EP1698758A2 - Fermeture de rotor à fente axiale - Google Patents

Fermeture de rotor à fente axiale Download PDF

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Publication number
EP1698758A2
EP1698758A2 EP20060110011 EP06110011A EP1698758A2 EP 1698758 A2 EP1698758 A2 EP 1698758A2 EP 20060110011 EP20060110011 EP 20060110011 EP 06110011 A EP06110011 A EP 06110011A EP 1698758 A2 EP1698758 A2 EP 1698758A2
Authority
EP
European Patent Office
Prior art keywords
halves
rotor
wedge
clip
blades
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
EP20060110011
Other languages
German (de)
English (en)
Other versions
EP1698758A3 (fr
EP1698758B1 (fr
Inventor
René Bachofner
Wolfgang Kappis
Kurt Rubischon
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1698758A2 publication Critical patent/EP1698758A2/fr
Publication of EP1698758A3 publication Critical patent/EP1698758A3/fr
Application granted granted Critical
Publication of EP1698758B1 publication Critical patent/EP1698758B1/fr
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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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

Definitions

  • the invention relates to the field of thermal turbomachinery, in particular it relates to a rotor end for rotors according to the preamble of claim 1. Furthermore, an assembly method for a rotor according to the invention is given.
  • Thermal turbomachinery with axial turbines and axial compressors have a rotor equipped with blades and a stator, are mounted in the guide vanes for flow guidance.
  • the stationary guide vanes have the task of directing the flow of the gas medium to be compressed or to be relaxed in such a way onto the rotating running blading of the respective compressor stage or the respective turbine stage that the energy conversion takes place with the best possible efficiency.
  • Both blades and vanes essentially comprise a profiled airfoil and a blade root.
  • grooved in the stator and on the rotor shaft are the Feet of the blades inserted and locked there.
  • compressor blade rows of gas turbine rotors are arranged in circumferential grooves, which often have a T-shaped cross-section.
  • blades and spacers alternate here.
  • a special solution must be found for the last blades to be mounted, since then the remaining filling opening for a complete intermediate piece is too small. This residual opening is therefore filled with a so-called rotor-end.
  • the known rotor closure consists of a halved intermediate piece, that is to say of two halves split circumferentially with respect to the rotor, and a wedge with the aid of which the end halves in the rotor are caulked in the circumferential direction.
  • the two end halves each have a straight lateral surface.
  • the side surfaces mentioned are opposite in the installed state, in which case the wedge is located between them.
  • the formed at the top of the wedge flaps are bent into appropriate undercuts in the side surfaces of the end halves and the wedge and thus the entire tail secured against escaping.
  • EP 1 215 367 A2 and DE 103 10 432 A1 describe proposed solutions in which the forces in the adjacent blades, i. be initiated in the circumferential direction.
  • the solutions presented here are complex and costly in assembly and production.
  • the object of the invention is therefore to avoid the aforementioned disadvantages of the prior art.
  • the invention is based on the technical problem of providing a rotor end which, if possible, exerts no axial forces on the rotor, thereby avoiding the occurrence of disturbing rotor vibrations caused by axial forces.
  • the rotor end according to the invention is characterized in that a clamp is arranged in the residual gap, which accommodates the forces of the two end halves and two shim halves arranged between the end halves and clamped with the wedge.
  • an advantageous development of the invention provides that the opposing shims halves each have an undercut, in the arranged on the upper side of the wedge key flaps are hineinsp Schwarzbar. As a result, the wedge is secured in the package against flying out due to centrifugal forces.
  • a further advantageous embodiment of the invention provides that the supplement halves have over the undercuts Beilagelappen, which are drivable on the spread keys. This results in an additional securing of the wedge, since a drift apart of the side shells and associated exposure of the keys is safely avoided.
  • the package of the two supplements and the wedge is secured by flanged halves tail. This is it also an additional fuse that intervenes in case of failure of one of the previous fuses.
  • the clamp is designed as a substantially rectangular plate with a Lägsschlitz and U-shaped cross-section.
  • a development of the invention provides that the U-legs of the clip engage in corresponding grooves of the end halves.
  • the staple is in axial, i. mounted in the rotor longitudinal direction in the circumferential groove.
  • the clip is engaged with both the half shells and the half halves. Due to the centrifugal forces, the U-legs are additionally pressed into the corresponding grooves of the end halves.
  • a further advantageous embodiment of the present invention provides that the clamp is made of a chromium-molybdenum alloy.
  • a method for mounting an axially divided rotor closure which has two end halves, two side halves, a clamp and a wedge, comprises the following steps: inserting the clamp into the circumferential groove; Mounting the two end halves, which are engaged with the clip; Assembly of the two side halves, where these are also engaged with the clip; Tension the two side halves in the axial direction by inserting the wedge. Disassembly is in reverse order. The wedges are drilled out.
  • An advantageous development of the method for mounting an axially divided rotor closure further comprises the following steps: securing the wedge by Aufpreitzen the upper Keillappen in recesses of the side halves and Umbörteln of lobes of the side halves; Secure the sides of the garnish and fold over with cloths of the end halves. When disassembling the flanged cloths are usually ground away.
  • FIG. 1 shows a section in the rotor longitudinal direction through a rotor-end 1 according to the invention after installation in a compressor rotor.
  • FIG. 2 shows a section in the circumferential direction along the line II - II from FIG. 1.
  • FIG. 1 and FIG. 2 represents a partial section of a rotating rotor groove 3 of a compressor stage.
  • the groove 3 are already all upsetting blades and intermediate pieces (not shown in this section) and the two closing blades 4, 4 mounted.
  • the closing blades 4, 4 differ from the regular compression blades only in that the bulge on the inlet and outlet side is removed.
  • the axially separated rotor closure has two end halves 9, 9, a first side half 5, a second side half 6, a bracket 8 and a wedge 7 made of chrome nickel steel.
  • the package formed from the shims 5, 6 and the wedge 7, the clamp 8 and the end halves 9, 9 together have a comparable mass with an intermediate piece.
  • FIG. 3 shows a side view of a closure half 9, 9 according to the invention
  • FIG. 4 shows a plan view of the two closure halves
  • Fig. 5 shows a section along the line V -V of Figure 4.
  • the two end halves 9, 9 are made in the present embodiment of a chromium-nickel-molybdenum alloy.
  • the outer contour of the closing half 9 is designed so that it corresponds to the T-shaped cross-section of the circumferential groove 3 of the rotor disk 2.
  • the elongated webs or lobes 10 are shown at the top of the end half 9, which are crimped at the end of assembly.
  • FIG. 6 shows a side view of two supplement halves 5, 6 according to the invention, which in the present exemplary embodiment are made of a chromium-nickel-molybdenum alloy.
  • the bracket 8 is the component which absorbs the axial forces in the present invention and thus provides for the relief of the rotor groove.
  • the bracket 8 is a plan view of a substantially rectangular metal profile with a central longitudinal slot or a central elongated recess 12.
  • the bracket 8 has a U-profile in cross-section. Through the recess 12 and the U-legs 13, the clip with the end halves 9.9 and the supplement halves 5, 6 is engaged. Together with the wedge 7 so a fastening dressing is formed.
  • Fig. 7 shows a detail plan view of a clip 8 according to the invention.
  • Fig. 8 shows a cross section through the clip 8 along the line VIII - VIII from Figure 7.
  • the bracket 8 is made in the present embodiment of a chromium molybdenum alloy.
  • a circumferential groove 3 is inserted with a substantially T-shaped cross-section in a rotor disk 2.
  • upsetting blades and intermediate pieces 15 are alternately mounted until the two closing blades 4 are mounted, between which no regular intermediate piece 15 can be mounted because of the small space in the residual gap.
  • the wedges 7 are spread in the shims 18, 18, which together form a heart shape in side view.
  • the sheath tabs 16, 16 on the heart shape are then, as shown in Figure 10, driven over the spread wedge 7.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06110011.1A 2005-02-23 2006-02-16 Fermeture de rotor à fente axiale Active EP1698758B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH3222005 2005-02-23

Publications (3)

Publication Number Publication Date
EP1698758A2 true EP1698758A2 (fr) 2006-09-06
EP1698758A3 EP1698758A3 (fr) 2013-03-27
EP1698758B1 EP1698758B1 (fr) 2015-11-11

Family

ID=34974750

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06110011.1A Active EP1698758B1 (fr) 2005-02-23 2006-02-16 Fermeture de rotor à fente axiale

Country Status (2)

Country Link
US (1) US7338258B2 (fr)
EP (1) EP1698758B1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2045444A1 (fr) 2007-10-01 2009-04-08 ALSTOM Technology Ltd Aube de rotor, procédé de fabrication d'une aube de rotor, et compresseur avec une telle aube
CH702204A1 (de) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor für eine axial durchströmte turbomaschine sowie gasturbine für solchen rotor.
EP3159483A1 (fr) * 2015-10-22 2017-04-26 Siemens Aktiengesellschaft Dispositif de fixation d'aubes mobiles d'une turbomachine thermique
CN108791817A (zh) * 2018-06-26 2018-11-13 李荣旭 一种具有低阻力性能的飞行器螺旋桨及其组装方法

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8162615B2 (en) * 2009-03-17 2012-04-24 United Technologies Corporation Split disk assembly for a gas turbine engine
US8545184B2 (en) * 2010-01-05 2013-10-01 General Electric Company Locking spacer assembly
US8517688B2 (en) * 2010-09-21 2013-08-27 General Electric Company Rotor assembly for use in turbine engines and methods for assembling same
US10465699B2 (en) * 2017-01-26 2019-11-05 DOOSAN Heavy Industries Construction Co., LTD Compressor blade locking mechanism in disk with tangential groove

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH349624A (de) * 1957-03-05 1960-10-31 Oerlikon Maschf Axiale Strömungsmaschine
DE1751819B1 (de) * 1968-07-26 1971-01-21 Sulzer Ag Läufer für Str¦mungsmaschinen
EP1215367A2 (fr) * 2000-12-16 2002-06-19 ALSTOM Power N.V. Dispositif de fixation des aubes de turbomachine
EP1457642A2 (fr) * 2003-03-11 2004-09-15 Alstom Technology Ltd Dispositif de fixation d'aubes sur un rotor

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL56668C (fr) 1940-06-12
US2406703A (en) * 1944-06-08 1946-08-27 Allis Chalmers Mfg Co Turbine blade locking apparatus
FR974989A (fr) 1948-09-17 1951-02-28 Verrou pour l'aubage des rotors en forme de tambour de compresseurs axiaux et de turbines à vapeur ou à gaz
US3252687A (en) * 1965-02-01 1966-05-24 Gen Motors Corp Rotor blade locking
EP1028231B1 (fr) 1999-02-12 2003-09-03 ALSTOM (Switzerland) Ltd Fixation d'aubes de rotor d'une turbomachine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH349624A (de) * 1957-03-05 1960-10-31 Oerlikon Maschf Axiale Strömungsmaschine
DE1751819B1 (de) * 1968-07-26 1971-01-21 Sulzer Ag Läufer für Str¦mungsmaschinen
EP1215367A2 (fr) * 2000-12-16 2002-06-19 ALSTOM Power N.V. Dispositif de fixation des aubes de turbomachine
EP1457642A2 (fr) * 2003-03-11 2004-09-15 Alstom Technology Ltd Dispositif de fixation d'aubes sur un rotor

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2045444A1 (fr) 2007-10-01 2009-04-08 ALSTOM Technology Ltd Aube de rotor, procédé de fabrication d'une aube de rotor, et compresseur avec une telle aube
US8257047B2 (en) 2007-10-01 2012-09-04 Alstom Technology Ltd. Rotor blade, method for producing a rotor blade, and compressor with a rotor blade
CH702204A1 (de) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor für eine axial durchströmte turbomaschine sowie gasturbine für solchen rotor.
EP3159483A1 (fr) * 2015-10-22 2017-04-26 Siemens Aktiengesellschaft Dispositif de fixation d'aubes mobiles d'une turbomachine thermique
CN108791817A (zh) * 2018-06-26 2018-11-13 李荣旭 一种具有低阻力性能的飞行器螺旋桨及其组装方法
CN108791817B (zh) * 2018-06-26 2021-07-20 深圳市飞翼创新有限公司 一种具有低阻力性能的飞行器螺旋桨及其组装方法

Also Published As

Publication number Publication date
EP1698758A3 (fr) 2013-03-27
US20060188373A1 (en) 2006-08-24
US7338258B2 (en) 2008-03-04
EP1698758B1 (fr) 2015-11-11

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