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EP1120545B1 - Dispositif de verrouillage des aubes dans une turbine axiale - Google Patents

Dispositif de verrouillage des aubes dans une turbine axiale Download PDF

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Publication number
EP1120545B1
EP1120545B1 EP00118862A EP00118862A EP1120545B1 EP 1120545 B1 EP1120545 B1 EP 1120545B1 EP 00118862 A EP00118862 A EP 00118862A EP 00118862 A EP00118862 A EP 00118862A EP 1120545 B1 EP1120545 B1 EP 1120545B1
Authority
EP
European Patent Office
Prior art keywords
retaining ring
blade root
locking device
blade
accordance
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
EP00118862A
Other languages
German (de)
English (en)
Other versions
EP1120545A2 (fr
EP1120545A3 (fr
Inventor
Stuart Dr. Lee
Peter Broadhead
Tim MÖLLER
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1120545A2 publication Critical patent/EP1120545A2/fr
Publication of EP1120545A3 publication Critical patent/EP1120545A3/fr
Application granted granted Critical
Publication of EP1120545B1 publication Critical patent/EP1120545B1/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
    • F01D5/32—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
    • 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 a retaining device for rotor blades of an axial turbomachine according to the preamble of patent claim 1.
  • the blades of a turbine stage are generally anchored in recesses provided for this purpose on the circumference of a rotor disk.
  • the blade feet for example, droplet-shaped or dovetail-shaped, so that the individual blades can be easily axially push into corresponding recesses on the circumference of the rotor disk. Due to the tapering of the blade feet, the individual blades are held in the radial direction in the rotor disk. In order to avoid a displacement of the blades in the axial direction, they can be locked, for example by a grub screw in its anchorage. In other retention mechanisms clamping pins are provided to provide a corresponding locking in the axial direction.
  • a further known from the prior art retaining device has for receiving the rotor blades on the circumference of a rotor disk fir-tooth-like toothed recesses.
  • corresponding blade feet also provided with a fir tree-like toothing are inserted axially.
  • the blade root holder is slightly conical in the axial direction, so that the blade can be inserted and removed only in one direction.
  • the blade root is fixed in this prior art by holding plates in its positions.
  • Such retaining plates are for example described in EP 0761930 A1.
  • Such holding plates are expensive to manufacture and require special tools during assembly. Due to the high mass of the holding plates high centrifugal forces are generated.
  • US 4,846,628 proposes a closed, circumferential holding and sealing ring, which has elevations on its inner circumference, which engage in corresponding claws of the rotor disk.
  • This holding and sealing ring covers the entire blade root height and has a labyrinth seal on its outer circumference. Furthermore, the holding and sealing ring described here and the blade feet must be positioned exactly in the axial direction to each other, so that the holding and sealing ring circumferentially formed contact seal can act.
  • FIG. 90 A similar prior art retaining and sealing ring 90 is shown in FIG.
  • the assembly and locking takes place in this prior art in a manner similar to a bayonet lock. Since the holding and sealing ring used at the same time serves as a seal against leakage flows between the rotor 93 and blades 94, it covers virtually the entire blade root 91 and must be manufactured and mounted due to the circumferential contact seal 92 with great accuracy. Furthermore, this holding and sealing ring 90 on its outer circumference on a labyrinth seal 95.
  • EP 0463955 B1 shows in the context of an embodiment, a circumferential retaining ring for a rotor blading, which covers most of the blade root. Structure and operation of this retaining ring is not described further in this prior art.
  • GB 2 258 273 A which forms the closest prior art, describes a retaining device in which the rotor disk has a groove which opens radially inwardly and in which the blade root is provided with a groove which opens radially outwards.
  • the retaining ring can be inserted between these two grooves.
  • the retaining ring is double-walled in its retention area by a loop-like part of the retaining ring is bent upwards and acts resiliently. This results on the one hand, due to the elasticity of the bent-up part, problems with the game occurring, on the other hand, such a retaining ring is costly and expensive to install.
  • EP 0 833 039 A This publication shows a retaining ring with raised sections and recesses.
  • the present invention is therefore an object of the invention to provide a retainer for blades of a turbomachine, which avoids the disadvantages of the prior art.
  • this is to provide a cost-effective restraint device which enables the improved control of leakage flows in the blade root area, overall improved flow conditions in the interstage area, lower centrifugal forces and easy installation.
  • the device according to the invention with the features of claim 1 has the advantage that a cost-effective retainer for blades of an axial turbomachine is provided which allows an improved control of leaks in the blade root area, overall improved flow conditions in the interstage area, lower centrifugal forces and easy installation.
  • This is achieved by the separation of the retention function, which is fulfilled by the retaining ring according to the invention, and the sealing function, which is fulfilled by using a retaining ring according to the invention by corresponding sealing surfaces between the blade and rotor disk, a considerable statisticserspamis.
  • the retaining function is fulfilled by arranged on the outer periphery of the retaining ring raised portions which cooperate with corresponding blade root sections. The directions given below are based on the rotor disk as a reference system.
  • the raised portions formed on the outer circumference of the retaining ring can be formed either according to claim 2 or according to claim 4.
  • the corresponding blade root portions are formed according to claim 3 or according to claim 5.
  • the raised portion on the outer circumference of the retaining ring from the side inserted into a corresponding receptacle on the blade root.
  • Complex special tool can be dispensed with in the present invention, since the retaining ring can be easily assembled with the usual assembly tools.
  • the invention thus provides a locking mechanism for the retaining ring which acts in a manner similar to a bayonet closure.
  • a significant weight saving is associated, which reduces both the manufacturing costs and the centrifugal forces and thereby enables higher speeds. Furthermore, due to the low blade root overlap, flow channels in the blade root area become possible which positively influence the flow and cooling air ratios between the rotor stages while penetrating the blade root area.
  • an embodiment is provided as a blocking block, which is inserted between two jaws of the locking mechanism.
  • the block can be secured, for example by securing wires against accidental slipping out.
  • several of these locks are provided on a rotor stage for redundancy reasons.
  • the design of the Schaufelfuß technique according to the features of claim 10 is particularly advantageous.
  • a fir-tree-like configuration of the toothing, which tapers conically in the axial direction, is advantageous.
  • the restraint device described is otherwise suitable for compressor and turbine stages. Particularly advantageous is a use in a turbine stage.
  • FIG. 1 is a schematic sectional view of the retaining device, in which a section of a rotor disk 2 is shown in section.
  • a blade 4 also shown in fragmentary form.
  • the blade 4 is received via a blade root 3 in a formed on the outer periphery of the turbine disk 2 Schaufelfuß technique 12 and thereby fixed in the radial direction.
  • the blade 4 is secured by a retaining ring 1.
  • a arranged in the region of the blade root 3 flow channel 14 is shown in dashed lines, which contributes to the improvement of the interstage flow.
  • a corresponding flow channel 14 is substantially possible by the inventive design of the retaining ring 1, which covers less than a third, in the present case about one-eighth of the blade root height.
  • the outlet opening 16 of the flow channel 14 is free, so that cooling air from the flow channel 14 can freely enter the disc space 2 following the disc rotor.
  • retention and sealing function are decoupled from each other.
  • the sealing function is perceived by a blade / disc sealing surface 15 to avoid leakage.
  • the blade / disc sealing surface 15 is formed as a mating surface between the bottom 26 of the blade platform and the top of the disposed between the Schaufelfußfactn 12 disc posts 25.
  • the closed, circumferential has on its inner circumference inwardly projecting portions 20 which engage in protruding on the rotor disk 2 claws
  • the claws 21 are on the one hand from a vertically projecting from the turbine disk 2, but thereby interrupted in the circumferential direction (see Fig. 3) rail 6 and on the other from a parallel to the turbine disk 2 arranged (of course also not circulating - see again Fig .3) stop 9 are formed and are thus arranged at regular intervals on the circumference of the rotor disk 2.
  • the rotor disk 2 in this case has below the Schaufelfußability 12 a circumferential recess 23 (viewed in the axial direction), which is continued at its lower end as (while interrupted) rail 6. At its upper end, the recess 23 has a machined guide surface 27, which corresponds to a shoulder 22 of the retaining ring 1.
  • the radially inwardly projecting portions 20 and the claws 21 act like a bayonet lock together.
  • the retaining ring 1 is shown in detail in FIG. In the area of the outer circumference, the retaining ring 1 has the stepped shoulder 22 already mentioned above. This forms with the machined surface 27 of the recess 23 a guide for the retaining ring 1 and thereby allows the precise insertion of arranged on the outer periphery of the retaining ring 1 raised portions 17 in a groove or retaining groove 5 a protruding retaining lug 18 of the blade 4.
  • Further 2 shows a locking device 8 for fixing the retaining ring 1 in the circumferential direction.
  • the arresting device 8 is formed by a substantially block-shaped block which can be inserted into the recesses formed on the inner circumference of the retaining ring 1 between the protruding portions 20.
  • the locking device 8 is secured against displacement in the axial direction by locking wires 10, which are respectively passed through holes 24 at the two ends of the locking device 8, as the perspective view in Figure 6 can be removed.
  • the basic structure of the retaining ring 1 is clearer by the fragmentary view in Figure 3.
  • the retaining ring 1 is first, as shown in perspective in Figure 3, applied to the rotor disk 2.
  • the radially inwardly projecting from the retaining ring 1 sections 20 are each between two jaws 21 of the rotor disk 2.
  • the blade foot 12 formed on the outer circumference of the rotor disk 2 in this case have a fir-tree-like teeth 13.
  • the retaining ring 1 in the circumferential direction moved so that the Schaufelfuß techniquen 12 are completely released.
  • the radially inwardly projecting portions 20 on the inner circumference of the retaining ring 1 partially slide into the claws 21 on the rotor disk 2.
  • the blade 4 is then inserted into the blade root receiver 12, as shown by way of example for a blade in FIG.
  • the blade 4 in the region of the blade root 3 a retaining lug 18 with the retaining groove 5 shown in Figures 1 and 2 on.
  • the raised portions 17 arranged on the outer circumference of the retaining ring 1 are inserted into the corresponding retaining grooves 5.
  • the blades 4 are axially fixed in the Schaufelfußing techniquen 12.
  • the outlet opening 16 of the flow channel shown in FIG. 1 is provided or shown on the retaining lug 18.
  • the blade 4 After inserting the lock 8 and securing it by securing wires 10, the blade 4 is secured and ready for operation with the rotor disk 2, as shown by way of example with reference to a blade in Figure 6.
  • FIG. 7 shows a second embodiment of the present invention.
  • the same or similar parts are provided with the same reference numerals.
  • raised portions 17 are formed like a sawtooth.
  • the sawtooth-like raised portions 17 can be inserted laterally into recesses 28 provided thereon on the blade root 3, as indicated schematically in FIG.
  • FIG. 7 also shows the blade / disk sealing surfaces 15, which perform the function of the contact seal 91 of the prior art shown in FIG.
  • FIG. 8 shows a view of the retaining ring 1 provided with sawtooth-like raised portions 17.
  • the mounting of the retaining ring 1 takes place in an analogous manner as described with reference to FIGS. 1 to 6.
  • the radially inwardly projecting from the retaining ring 1 sections 20 are each between two jaws 21 of the rotor disk 2.
  • the blade foot 12 formed on the outer circumference of the rotor disk 2 in this case have a fir-tree-like teeth 13.
  • a locking device (not shown) is inserted into the recesses between the inwardly protruding portions 20 for locking the retaining ring 1.

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

Claims (7)

  1. Dispositif de verrouillage pour aubes mobiles d'une turbomachine axiale qui, sur un disque de rotor (2), présente des logements de pieds d'aube (12) destinés à loger des aubes de rotor (4) et à les fixer dans le sens radial, et présente de plus un anneau de verrouillage (1) fermé et continu destiné à fixer dans le sens axial les aubes de rotor (4) dans les logements de pieds d'aubes (12), ainsi qu'un dispositif de verrouillage (19) destiné à fixer l'anneau de verrouillage (1) dans le sens axial, sachant que l'anneau de verrouillage (1) présente sur sa circonférence extérieure des évidements (7) correspondant à des sections des logements de pieds d'aube et des sections protubérantes (17), et que le dispositif de verrouillage (19) est constitué de sections (20) faisant saillie vers l'intérieur sur l'anneau de verrouillage (1) et de crabots (21) correspondants avec elles et faisant saillie dans le sens axial sur le disque de rotor (2), caractérisé en ce que l'anneau de verrouillage (1) couvre moins d'un tiers de la hauteur de chaque pied d'aube (3), et qu'un dispositif de blocage (8) est prévu pour fixer l'anneau de verrouillage (1) dans le sens circonférentiel.
  2. Dispositif de verrouillage selon la revendication n° 1, caractérisé en ce que les sections protubérantes (17) sur la circonférence extérieure de l'anneau de verrouillage (1) ont une forme trapézoïdale avec des sections portant des flancs arqués.
  3. Dispositif de verrouillage selon une des revendications précédentes, caractérisé en ce que dans le tiers inférieur du pied d'aube (3) fait saillie un talon d'arrêt (18) dans le sens axial qui présente dans le sens circonférentiel une rainure de verrouillage (5) destinée à loger les sections protubérantes (17) de la circonférence extérieure de l'anneau de verrouillage (1).
  4. Dispositif de verrouillage selon la revendication n° 1, caractérisé en ce que les sections protubérantes (17) sur la circonférence extérieure sont conçues en dents de scie.
  5. Dispositif de verrouillage selon la revendication n° 4, caractérisé en ce que dans son tiers inférieur, le pied d'aube (3) présente des évidements (7) correspondant aux sections en dents de scie de l'anneau de verrouillage (1).
  6. Dispositif de verrouillage selon une des revendications précédentes, caractérisé en ce qu'une surface d'étanchéité (15) est respectivement prévue sur la face supérieure des branches de disque (25) faisant saillie sur la circonférence du disque de rotor (2) entre les logements de pieds d'aube (12), ainsi que sur la face inférieure des plates-formes d'aube (26).
  7. Dispositif de verrouillage selon une des revendications précédentes, caractérisé en ce que le logement de pied d'aube (12) présente un endentement.
EP00118862A 1999-12-17 2000-08-31 Dispositif de verrouillage des aubes dans une turbine axiale Expired - Lifetime EP1120545B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19960896 1999-12-17
DE19960896A DE19960896A1 (de) 1999-12-17 1999-12-17 Rückhaltevorrichtung für Rotorschaufeln einer Axialturbomaschine

Publications (3)

Publication Number Publication Date
EP1120545A2 EP1120545A2 (fr) 2001-08-01
EP1120545A3 EP1120545A3 (fr) 2004-01-14
EP1120545B1 true EP1120545B1 (fr) 2006-10-18

Family

ID=7933025

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00118862A Expired - Lifetime EP1120545B1 (fr) 1999-12-17 2000-08-31 Dispositif de verrouillage des aubes dans une turbine axiale

Country Status (3)

Country Link
US (1) US6488473B1 (fr)
EP (1) EP1120545B1 (fr)
DE (2) DE19960896A1 (fr)

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9925261D0 (en) * 1999-10-27 1999-12-29 Rolls Royce Plc Locking devices
US6951448B2 (en) * 2002-04-16 2005-10-04 United Technologies Corporation Axial retention system and components thereof for a bladed rotor
GB0302116D0 (en) * 2003-01-30 2003-03-05 Rolls Royce Plc A rotor
GB0413652D0 (en) 2004-06-18 2004-07-21 Rolls Royce Plc Gas turbine engine structure
US7530791B2 (en) * 2005-12-22 2009-05-12 Pratt & Whitney Canada Corp. Turbine blade retaining apparatus
JP2007247406A (ja) * 2006-03-13 2007-09-27 Ihi Corp ファンブレードの保持構造
FR2900437B1 (fr) * 2006-04-27 2008-07-25 Snecma Sa Systeme de retention des aubes dans un rotor
FR2928406A1 (fr) * 2008-03-07 2009-09-11 Snecma Sa Dispositif de retenue axiale d'aubes montees sur un disque de rotor de turbomachine, disque de rotor et flasque de maintien d'un tel dispositif
US8814524B2 (en) * 2008-12-11 2014-08-26 Rolls-Royce Corporation Wheel formed from a bladed ring and disk
FR2939832B1 (fr) * 2008-12-11 2011-01-07 Turbomeca Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque.
FR2939834B1 (fr) * 2008-12-17 2016-02-19 Turbomeca Roue de turbine avec systeme de retention axiale des aubes
US8905717B2 (en) 2010-10-06 2014-12-09 General Electric Company Turbine bucket lockwire rotation prevention
US8864471B2 (en) 2011-08-12 2014-10-21 Hamilton Sundstrand Corporation Gas turbine rotor with purge blades
US9112383B2 (en) 2011-10-31 2015-08-18 General Electric Company System and method for Var injection at a distributed power generation source
EP2696035A1 (fr) 2012-08-09 2014-02-12 MTU Aero Engines GmbH Dispositif de retenue pour aubes mobiles d'une turbomachine et procédé de montage associé
US9664056B2 (en) * 2013-08-23 2017-05-30 General Electric Company Turbine system and adapter
GB201317161D0 (en) * 2013-09-27 2013-11-06 Rolls Royce Plc Retainer plate
EP2860349A1 (fr) * 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Aube de turbine et turbine à gaz
EP2860350A1 (fr) * 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Aube de turbine et turbine à gaz
FR3024491B1 (fr) * 2014-08-01 2018-12-07 Safran Aircraft Engines Ensemble rotatif pour turbomachine a dispositif de mise en place d'aubes
KR102182102B1 (ko) 2014-11-27 2020-11-23 한화에어로스페이스 주식회사 터빈 장치
FR3029962B1 (fr) * 2014-12-11 2019-08-23 Safran Aircraft Engines Blocage axial des aubes dans une roue de turbomachine
EP3564489A1 (fr) * 2018-05-03 2019-11-06 Siemens Aktiengesellschaft Rotor à surfaces de contact optimisées au niveau de forces centrifuges
EP3581765A1 (fr) * 2018-06-11 2019-12-18 Siemens Aktiengesellschaft Rotor pourvu de pales tournantes verrouillées axialement sur le disque de rotor

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1479332A (en) * 1974-11-06 1977-07-13 Rolls Royce Means for retaining blades to a disc or like structure
GB2042652B (en) * 1979-02-21 1983-07-20 Rolls Royce Joint making packing
US4566857A (en) * 1980-12-19 1986-01-28 United Technologies Corporation Locking of rotor blades on a rotor disk
FR2524932A1 (fr) * 1982-04-08 1983-10-14 Snecma Dispositif de retenue axiale de pieds d'aube dans un disque de turbomachine
FR2603333B1 (fr) * 1986-09-03 1990-07-20 Snecma Rotor de turbomachine comportant un moyen de verrouillage axial et d'etancheite d'aubes montees dans des brochages axiaux du disque et procede de montage
GB8705216D0 (en) * 1987-03-06 1987-04-08 Rolls Royce Plc Rotor assembly
FR2637321B1 (fr) * 1988-10-05 1990-11-30 Snecma Rotor de turbomachine muni d'un dispositif de fixation des aubes
US4921405A (en) * 1988-11-10 1990-05-01 Allied-Signal Inc. Dual structure turbine blade
US4846628A (en) 1988-12-23 1989-07-11 United Technologies Corporation Rotor assembly for a turbomachine
FR2663997B1 (fr) 1990-06-27 1993-12-24 Snecma Dispositif de fixation d'une couronne de revolution sur un disque de turbomachine.
US5112193A (en) * 1990-09-11 1992-05-12 Pratt & Whitney Canada Fan blade axial retention device
GB2258273B (en) * 1991-08-02 1994-08-10 Ruston Gas Turbines Ltd Rotor blade locking arrangement
US5256035A (en) * 1992-06-01 1993-10-26 United Technologies Corporation Rotor blade retention and sealing construction
FR2695433B1 (fr) * 1992-09-09 1994-10-21 Snecma Joint annulaire d'étanchéité disposé à une extrémité axiale d'un rotor et recouvrant des brochages d'aubes.
FR2710103B1 (fr) * 1993-09-16 1995-10-20 Snecma Flasque de rotor de turbomachine et assemblage de ce flasque avec un rotor.
GB9517369D0 (en) 1995-08-24 1995-10-25 Rolls Royce Plc Bladed rotor
GB2317652B (en) * 1996-09-26 2000-05-17 Rolls Royce Plc Seal arrangement

Also Published As

Publication number Publication date
EP1120545A2 (fr) 2001-08-01
US6488473B1 (en) 2002-12-03
EP1120545A3 (fr) 2004-01-14
DE50013633D1 (de) 2006-11-30
DE19960896A1 (de) 2001-06-28

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