EP1120545A2 - Verrouillage des aubes dans une turbine axiale - Google Patents

Verrouillage des aubes dans une turbine axiale Download PDF

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Publication number
EP1120545A2
EP1120545A2 EP00118862A EP00118862A EP1120545A2 EP 1120545 A2 EP1120545 A2 EP 1120545A2 EP 00118862 A EP00118862 A EP 00118862A EP 00118862 A EP00118862 A EP 00118862A EP 1120545 A2 EP1120545 A2 EP 1120545A2
Authority
EP
European Patent Office
Prior art keywords
retaining ring
blade root
retaining
restraint device
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.)
Granted
Application number
EP00118862A
Other languages
German (de)
English (en)
Other versions
EP1120545A3 (fr
EP1120545B1 (fr
Inventor
Stuart Dr. Lee
Peter Broadhead
Tim Hopp
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 turbo machine according to the preamble of claim 1.
  • Another restraint device known from the prior art has the Inclusion of the rotor blades on the circumference of a rotor disk toothed like a fir tree Deepening. Here are also corresponding with a fir tree-like Toothed blade feet are inserted axially. It is the blade root holder is slightly conical in the axial direction, so that the Bucket can only be inserted and removed in one direction. To prevent the blade from accidentally loosening and slipping out of the blade root holder To avoid the blade root in this prior art fixed in position by holding plates. Such holding plates are for example described in EP 0761930 A1. Such holding plates are expensive in manufacture and require special tools for assembly. Due to the high centrifugal forces are generated due to the high mass of the holding plates.
  • US 4,846,628 proposes a closed, rotating holding and Sealing ring in front, which has elevations on its inner circumference, which in corresponding Engage the claws of the rotor disc.
  • This retaining and sealing ring covers the entire blade root height and has a labyrinth seal on its outer circumference on.
  • the retaining and sealing ring described here and the blade feet must be positioned exactly in the axial direction to one another, so that the all-round contact seal on the retaining and sealing ring act can.
  • FIG. 9 A similar retaining and sealing ring 90 from the prior art is shown in FIG. 9. This state of the art is used for assembly and locking in one Way similar to a bayonet catch. Because the retaining and sealing ring used at the same time as a seal against leakage flows between rotor 93 and Serves blades 94, it covers almost the entire blade root 91 and has to the circumferential contact seal 92 manufactured with great accuracy and to be assembled. Furthermore, this holding and sealing ring 90 has on its outer circumference a labyrinth seal 95.
  • EP 0463955 B1 does indeed show a rotating one in the context of an exemplary embodiment Retaining ring for a rotor blading, which the largest part of the Blade foot covered. Structure and functioning of this retaining ring however, not further described in this prior art.
  • the present invention is therefore based on the object of a restraint device for rotor blades of a turbo machine to create the disadvantages avoids the prior art.
  • this is said to be an inexpensive Restraint devices are provided which provide improved control of leakage flows in the blade root area, overall improved flow conditions in the intermediate stage area, lower centrifugal forces and one allows easy assembly.
  • the device according to the invention with the features of claim 1 has the advantage that an inexpensive retaining device for blades one Axial turbomachine is provided which has improved mastery of leakage flows in the blade root area, overall improved flow conditions in the intermediate stage area, lower centrifugal forces and easy assembly enables.
  • the separation of the restraint function, that of the invention Retaining ring is fulfilled, and the sealing function that when used a retaining ring according to the invention by appropriate sealing surfaces between the blade and the rotor disk is achieved, a considerable weight saving achieved.
  • due to the elimination of contact and labyrinth seals Larger manufacturing and assembly tolerances possible.
  • the retention function is raised by arranged on the outer circumference of the retaining ring Sections met, which interact with corresponding blade root sections. The directions used in the following are based on the Rotor disc as a reference system.
  • the raised sections formed on the outer circumference of the retaining ring can be designed either according to claim 2 or according to claim 4.
  • the corresponding blade root sections are designed according to claim 3 or according to claim 5.
  • the raised portion on the A and the retaining ring from the side in a corresponding receptacle ⁇ enlie inserted at the blade root in contrast to the embodiment according to claim 2 and 3, in the embodiment according to claim 4 and 5, the raised portion on the A and the retaining ring from the side in a corresponding receptacle ⁇ enograph inserted at the blade root.
  • Elaborate special tools can be dispensed with in the present invention, since the retaining ring can be easily assembled with the common assembly tools.
  • An advantageous embodiment of the present invention with the features of claim 6 sees one acting in a manner similar to a bayonet lock Locking mechanism for the retaining ring in front.
  • An embodiment according to claim 7 is particularly advantageous considerable weight savings associated with both the manufacturing cost centrifugal forces are also reduced, which enables higher speeds. Further are flow channels in the low blade root coverage Blade root area possible, the penetration of the blade root area Influence flow and cooling air between the rotor stages positively.
  • An advantageous development of the invention with the features of claim 8 can be designed, for example, as a blocking block, which is between two claws of the Locking mechanism is inserted.
  • the locking block can, for example secured with safety wires against unintentional sliding out become. Normally, several of these locks are on for reasons of redundancy a rotor stage provided.
  • the design of the blade root receptacle according to the features of the claim 10 is particularly advantageous.
  • it is a fir tree-like one Formation of the toothing, which tapers conically in the axial direction, advantageous.
  • the retention device described is otherwise for compressor and turbine stages suitable. Use in a turbine stage is particularly advantageous.
  • FIG. 1 is a schematic sectional view of the restraint device, in which a section of a rotor disk 2 is shown in section. At the The outer circumference of the rotor disk 2 is also shown in sections Blade 4 arranged. The blade 4 is in the outer circumference via a blade root 3 the turbine disk 2 formed blade root receptacle 12 and thereby fixed in the radial direction. against displacement in the axial Direction, the blade 4 is secured by a retaining ring 1.
  • a flow channel 14 arranged in the area of the blade root 3 is shown in broken lines, which contributes to the improvement of the interstage flow.
  • Training a corresponding flow channel 14 is essentially due to the invention Design of the retaining ring 1 possible, the less than one Third, in the present case covering approximately one eighth of the blade root height.
  • the outlet opening 16 of the flow channel 14 is free, so that cooling air is out the flow channel 14 in the downstream of the rotor disc 2 Space between the panes can occur.
  • the retention and sealing function decoupled from each other.
  • the sealing function to avoid leakage from a blade / disc Perceived sealing surface 15.
  • the blade / disc sealing surface 15 is as Mating surface between the bottom 26 of the blade platform and the top of the disc posts 25 arranged between the blade root receptacles 12 are formed.
  • the closed, circumferential has protruding inwards on its inner circumference Sections 20, which in claws 21 protruding from the rotor disk 2 intervention.
  • the claws 21 are made perpendicular to the turbine disk 2 protruding but interrupted in the circumferential direction (cf. 3) rail 6 and the other from a parallel to the tubing disc 2 arranged (of course also not circulating - see again Fig. 3) stop 9 is formed and are therefore at regular intervals on the circumference the rotor disc 2 arranged.
  • the rotor disk 2 has below the Blade root receptacle 12 a circumferential recess 23 (viewed in the axial direction) on, which continues at its lower end as (but interrupted) rail 6 is.
  • the recess 23 has a machined guide surface 27, which corresponds to a shoulder 22 of the retaining ring 1.
  • Radially inwardly projecting sections 20 and the claws 21 act thereby almost like a bayonet catch.
  • the retaining ring 1 is shown in detail in FIG. 2.
  • the retaining ring 1 has the step-shaped heel already mentioned above 22 on. This forms a guide with the machined surface 27 of the recess 23 for the retaining ring 1 and thereby enables the exact insertion of the outer circumference of the retaining ring 1 arranged raised portions 17 in a Groove or retaining groove 5 of a protruding retaining lug 18 of the blade 4.
  • FIG. 2 shows a locking device 8 for fixing the retaining ring 1 in the circumferential direction.
  • the locking device 8 is essentially by a cuboid block formed in the on the inner circumference of the retaining ring 1 inserted between the protruding portions 20 recesses is.
  • the locking device 8 is against displacement in the axial direction secured by locking wires 10, each through holes 24 in the two Ends of the locking device 8 are passed, as the perspective view can be seen in Figure 6.
  • the basic structure of the retaining ring 1 becomes clearer from the partial view in FIG. 3.
  • the retaining ring 1 first becomes perspective, as in FIG. 3 shown, applied to the rotor disc 2.
  • the ones from the retaining ring 1 sections 20 projecting radially inwards between two claws 21 the rotor disk 2.
  • the blade root receptacles formed on the outer circumference of the rotor disk 2 12 have a fir tree-like toothing 13.
  • the retaining ring 1 is now shifted in the circumferential direction, as shown in FIG. that the blade root receptacles 12 are completely released. Slide it that protrude radially inwards on the inner circumference of the retaining ring 1 Sections 20 partially into the claws 21 on the rotor disk 2. Then the blade 4 is inserted into the blade root receptacle 12, as is exemplary for a blade shown in Figure 5.
  • the blade 4 has in the area of the blade root 3 a retaining lug 18 with the retaining groove 5 shown in FIGS. 1 and 2 on.
  • the outer circumference of the retaining ring 1 arranged raised portions 17 in the corresponding Retaining grooves 5 introduced.
  • the retaining lug 18 is also the Outlet opening 16 of the flow channel shown in FIG. 1 is provided or shown.
  • the blade 4 is secured and connected to the rotor disk 2 ready for operation, as shown by way of example using a shovel in FIG. 6.
  • Figures 7 and 8 show a second embodiment of the present invention.
  • the raised sections 17 arranged on the outer circumference of the retaining ring 1 are of sawtooth-like design.
  • the sawtooth-like raised sections 17 can be inserted laterally into recesses 28 provided for this purpose on the blade root 3, as indicated schematically in FIG. 7.
  • the blade / disk sealing surfaces 15 can also be seen, which take over the function of the contact seal 91 of the prior art shown in FIG. 9.
  • FIG. 8 shows a view of the section 17 provided with sawtooth-like raised portions Retaining ring 1.
  • the retaining ring 1 is installed in an analog manner Way as described to Figures 1 to 6.
  • the retaining ring 1 is radial inwardly projecting sections 20 between two claws 21 each Rotor disk 2.
  • the blade root receptacles formed on the outer circumference of the rotor disk 2 12 have a fir tree-like toothing 13.
  • the rotor blades, not shown, in the blade root receptacles 12 is the Retaining ring 1 in a manner similar to a bayonet lock in the claws 21 in locked in the axial direction.
  • a locking device (not shown) is inserted into the Recesses between the inwardly projecting sections 20 for locking the retaining ring 1 introduced.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
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 true EP1120545A2 (fr) 2001-08-01
EP1120545A3 EP1120545A3 (fr) 2004-01-14
EP1120545B1 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)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1096107A3 (fr) * 1999-10-27 2004-05-12 Rolls-Royce Plc Dispositif de verrouillage
EP1357254A3 (fr) * 2002-04-16 2005-08-31 United Technologies Corporation Système de retenue axial et composants dudit système pour un rotor à aubes

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4846628A (en) 1988-12-23 1989-07-11 United Technologies Corporation Rotor assembly for a turbomachine
EP0463955B1 (fr) 1990-06-27 1994-09-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Dispositif de fixation d'une couronne de révolution sur un disque de turbomachine
EP0761930A1 (fr) 1995-08-24 1997-03-12 ROLLS-ROYCE plc Segments d'étanchéité et de rétention pour les aubes d'une turbomachine

Family Cites Families (14)

* 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
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.
GB2317652B (en) * 1996-09-26 2000-05-17 Rolls Royce Plc Seal arrangement

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4846628A (en) 1988-12-23 1989-07-11 United Technologies Corporation Rotor assembly for a turbomachine
EP0463955B1 (fr) 1990-06-27 1994-09-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Dispositif de fixation d'une couronne de révolution sur un disque de turbomachine
EP0761930A1 (fr) 1995-08-24 1997-03-12 ROLLS-ROYCE plc Segments d'étanchéité et de rétention pour les aubes d'une turbomachine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1096107A3 (fr) * 1999-10-27 2004-05-12 Rolls-Royce Plc Dispositif de verrouillage
EP1357254A3 (fr) * 2002-04-16 2005-08-31 United Technologies Corporation Système de retenue axial et composants dudit système pour un rotor à aubes

Also Published As

Publication number Publication date
EP1120545A3 (fr) 2004-01-14
EP1120545B1 (fr) 2006-10-18
DE50013633D1 (de) 2006-11-30
US6488473B1 (en) 2002-12-03
DE19960896A1 (de) 2001-06-28

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