EP3418498A1 - Segment ressort de precontrainte, rotor et procédé de fabrication associés - Google Patents

Segment ressort de precontrainte, rotor et procédé de fabrication associés Download PDF

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Publication number
EP3418498A1
EP3418498A1 EP17177364.1A EP17177364A EP3418498A1 EP 3418498 A1 EP3418498 A1 EP 3418498A1 EP 17177364 A EP17177364 A EP 17177364A EP 3418498 A1 EP3418498 A1 EP 3418498A1
Authority
EP
European Patent Office
Prior art keywords
spring segment
biasing spring
turbine
turbine blade
segment
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.)
Withdrawn
Application number
EP17177364.1A
Other languages
German (de)
English (en)
Inventor
Stefan Bentele
Thomas Helmis
Thorsten Ruhr
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
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP17177364.1A priority Critical patent/EP3418498A1/fr
Publication of EP3418498A1 publication Critical patent/EP3418498A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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 biasing spring segment for radially biasing a turbine blade within a turbine rotor groove.
  • the invention relates to a method for producing a rotor.
  • the Stemm research is placed in a so-called Stemmnut in the turbine shaft.
  • the Stemmnut weakens the shaft cross-section and thus limits the number of starts and the size of the groove.
  • the object of the invention is to provide an improved device with which a turbine blade can be biased.
  • biasing spring segment for radially biasing a turbine blade within a turbine rotor groove, wherein the biasing spring segment has at least one bead.
  • the object is achieved by a method for producing a rotor, wherein in a first step, the biasing spring segment is placed in the turbine rotor groove and in a second step, the turbine blade is moved over the biasing spring segment.
  • a turbine blade is thus now secured with a single Stemm ma, wherein the Stemm congress is designed as a biasing spring segment.
  • This biasing spring segment is a sheet with pressed beads.
  • the pressed-in beads have the shape of a bulge and can also be referred to as warts.
  • the biasing spring segment is placed in the groove and moves the blade over the biasing spring segment. This process can be done in one operation and is therefore advantageous because less time is needed.
  • the geometry of the groove can be changed so that a design limiting Stemmnut can be omitted. This improves the strength properties of the rotor.
  • the bead is formed substantially circular. In alternative embodiments the bead may be oval or substantially round.
  • the biasing spring segment is formed from a sheet, wherein the sheet is a spring plate.
  • the biasing spring segment has a bore, wherein the bore is arranged in the region of an end face. This allows the biasing spring segment with a further tool that can be inserted into the bore, easy to move in the groove.
  • the turbine blade with the biasing spring segment according to the invention can be done in one operation and is therefore time-reduced.
  • the installation can be carried out by means of hydraulic or pneumatic devices, which leads to an improvement in the ergonomics of the employees.
  • Another advantageous effect of the invention is that the Stemmnut in the turbine rotor groove is no longer needed, which leads to an improvement in the life of the shaft.
  • the notch effect of the shaft is improved.
  • FIG. 1 shows a cross-sectional view of a portion of a rotor 1.
  • This rotor 1 is rotatable about a rotation axis, not shown.
  • the rotor 1 has a turbine rotor groove 2.
  • This turbine rotor groove 2 is formed in the circumferential direction. As a rule, the turbine rotor groove 2 is produced by means of a lathe.
  • turbine rotor groove 2 has an axis of symmetry 3.
  • the turbine rotor groove 2 is formed in a first approximation symmetrical to the axis of symmetry 3.
  • a lower side 4 delimits the turbine rotor groove 2.
  • the underside 4 is closed on the left and on the right the symmetry axis 3, a left undercut 5 and a right undercut 6 at.
  • a left support flank 7 and a right support flank 8 are formed.
  • the turbine rotor groove 2 has a constriction 10.
  • Above the constriction 10 each have a left support edge 11 and a right support edge 12 is arranged.
  • a turbine blade is arranged in the turbine rotor groove 2.
  • FIG. 1 is a part of the turbine blade to see.
  • Shown is a turbine blade root 13 of the turbine blade.
  • the turbine blade root 13 is adapted to the turbine rotor groove 2.
  • the turbine blade root 13 is formed substantially symmetrically to the symmetry axis 3.
  • the turbine blade root 13 has a left projection 14 and a right projection 15.
  • the left projection 14 and the right projection 15 are in this case formed such that they rest against the left support flank 7 and right support flank 8 of the turbine rotor groove 2.
  • a comparatively high force acts in the radial direction 9.
  • By the left support flank 7 and the right support flank 8, a movement of the turbine blade in the radial direction 9 is prevented.
  • a gap 16 is formed between the bottom 4 and the turbine blade root 13.
  • a biasing spring segment 17 is arranged.
  • the biasing spring segment 17 can be arranged symmetrically to the symmetry axis 3 and extends substantially from the left undercut 5 to the right undercut 6.
  • the biasing spring segment 17 exerts a radial force in the radial direction.
  • the biasing spring segment 17 is formed with a bead 18.
  • the bead 18 is shown in cross-section and is characterized by an out of the plane of the biasing spring segment 17 bulge 19th
  • the biasing spring segment 17 is shown.
  • FIG. 2 is a perspective view of the biasing spring segment 17 can be seen.
  • FIG. 3 is a plan view of the biasing spring segment 17 represents.
  • the biasing spring segment 17 has, as in FIG. 2 and FIG. 3 can be seen, four beads 18 on. These beads 18 are substantially out of the plane of the biasing spring segment 17 protruding bulges 19 which are pressed. The beads 18 are therefore substantially circular. However, in alternative embodiments, the beads 18 may be other geometry such as oval or the like.
  • the biasing spring segment 17 is formed from a metal sheet, in particular a spring plate.
  • the biasing spring segment 17 comprises a planar base part 20.
  • the base part 20 is essentially formed by a first edge 21 and an edge 22 arranged parallel to the first edge 21. Furthermore, the biasing spring segment 17 has a front edge 23 and a rear edge 24 aligned parallel thereto. The angle between the first edge 21 and the front edge 23 may vary between 0 ° and 180 °. Thus, the biasing spring segment 17 either a rectangular shape or as in FIG. 3 to see is parallelogram-like shape.
  • a recess 25 is formed in the front edge 23, a recess 25 is formed.
  • a demounting pocket 26 is formed on the rear edge 24.
  • the demounting pocket 26 has a bore 27. The demounting pocket 26 is in this case designed such that it can protrude into an adjacent biasing spring segment 17 in the recess 25.
  • the bead 18 is pressed with a caulking (not shown) and therefore has a curvature 19 on a opposite side.
  • the bead 18 can therefore also be referred to as a wart.
  • four beads 18 are formed. First and second beads 18 are at first edge 21 and second and third beads are formed at second edge 22. The distance between the first and second bead 18 is equal to the distance between the third and fourth bead 18th
  • the biasing spring segment 17 is first placed in the turbine rotor groove 2 in a first method step, and then the turbine blade is moved over the biasing spring segment 17 in a second step.
  • the biasing spring segment 17 can be pulled or pushed here.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP17177364.1A 2017-06-22 2017-06-22 Segment ressort de precontrainte, rotor et procédé de fabrication associés Withdrawn EP3418498A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP17177364.1A EP3418498A1 (fr) 2017-06-22 2017-06-22 Segment ressort de precontrainte, rotor et procédé de fabrication associés

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17177364.1A EP3418498A1 (fr) 2017-06-22 2017-06-22 Segment ressort de precontrainte, rotor et procédé de fabrication associés

Publications (1)

Publication Number Publication Date
EP3418498A1 true EP3418498A1 (fr) 2018-12-26

Family

ID=59101413

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17177364.1A Withdrawn EP3418498A1 (fr) 2017-06-22 2017-06-22 Segment ressort de precontrainte, rotor et procédé de fabrication associés

Country Status (1)

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EP (1) EP3418498A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019210699A1 (de) * 2019-07-19 2021-01-21 MTU Aero Engines AG Zwischenelement für eine Schaufel-Rotorscheiben-Verbindung bei einem Rotor einer Strömungsmaschine und Rotor für eine Strömungsmaschine
FR3139361A1 (fr) * 2022-09-01 2024-03-08 Safran Aircraft Engines Clinquant pour aube mobile de turbomachine, ensemble pour rotor comportant un tel clinquant et procédé de montage d’un tel ensemble

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2641443A (en) * 1951-03-17 1953-06-09 A V Roe Canada Ltd Rotor blade locking
US5282720A (en) * 1992-09-15 1994-02-01 General Electric Company Fan blade retainer
EP2246575A1 (fr) * 2009-04-28 2010-11-03 Siemens Aktiengesellschaft Agencement d'aube mobile pour un compresseur axial
EP2562356A1 (fr) * 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Agencement de pales
EP2617946A2 (fr) * 2012-01-23 2013-07-24 MTU Aero Engines GmbH Système pour prédéterminer la position de montage d'aubes mobiles, élément de sécurisation, aube directrice, turbomachine et procédé
EP2719864A1 (fr) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Insert pour une connexion aube-disque pour un rotor d'une turbomachine et un rotor d'une turbomachine associé

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2641443A (en) * 1951-03-17 1953-06-09 A V Roe Canada Ltd Rotor blade locking
US5282720A (en) * 1992-09-15 1994-02-01 General Electric Company Fan blade retainer
EP2246575A1 (fr) * 2009-04-28 2010-11-03 Siemens Aktiengesellschaft Agencement d'aube mobile pour un compresseur axial
EP2562356A1 (fr) * 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Agencement de pales
EP2617946A2 (fr) * 2012-01-23 2013-07-24 MTU Aero Engines GmbH Système pour prédéterminer la position de montage d'aubes mobiles, élément de sécurisation, aube directrice, turbomachine et procédé
EP2719864A1 (fr) * 2012-10-12 2014-04-16 MTU Aero Engines GmbH Insert pour une connexion aube-disque pour un rotor d'une turbomachine et un rotor d'une turbomachine associé

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019210699A1 (de) * 2019-07-19 2021-01-21 MTU Aero Engines AG Zwischenelement für eine Schaufel-Rotorscheiben-Verbindung bei einem Rotor einer Strömungsmaschine und Rotor für eine Strömungsmaschine
WO2021013280A1 (fr) * 2019-07-19 2021-01-28 MTU Aero Engines AG Élément intermédiaire pour une liaison aube-disque de rotor dans un rotor d'une turbomachine, rotor associé pour une turbomachine et turbomachine
US11905852B2 (en) 2019-07-19 2024-02-20 MTU Aero Engines AG Intermediate element for a blade/rotor disc connection in a rotor of a turbomachine, associated rotor for a turbomachine, and turbomachine
FR3139361A1 (fr) * 2022-09-01 2024-03-08 Safran Aircraft Engines Clinquant pour aube mobile de turbomachine, ensemble pour rotor comportant un tel clinquant et procédé de montage d’un tel ensemble

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