EP1130217A1 - Fixation des aubes dans une turbomachine - Google Patents

Fixation des aubes dans une turbomachine Download PDF

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Publication number
EP1130217A1
EP1130217A1 EP00810175A EP00810175A EP1130217A1 EP 1130217 A1 EP1130217 A1 EP 1130217A1 EP 00810175 A EP00810175 A EP 00810175A EP 00810175 A EP00810175 A EP 00810175A EP 1130217 A1 EP1130217 A1 EP 1130217A1
Authority
EP
European Patent Office
Prior art keywords
blade
opening
feet
connecting piece
blades according
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
EP00810175A
Other languages
German (de)
English (en)
Other versions
EP1130217B1 (fr
Inventor
Michael Prof. Dr. Müller
Manfred Knorr
Jörg Dr. Pross
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 Schweiz AG
ABB Alstom Power NV
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 Alstom Schweiz AG, ABB Alstom Power NV filed Critical Alstom Schweiz AG
Priority to EP00810175A priority Critical patent/EP1130217B1/fr
Priority to DE50010348T priority patent/DE50010348D1/de
Priority to US09/794,050 priority patent/US20010019697A1/en
Publication of EP1130217A1 publication Critical patent/EP1130217A1/fr
Application granted granted Critical
Publication of EP1130217B1 publication Critical patent/EP1130217B1/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
    • 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

Definitions

  • the invention relates to blades with blade feet, which in the circumferential grooves Rotor of a turbomachine are attached. It particularly affects hers Fastening and securing against twisting and falling out of the groove.
  • a known way of moving blades on a rotor Assembling the turbo machine is anchoring using T-shaped shovel feet Circumferential grooves.
  • To mount the blades in a circumferential groove To enable the last bucket in particular is a certain assembly game required in the circumferential direction. When operating the machine it can happen that the blades move and form a gap that is large it is enough that a blade root rotates and falls out of the groove. This Problem is solved by reducing the assembly play by between the bucket feet spacers are tightly installed, so that Assembly game is filled out. After installing the spacers that is however, remaining play between the blade feet is often too small to be free to allow thermal expansions. Because of the strains arise forces that disturb the smooth running of the rotor and finally vibrations can cause.
  • the blade roots which are anchored in circumferential grooves, each have at least one depression or opening which runs in the circumferential direction and in which a connecting piece is arranged in each case, which connects at least two blade roots to one another to form a blade package.
  • the blade feet thus connected are prevented from twisting.
  • a connecting piece consists of a shaped piece of any cross section and is arranged in a recess or opening, the cross section of which is adapted to the shaped piece.
  • the depression or opening and the shaped piece are dimensioned such that the shaped piece lies in a depression or opening with little play and a displacement of a blade root and the shaped piece relative to one another is still possible.
  • the connecting piece consists of a shaped piece of rectangular cross section, which is inserted in a likewise rectangular depression on the side of the blade root which faces the rotor and the groove base.
  • the connecting piece consists of a round wire which is inserted into a drilling opening in the blade root. Again, the diameter of the opening and of the wire is dimensioned such that the blade root can be moved along the wire.
  • the blade feet each have a depression or opening which extends in the circumferential direction.
  • the blade feet each have two parallel in the circumferential direction running recesses or openings, in each of which a connecting piece is inserted or inserted.
  • a single connecting piece is arranged in one embodiment, which extends almost over the entire circumference of a groove and connects almost all blade roots in this groove to one another.
  • shorter connecting pieces are arranged in the depressions or openings, each of which connects two or more adjacent blade roots to one another to form a blade package.
  • Wells or openings are arranged short connecting pieces that Connect two blade feet to each other to form a pair of blade feet.
  • Side by side and parallel connectors are around one Blade root offset from each other by a first connector in a first recess or opening is inserted and a first and adjacent, connects the second blade root.
  • a second, parallel Connector is in the second, adjacent recess or opening inserted and connects the second and adjacent, third blade root, and immediately.
  • the foot of the last shovel is placed in a mounting gap provided for it the groove is screwed in and secured against rotation by a connecting piece interlocked with the adjacent blade feet by a connector in the depression or opening of the last blade root is pulled in.
  • blade attachment In a further embodiment of the blade attachment according to the invention is on the side of the blade root facing the groove base each in one Recess arranged a pressure spring, which causes displacement of the blade further reduced on the rotor, so that a gap formation and resulting aerodynamic disadvantages can be avoided.
  • FIG. 1 shows a blade root 1 which is anchored in an inverse T-shaped circumferential groove 2 in a rotor 3 of a turbomachine.
  • the blade root 1 has a recess 4 with a rectangular cross section on the side facing the groove base.
  • a connector 5 with a similar rectangular cross section is inserted with a little play in the recess.
  • the cross section of the recess in the blade root and the associated connecting piece is fundamentally arbitrary. Instead of the rectangular cross section for the depression and the connecting piece, for example, elliptical or round shapes can also be implemented.
  • a round recess 6 is arranged, in which a compression spring 7 is inserted, which additionally prevents the blade root from being displaced.
  • FIG. 1 shows a blade root 1 which is anchored in an inverse T-shaped circumferential groove 2 in a rotor 3 of a turbomachine.
  • the blade root 1 has a recess 4 with a rectangular cross section on the side facing the groove base.
  • FIG. 2 shows a view II of several adjacent blade feet 1 anchored in the circumferential groove, which are connected by a connecting piece 5. They form a package of blade feet which, thanks to their greater length, cannot twist in the circumferential groove, even if an assembly gap has arisen due to displacement of the blade feet during operation.
  • the connecting piece thus provides an anti-rotation device, which prevents the blades from falling out.
  • the blade roots along the entire circumferential groove are connected to one another to form several such blade root packages.
  • a connection of almost all blade roots, with the exception of the last or two last blades, can also be carried out.
  • FIG. 3 shows several blade roots anchored in a circumferential groove with a further arrangement of connecting pieces according to the invention.
  • the blade roots 1, 1a, 1b, 1c, 1d each have two parallel depressions on their side facing the groove bottom, which are arranged on both sides of the blade root center.
  • Short connecting pieces 5a, 5b, 5c are inserted in both recesses.
  • Each connecting piece connects a pair of blade roots, the connecting pieces arranged in parallel next to each other being offset by one blade root.
  • a connecting piece 5a is inserted in the first depression of the two blade feet 1a and 1b, connecting them and securing them against rotation.
  • a second connecting piece 5b is inserted in the second, parallel recess of the blade roots 1b and 1c, connecting this pair of blade roots.
  • FIG. 4a shows blade feet 11 and 12, which are spaced apart from the blade feet 13 and 14 by a mounting gap in the circumferential groove 2.
  • the blade roots 11 and 12 are connected to one another by connecting pieces 5d and 5e. They both extend over several blade feet, for example.
  • the blade feet 13 and 14 are connected and secured to one another by means of connecting pieces 5f and 5g.
  • FIG. 4a shows blade feet 11 and 12, which are spaced apart from the blade feet 13 and 14 by a mounting gap in the circumferential groove 2.
  • the blade roots 11 and 12 are connected to one another by connecting pieces 5d and 5e. They both extend over several blade feet, for example.
  • the blade feet 13 and 14 are connected and secured to one another by means of connecting pieces 5f and 5g.
  • FIGS. 4c-e shows the same circumferential groove 2 with the last blade, the blade root 15 of which has been anchored in the assembly gap of the groove 2.
  • the depressions 4 of the blade root 15 are still empty here, so the blade root is not yet secured against rotation.
  • the locking of this last blade root proceeds as follows according to FIGS. 4c-e: The blade root 12 is first pushed over the remaining gap next to the blade root 15, so that the ends of the connecting pieces 5d and 5e become visible. The connecting piece 5d is then pulled in the same direction until its end comes to rest in the recess 4 of the blade root 12.
  • the assembly and locking is completed by slightly increasing the gaps between all the blade feet in the circumferential groove so that the gap that remains after the last blade has been installed is distributed over the entire circumferential groove.
  • the intermediate pieces are a known component and are not shown here. They are dimensioned so that they reduce the assembly play and no longer a larger gap can form during turbine operation, which could disturb the smooth running of the rotor. Thanks to the anti-rotation device, however, they no longer have to completely fill up the assembly play, so that there is a sufficiently large free space between the blade feet, in which thermal expansion is freely allowed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00810175A 2000-03-01 2000-03-01 Fixation des aubes dans une turbomachine Expired - Lifetime EP1130217B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP00810175A EP1130217B1 (fr) 2000-03-01 2000-03-01 Fixation des aubes dans une turbomachine
DE50010348T DE50010348D1 (de) 2000-03-01 2000-03-01 Befestigung von Laufschaufeln in einer Turbomaschine
US09/794,050 US20010019697A1 (en) 2000-03-01 2001-02-28 Fastening rotor blades in a turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00810175A EP1130217B1 (fr) 2000-03-01 2000-03-01 Fixation des aubes dans une turbomachine

Publications (2)

Publication Number Publication Date
EP1130217A1 true EP1130217A1 (fr) 2001-09-05
EP1130217B1 EP1130217B1 (fr) 2005-05-18

Family

ID=8174578

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00810175A Expired - Lifetime EP1130217B1 (fr) 2000-03-01 2000-03-01 Fixation des aubes dans une turbomachine

Country Status (3)

Country Link
US (1) US20010019697A1 (fr)
EP (1) EP1130217B1 (fr)
DE (1) DE50010348D1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1707746A1 (fr) * 2005-03-18 2006-10-04 Siemens Aktiengesellschaft Composant de turbomachine, turbomachine et procédé de fixation d'aubes sur un composant
EP2320030A1 (fr) * 2009-11-10 2011-05-11 Alstom Technology Ltd Rotor et aube de rotor pour une turbomachine axiale
CH702203A1 (de) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor für eine axial durchströmte turbomaschine sowie laufschaufel für einen solchen rotor.
EP2562356A1 (fr) * 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Agencement de pales
EP4209658A1 (fr) * 2022-01-05 2023-07-12 General Electric Company Composant de compresseur avec ressort de retenue

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005010323A1 (fr) * 2003-07-26 2005-02-03 Alstom Technology Ltd Systeme de fixation des emplantures d'aubes d'une turbomachine
US7474643B2 (en) * 2003-10-02 2009-01-06 Qualcomm Incorporated Systems and methods for communicating control data using multiple slot formats
EP2045444B1 (fr) * 2007-10-01 2015-11-18 Alstom Technology Ltd Aube de rotor, procédé de fabrication d'une aube de rotor, et compresseur avec une telle aube
DE102010053141B4 (de) * 2009-12-07 2018-10-11 General Electric Technology Gmbh Turbinenaggregat mit möglicher Überdrehung des Fußes einer Schaufel bis zum Einbau einer letzten Schaufel
GB201203303D0 (en) 2012-02-27 2012-04-11 Rolls Royce Plc Balancing of rotor

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE333353C (de) * 1920-04-16 1921-03-18 Osthoff Fa Walter Gewebe-Gassengmaschine
DE459203C (de) * 1928-04-27 E H Hans Holzwarth Dr Ing Einrichtung zur Schaufelbefestigung fuer Dampf- und Gasturbinen
GB614678A (en) * 1946-07-19 1948-12-20 Parsons C A & Co Ltd Improvements in or relating to turbine blading or the like
US2809801A (en) * 1952-04-18 1957-10-15 Ingersoll Rand Co Turbine rotor construction
DE1751819B1 (de) * 1968-07-26 1971-01-21 Sulzer Ag Läufer für Str¦mungsmaschinen
EP0530097A1 (fr) * 1991-08-28 1993-03-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Rotor de turbomachine à positionnement angulaire amélioré des aubes
US5509784A (en) * 1994-07-27 1996-04-23 General Electric Co. Turbine bucket and wheel assembly with integral bucket shroud

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE459203C (de) * 1928-04-27 E H Hans Holzwarth Dr Ing Einrichtung zur Schaufelbefestigung fuer Dampf- und Gasturbinen
DE333353C (de) * 1920-04-16 1921-03-18 Osthoff Fa Walter Gewebe-Gassengmaschine
GB614678A (en) * 1946-07-19 1948-12-20 Parsons C A & Co Ltd Improvements in or relating to turbine blading or the like
US2809801A (en) * 1952-04-18 1957-10-15 Ingersoll Rand Co Turbine rotor construction
DE1751819B1 (de) * 1968-07-26 1971-01-21 Sulzer Ag Läufer für Str¦mungsmaschinen
EP0530097A1 (fr) * 1991-08-28 1993-03-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Rotor de turbomachine à positionnement angulaire amélioré des aubes
US5509784A (en) * 1994-07-27 1996-04-23 General Electric Co. Turbine bucket and wheel assembly with integral bucket shroud

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1707746A1 (fr) * 2005-03-18 2006-10-04 Siemens Aktiengesellschaft Composant de turbomachine, turbomachine et procédé de fixation d'aubes sur un composant
EP2320030A1 (fr) * 2009-11-10 2011-05-11 Alstom Technology Ltd Rotor et aube de rotor pour une turbomachine axiale
CH702203A1 (de) * 2009-11-10 2011-05-13 Alstom Technology Ltd Rotor für eine axial durchströmte turbomaschine sowie laufschaufel für einen solchen rotor.
US8770938B2 (en) 2009-11-10 2014-07-08 Alstom Technology Ltd Rotor for an axial-throughflow turbomachine and moving blade for such a rotor
EP2562356A1 (fr) * 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Agencement de pales
WO2013026735A1 (fr) * 2011-08-24 2013-02-28 Siemens Aktiengesellschaft Agencement d'aubes
CN104053858B (zh) * 2011-08-24 2016-02-17 西门子公司 叶片装置
US9708919B2 (en) 2011-08-24 2017-07-18 Siemens Aktiengesellschaft Blade arrangement
EP4209658A1 (fr) * 2022-01-05 2023-07-12 General Electric Company Composant de compresseur avec ressort de retenue

Also Published As

Publication number Publication date
EP1130217B1 (fr) 2005-05-18
DE50010348D1 (de) 2005-06-23
US20010019697A1 (en) 2001-09-06

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