrière à chaque fois par une première région d'extrémité de deux régions d'extrémité (26) avec le côté arrière (40) orienté vers l'aval du support d'aubes (16), caractérisé en ce qu'un élément de fixation (24) réalisé d'une seule pièce avec le support d'aubes (16) est disposé de manière axialement adjacente à la première région d'extrémité (26) du corps de fixation (22) et forme pour celui-ci une butée axiale (34).
  2. Système de fixation selon la revendication 1, caractérisé en ce que dans l'état monté, la première région d'extrémité (26) du corps de fixation (22) est disposée dans une rainure périphérique (42) entre la butée (34) et le support d'aubes (16).
  3. Système de fixation selon la revendication 1 ou 2,
    caractérisé en ce que l'élément de fixation (24) est fabriqué par tournage et/ou fraisage.
  4. Système de fixation selon la revendication 1 ou 2, caractérisé en ce que l'élément de fixation (24) est fabriqué sous forme de disque de fixation séparé (32) ou sous forme de bague de fixation séparée et peut être connecté au support d'aubes (16) pour former un corps d'une seule pièce.
  5. Système de fixation selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le corps de fixation (22) dépasse avec ses deux régions d'extrémité (26, 26') axialement au-delà de la rainure axiale (14) et les régions d'extrémité (26, 26') viennent en prise par l'arrière dans l'état monté avec un côté frontal respectif (38, 40) du support d'aubes (16).
  6. Système de fixation selon la revendication 5, caractérisé en ce que les régions d'extrémité (26, 26') sont plus larges que la partie de base (28) les connectant et sont plus larges que la rainure axiale (14) de sorte qu'elles dépassent de la rainure axiale (14) dans la direction périphérique.
  7. Système de fixation selon les revendications 5 et 6, caractérisé en ce que dans l'état monté, les régions d'extrémité (26, 26') du corps de fixation (22) font saillie radialement vers l'extérieur depuis la partie de base (28) et viennent en prise par l'arrière avec les côtés frontaux (38', 40') de la base d'aube (12) et avec des parties des côtés frontaux (38, 40) du support d'aubes (16).
  8. Disque de fixation (32) pour la fixation axiale d'aubes mobiles (10) de turbomachines à écoulement axial, dans lesquelles chaque aube mobile (10) présente une base d'aube (12) qui est enfoncée dans une rainure axiale (14) d'un support d'aubes (16), de sorte que l'aube mobile (10) soit fixée dans la direction radiale et périphérique, et dans lesquelles des corps de fixation (22) sont disposés dans les rainures axiales (14) entre les bases d'aubes (12) et le support d'aubes (16),lesquels viennent en prise par l'arrière à chaque fois par une première région d'extrémité de deux régions d'extrémité (26) avec le côté arrière (40) orienté vers l'aval du support d'aubes (16), le disque de fixation (32) étant réalisé de telle sorte et pouvant être connecté au support d'aubes (16) de telle sorte qu'il forme pour les premières régions d'extrémité (26) du corps de fixation (22) une butée axiale (34).
  9. Disque de fixation (32) selon la revendication 8, caractérisé en ce que le disque de fixation (32) est réalisé sous forme annulaire.
  10. Disque de fixation (32) selon la revendication 8 ou 9, caractérisé en ce que le disque de fixation (32) peut être connecté par son premier côté au support d'aubes (16) et présente sur le premier côté un épaulement et en ce que lors de la connexion du disque de fixation (32) au support d'aubes (16), il se forme une rainure périphérique entre le disque de fixation (32) et le support d'aubes (16), dans laquelle les premières régions d'extrémité (26) des corps de fixation (22) peuvent être enfoncées.
EP02737718A 2001-07-03 2002-06-25 Systeme de retenue pour des aubes mobiles de turbomachines a ecoulement axial Expired - Lifetime EP1402152B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH121901 2001-07-03
CH12192001 2001-07-03
PCT/CH2002/000344 WO2003004834A1 (fr) 2001-07-03 2002-06-25 Systeme de retenue pour des aubes mobiles de turbomachines a ecoulement axial

Publications (2)

Publication Number Publication Date
EP1402152A1 EP1402152A1 (fr) 2004-03-31
EP1402152B1 true EP1402152B1 (fr) 2007-01-17

Family

ID=4563621

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02737718A Expired - Lifetime EP1402152B1 (fr) 2001-07-03 2002-06-25 Systeme de retenue pour des aubes mobiles de turbomachines a ecoulement axial

Country Status (6)

Country Link
EP (1) EP1402152B1 (fr)
JP (1) JP4315801B2 (fr)
KR (1) KR100837134B1 (fr)
CN (1) CN100416045C (fr)
DE (1) DE50209295D1 (fr)
WO (1) WO2003004834A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
PL1694845T3 (pl) * 2003-11-28 2019-01-31 National Research Council Of Canada Przeciwciała przeciwko rakowi i ich zastosowania
DE102008013118B4 (de) * 2008-03-07 2014-03-27 Man Diesel & Turbo Se Anordnung zum Befestigen von Turbinenschaufeln
FR2931196B1 (fr) * 2008-05-16 2010-06-18 Snecma Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des passages radiaux permettant sa prehension
FR2963806B1 (fr) * 2010-08-10 2013-05-03 Snecma Dispositif de blocage d'un pied d'une aube de rotor
CN102022140B (zh) * 2010-12-28 2013-11-27 成都成发科能动力工程有限公司 叶片可独立拆装的透平机转子叶片安装方法
JP5999845B2 (ja) 2013-11-20 2016-09-28 三菱重工業株式会社 タービンロータ組立体およびタービンロータ組立体における翼止板並びに翼止板の組付け方法
CN113677478B (zh) * 2019-03-29 2023-06-23 平田机工株式会社 安装装置

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB643914A (en) * 1948-03-08 1950-09-27 Joseph Stanley Hall Improvements in and relating to turbine or like blade securing means
US2928651A (en) * 1955-01-21 1960-03-15 United Aircraft Corp Blade locking means
US2944507A (en) 1958-03-24 1960-07-12 Beal John Perry Water ski towing assembly
US2994507A (en) * 1959-01-23 1961-08-01 Westinghouse Electric Corp Blade locking structure
GB944326A (en) * 1959-06-12 1963-12-11 Ass Elect Ind Locking means for turbine or compressor blading
US3045329A (en) * 1959-07-30 1962-07-24 Gen Electric Method for assembling tongue-and-groove members with locking keys
DE1124968B (de) * 1960-10-27 1962-03-08 Associated Electrical Ind Manc Sicherung einer Axialturbomaschinen-Laufschaufel gegen Axialverschiebung
US3508844A (en) * 1968-07-25 1970-04-28 United Aircraft Corp Blade lock
US3556675A (en) 1969-01-29 1971-01-19 Gen Electric Turbomachinery rotor with integral shroud
GB1491480A (en) 1975-07-28 1977-11-09 Rolls Royce Fixing blades for fluid flow machines
FR2715975B1 (fr) * 1994-02-10 1996-03-29 Snecma Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées.
DE19757178C1 (de) * 1997-12-22 1999-06-10 Kloeckner Moeller Gmbh Verriegelungsvorrichtung
DE19757188A1 (de) * 1997-12-22 1999-06-24 Asea Brown Boveri Einrichtung zur Befestigung der Laufschaufeln einstufiger Axialturbinen

Also Published As

Publication number Publication date
CN1524160A (zh) 2004-08-25
WO2003004834A1 (fr) 2003-01-16
EP1402152A1 (fr) 2004-03-31
DE50209295D1 (de) 2007-03-08
JP2004532952A (ja) 2004-10-28
KR20040018409A (ko) 2004-03-03
JP4315801B2 (ja) 2009-08-19
KR100837134B1 (ko) 2008-06-11
CN100416045C (zh) 2008-09-03

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