EP2149677A1 - Dispositif de fixation destiné à la fixation d'une pale de rotor sur une turbomachine - Google Patents

Dispositif de fixation destiné à la fixation d'une pale de rotor sur une turbomachine Download PDF

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Publication number
EP2149677A1
EP2149677A1 EP08013704A EP08013704A EP2149677A1 EP 2149677 A1 EP2149677 A1 EP 2149677A1 EP 08013704 A EP08013704 A EP 08013704A EP 08013704 A EP08013704 A EP 08013704A EP 2149677 A1 EP2149677 A1 EP 2149677A1
Authority
EP
European Patent Office
Prior art keywords
blade
abutment
rotor
retaining groove
blade root
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
EP08013704A
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German (de)
English (en)
Other versions
EP2149677B1 (fr
Inventor
François Dr. Benkler
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.)
Siemens AG
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Siemens AG
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Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP08013704A priority Critical patent/EP2149677B1/fr
Priority to AT08013704T priority patent/ATE523659T1/de
Publication of EP2149677A1 publication Critical patent/EP2149677A1/fr
Application granted granted Critical
Publication of EP2149677B1 publication Critical patent/EP2149677B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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

Definitions

  • the invention relates to a fastening arrangement for attachment of a blade to a rotor of a turbomachine, having a holding portion arranged in a mounting portion, which has two opposite openings for insertion of the blade and in which a blade root of the blade is inserted, wherein between a groove bottom of the retaining groove and a lower side of the blade root a tensioning device is provided.
  • Stationary gas turbines have as a component a compressor through which the air needed for combustion of a fuel can be compressed to a high pressure.
  • a compressor of a stationary gas turbine is designed as an axial flow compressor.
  • the compressed air within its flow path thus flows in the axial direction of the rotor mounted therein, wherein the rotor blades arranged on the rotor blades and the casings attached to the housing form pairs of compressor stages, which are arranged in cascade.
  • axial compressors having fourteen or twenty compressor stages are known. Their front compressor stages, ie the inflow-side compressor stages, have comparatively large airfoils, whereas their rear, outflow-side compressor stages have comparatively short airfoils.
  • the front blades of the compressor usually have a dovetail-shaped blade root for attachment, which is inserted into corresponding retaining grooves.
  • the retaining grooves arranged in the rotor are distributed along the circumference of a rotor disk and extend in each case in the axial direction or slightly inclined thereto.
  • the blades sit safely and backlash in the retaining grooves, as due to the centrifugal forces acting on them at rated speed, they strongly strive outwards and thus rest rigidly against the support flanks of the retaining groove.
  • the blade root is designed with slight excess to the retaining groove.
  • this has the disadvantage that the blades can be difficult to be inserted into the retaining groove during assembly.
  • the object of the invention is therefore to provide a fastening arrangement of the type mentioned in the always a biased seat of the blade is reliably ensured in the holding for each operating condition.
  • the tensioning device comprises a tension rod which extends parallel to the extension of the retaining groove and has a thread at its first end, a first abutment screwed onto the thread and a second abutment at its second end opposite the first end comprises, wherein between the two abutments, a dowel is provided, which is compressible by rotating the tie rod by the then abutting each other to abutment.
  • the invention thus comes off the idea that the biasing force required in the radial direction already has to be generated with the insertion of the blade into the retaining groove.
  • the invention proposes, however, to provide a slight clearance between the blade root and retaining groove, so that the blade can be relatively easily inserted during assembly or during maintenance in the holding or taken out of this.
  • a tensioning device is inserted between the underside of the blade root and the groove base of the retaining groove only after insertion of the blade, by means of which a bias for the heat-expansion-tolerant attachment of the blade to the latter can be applied.
  • the novel clamping device for rattle avoidance or to prevent relative movement of the blades within the retaining groove comprises a dowel arranged between the underside of the blade root and the groove base of the retaining groove, which can be compressed axially. By compressing the dowel this deviates laterally, so that a force is generated, which presses the blade root in the radial direction. However, since the blade root is held positively in the radial direction by the retaining groove, can be generated by the evasive dowel a bias on the blade root, which presses it reliably into the retaining groove. This allows a backlash-free seat of the blade within the retaining groove, regardless of the speed of the rotor.
  • the bias is chosen so that even heat-related strains in the material of the mounting assembly, ie in the material surrounding the retaining groove, does not lead to a playful seat of the blade in the retaining groove, even if the rotor only at a reduced speed - ie Starting the gas turbine or during rotary operation - is driven and the centrifugal load on the blade is only comparatively low.
  • the tensioning device comprises a tension rod, a first abutment which can be screwed to the tension rod, a second abutment and the dowel arranged therebetween.
  • the first abutment which is secured against turning, is moved in the direction of the second abutment, during which the dowel arranged between the abutments is compressed and thereby evades in a direction transverse to the direction of displacement of the first abutment.
  • the dowel is pressed on the one hand against the groove bottom of the retaining groove and on the other hand against the underside of the blade root, whereby a bias voltage in the radial direction of the rotor can be built up and further increased with continued tensioning, so that even when in (rotary) operation still existing thermal expansion a sufficient bias is maintained, which ensures a play-free seat of the blade within the retaining groove.
  • the invention thus enables the introduction of biasing forces acting in the radial direction of the rotor after the actual assembly of the compressor blades into the retaining groove.
  • the effort when inserting the blade can be minimized in the holding.
  • the first abutment for preventing rotation on a contour which corresponds at least partially to the contour of the underside of the blade root and / or the contour of the retaining groove.
  • the contour of the abutment serves as its rotation.
  • the second abutment is preferably formed as a locking disc, on the one hand, i. radially outward, with the blade root and on the other hand, i. radially inward with the rotor disk is respectively engaged.
  • a further locking disc may be provided which engages on the one hand with the blade root and on the other hand with the retaining groove. This also makes it possible to prevent a displacement of the blade root along the retaining groove, which ensures a secure axial seating of the blade on the rotor.
  • the further locking disc has an opening into which the tension rod projects at least partially.
  • the anchor can be designed in the manner of a spring shaft or as a spring element. During the tensioning process this can dodge in the direction of the underside of the blade root and in the direction of the groove bottom of the retaining groove.
  • a rotor for a turbomachine has at least one shaft collar, which has a plurality of fastening arrangements according to the invention as a fastening section on its circumference.
  • the rotor is modular, so that the shaft collar can be formed by a rotor disk.
  • the retaining grooves may extend along the axial direction of the rotor or slightly inclined thereto, so that the two opposing openings of the retaining groove are each arranged on the front side on the shaft collar or on the rotor disk.
  • a fastening arrangement 10 for fastening a rotor blade 12 to a rotor 14 of a turbomachine, preferably an axial compressor, is disclosed in US Pat FIG. 1 shown schematically in a longitudinal section.
  • the rotor 14 has a machine axis 16 about which the rotor 14 is rotatably mounted in the turbomachine.
  • a shaft collar in the form of a rotor disk 18 is provided, which may be one of a plurality of rotor disks of the rotor 14.
  • the Rotor disks 18 are axially adjacent to each other - stacked - and connected to each other by a centrally extending through them by tie rods in a known manner.
  • the retaining groove 20 has two opposing openings 22, 24, through which the blade 12 can be inserted into the retaining groove 20.
  • the blade 12 comprises an airfoil 26 and a blade root 28 arranged thereon.
  • the blade root 28 is viewed in cross section (FIG. FIG. 2 ) formed dovetail-shaped, wherein the retaining groove 20 is at least partially formed corresponding to the dovetail shape of the blade root 28.
  • the dovetail-shaped blade root 28 has two flanks 29 extending in axial directions, which bear against corresponding flanks 31 of the retaining groove 28. By the dovetail shape, the blade 12 is held in the radial direction R in the retaining groove 20.
  • the blade root 28 has an underside 30, which is opposite to a groove bottom 32 of the retaining groove 20 at a distance.
  • a clamping device 34 according to the invention is arranged, which comprises a between the two openings 22, 24 extending tie rod 36 which is provided with a thread.
  • the tensioning device 34 comprises an in FIG. 1 further left illustrated first abutment 38 at a first end 40 of the tie rod 36 and at a first end 40 opposite the second end 42 plugged second abutment 44. Between the two abutments 38, 44 is a tubular wavy dowel 46 is provided in longitudinal section.
  • the second end 42 of the tie rod 36 extends through the second abutment 44 therethrough and has a bent end piece, through which the tension rod 36 can be rotated.
  • the tension rod 36 By the rotation of the tension rod 36, the first abutment 38 is moved in the direction of the second abutment 44, whereby the between them arranged on both sides open dowel 46 is compressed and compressed. Due to the compression of the dowel 46 tries this laterally to escape the direction of displacement of the first abutment 38.
  • the dowel 46 is thus pressed on the one hand in the direction of the bottom 30 of the blade root 28 and on the other hand in the direction of the groove bottom 32 of the retaining groove 20. In this way, a biasing force acting in the radial direction R can be generated by which the flanks 29 of the blade root 28 are pressed against the corresponding flanks 31 of the retaining groove 20.
  • the first abutment 38 has an outer contour which corresponds at least partially to the contour of the underside 30 of the blade root 28 and / or the contour of the groove bottom 32 of the retaining groove 20.
  • the abutment 38 moves along the axial direction to the second abutment 44 back.
  • a locking disc 48 is provided at that opening 22, on which the first abutment 38 is provided.
  • the locking disc 48 has a centrally located opening 50, at which the first end 40 of the tension rod 36 extends into and thus can be securely held in position.
  • Both the locking disc 48 and the second abutment 44 may be formed in the retaining groove 20 for axial securing of the blade 12.
  • securing grooves 52 are provided in the region of the underside 30 in the area of the openings 22, 24 arranged in the blade root 28 . These locking grooves 52 are opposite in the groove bottom 32 of the retaining groove 20 corresponding locking grooves 54 are arranged. Both the lock washer 48 and the second abutment 44 are engaged with the lock grooves 52, 54 so that the blade 12 is secured against displacement within the retainer groove 20 in the axial direction, that is, along the machine axis 16.
  • FIG. 1 and the in FIG. 2 shown mounting arrangement for each provided on the circumference of the rotor disk 18 blade 12 is provided.
  • the blade 12 is inserted with its blade root 28 into the retaining groove 20.
  • a partially preassembled clamping device 34 consisting of pull rod 36, first abutment 38 and the dowel 46 open on both sides in the space between the bottom 30 of the blade root 28 and groove bottom 32 of the retaining groove 20 through one of the two openings 22, 24 is inserted.
  • the second abutment 44 is inserted into the securing grooves 52, 54, after which the second end 42 of the tension rod 36 is bent.
  • a completely pre-assembled clamping device can be used.
  • the locking disc 48 can be inserted into the opening 22, on which the first abutment 38 is arranged.
  • the second abutment 38 can be moved in the direction of the first abutment 44, whereby the dowel 46 arranged therebetween is compressed.
  • the dowel 46 may be made for example of a temperature-resistant plastic, but also of metal.
  • the dowel 46 is made of a resilient metal.
  • the invention thus relates to a total of a mounting assembly 10 for attachment of a blade 12 to a rotor 14 of a turbomachine, wherein in axial holding grooves 20 between the bottom 30 of the blade root 28 and the groove bottom 32 of the retaining groove 20, a novel clamping device 34 is provided.
  • the clamping device 34 according to the invention comprises a parallel to the extension of the retaining groove 20 extending tie rod 36 with a thread.
  • a rotationally secured first abutment 38 is screwed and at its second end 40, a second abutment 44.
  • a dowel 46 is provided, which escapes by the Auffactzube admire the abutment 38, 44 in the radial direction of the rotor 14 and In this case, the blade 12 with the aid of a bias backlash and stretch tolerant fixed in the retaining groove 20, even for a provided after the operation of the gas turbine rotary operation.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP08013704A 2008-07-30 2008-07-30 Dispositif de fixation destiné à la fixation d'une pale de rotor sur une turbomachine Not-in-force EP2149677B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP08013704A EP2149677B1 (fr) 2008-07-30 2008-07-30 Dispositif de fixation destiné à la fixation d'une pale de rotor sur une turbomachine
AT08013704T ATE523659T1 (de) 2008-07-30 2008-07-30 Befestigungsanordnung zur befestigung von einer laufschaufel an einem rotor einer turbomaschine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08013704A EP2149677B1 (fr) 2008-07-30 2008-07-30 Dispositif de fixation destiné à la fixation d'une pale de rotor sur une turbomachine

Publications (2)

Publication Number Publication Date
EP2149677A1 true EP2149677A1 (fr) 2010-02-03
EP2149677B1 EP2149677B1 (fr) 2011-09-07

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EP08013704A Not-in-force EP2149677B1 (fr) 2008-07-30 2008-07-30 Dispositif de fixation destiné à la fixation d'une pale de rotor sur une turbomachine

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EP (1) EP2149677B1 (fr)
AT (1) ATE523659T1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010015404A1 (de) * 2010-04-19 2011-10-20 Mtu Aero Engines Gmbh Verfahren zur Reparatur einer Rotoranordnung einer Turbomaschine, Ringelement für eine Rotoranordnung einer Turbomaschine sowie Rotoranordnung für eine Turbomaschine
WO2015057424A1 (fr) * 2013-10-18 2015-04-23 Siemens Aktiengesellschaft Ressort de racine de pale réglable pour fixation de pale de turbine dans une turbomachine
WO2021008815A1 (fr) * 2019-07-18 2021-01-21 Siemens Energy Global GmbH & Co. KG Couronne d'aube servant à une turbomachine axiale
CN112943685A (zh) * 2021-03-10 2021-06-11 哈电发电设备国家工程研究中心有限公司 一种拉杆式叶根连接结构
CN113931701A (zh) * 2021-09-30 2022-01-14 中国长江动力集团有限公司 一种末叶片固定方法及固定结构

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0069620A1 (fr) * 1981-06-25 1983-01-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif d'amortissement d'aubes de turbomachines, notamment de soufflantes
US4836749A (en) 1988-02-19 1989-06-06 Westinghouse Electric Corp. Pre-load device for a turbomachine rotor
US5123813A (en) 1991-03-01 1992-06-23 General Electric Company Apparatus for preloading an airfoil blade in a gas turbine engine
US5984639A (en) * 1998-07-09 1999-11-16 Pratt & Whitney Canada Inc. Blade retention apparatus for gas turbine rotor
EP1905957A1 (fr) 2006-09-27 2008-04-02 Siemens Aktiengesellschaft Dispositif de fixation d'une aube de turbine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0069620A1 (fr) * 1981-06-25 1983-01-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif d'amortissement d'aubes de turbomachines, notamment de soufflantes
US4453891A (en) 1981-06-25 1984-06-12 S.N.E.C.M.A. Vibration damping device, especially for a blade of a turbojet engine
US4836749A (en) 1988-02-19 1989-06-06 Westinghouse Electric Corp. Pre-load device for a turbomachine rotor
US5123813A (en) 1991-03-01 1992-06-23 General Electric Company Apparatus for preloading an airfoil blade in a gas turbine engine
US5984639A (en) * 1998-07-09 1999-11-16 Pratt & Whitney Canada Inc. Blade retention apparatus for gas turbine rotor
EP1905957A1 (fr) 2006-09-27 2008-04-02 Siemens Aktiengesellschaft Dispositif de fixation d'une aube de turbine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010015404A1 (de) * 2010-04-19 2011-10-20 Mtu Aero Engines Gmbh Verfahren zur Reparatur einer Rotoranordnung einer Turbomaschine, Ringelement für eine Rotoranordnung einer Turbomaschine sowie Rotoranordnung für eine Turbomaschine
DE102010015404B4 (de) * 2010-04-19 2012-02-16 Mtu Aero Engines Gmbh Verfahren zur Reparatur einer Rotoranordnung einer Turbomaschine, Ringelement für eine Rotoranordnung einer Turbomaschine sowie Rotoranordnung für eine Turbomaschine
US8899919B2 (en) 2010-04-19 2014-12-02 Mtu Aero Engines Gmbh Method for repairing a rotor system of a turbomachine, annular element for a rotor system of a turbomachine, and rotor system for a turbomachine
WO2015057424A1 (fr) * 2013-10-18 2015-04-23 Siemens Aktiengesellschaft Ressort de racine de pale réglable pour fixation de pale de turbine dans une turbomachine
US9739160B2 (en) 2013-10-18 2017-08-22 Siemens Aktiengesellschaft Adjustable blade root spring for turbine blade fixation in turbomachinery
WO2021008815A1 (fr) * 2019-07-18 2021-01-21 Siemens Energy Global GmbH & Co. KG Couronne d'aube servant à une turbomachine axiale
CN112943685A (zh) * 2021-03-10 2021-06-11 哈电发电设备国家工程研究中心有限公司 一种拉杆式叶根连接结构
CN113931701A (zh) * 2021-09-30 2022-01-14 中国长江动力集团有限公司 一种末叶片固定方法及固定结构

Also Published As

Publication number Publication date
ATE523659T1 (de) 2011-09-15
EP2149677B1 (fr) 2011-09-07

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