EP1905957A1 - Dispositif de fixation d'une aube de turbine - Google Patents

Dispositif de fixation d'une aube de turbine Download PDF

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Publication number
EP1905957A1
EP1905957A1 EP06020318A EP06020318A EP1905957A1 EP 1905957 A1 EP1905957 A1 EP 1905957A1 EP 06020318 A EP06020318 A EP 06020318A EP 06020318 A EP06020318 A EP 06020318A EP 1905957 A1 EP1905957 A1 EP 1905957A1
Authority
EP
European Patent Office
Prior art keywords
securing device
pressure
displacement
blade root
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.)
Withdrawn
Application number
EP06020318A
Other languages
German (de)
English (en)
Inventor
Bernd Czerwik
Thomas Helmis
Michael Kleinhaus
Christoph Dr. Richter
Kai Dr. Wieghardt
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 EP06020318A priority Critical patent/EP1905957A1/fr
Priority to AT07820448T priority patent/ATE530734T1/de
Priority to EP07820448A priority patent/EP2066871B1/fr
Priority to PCT/EP2007/060021 priority patent/WO2008037661A1/fr
Publication of EP1905957A1 publication Critical patent/EP1905957A1/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Withdrawn legal-status Critical Current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
    • F01D5/32—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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/281—Three-dimensional patterned threaded
    • 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 a securing device for radial securing of a turbine blade, wherein a pressure means for exerting a compressive force is provided on a turbine blade root in the radial direction.
  • Blade fasteners of the above type are typically used to secure blades to a rotor of a turbine which revolve at high speed as the rotor rotates. Due to the fast rotation of the rotor, the associated blades are subjected to high centrifugal force. The blade root of the blades is therefore exposed to high forces and is strongly forced radially outward in the groove on the blade holder. In addition, the blades are exposed to strong vibration loads, so that it can come to the groove to mechanical damage, material fatigue, corrosion and migration of the blade root within the groove. For fixing the blade root within the groove, various solutions such as metal wedges, spring washers or sealing pieces are known.
  • the invention has for its object to provide a blade mounting a turbine, in which over a long period of operation, a precise and low-vibration mounting of blades is secured in associated blade holders.
  • a securing device for radial securing of a turbine blade wherein a pressure means for exerting a compressive force on a turbine blade root in the radial direction and a rotating means is provided and the securing device is designed such that the pressing force can be exerted by a rotational movement of the rotating means.
  • the securing device is first inserted into a groove.
  • the rotating means is set in a rotational movement. Due to the rotational movement of the rotating means, the pressure medium is enabled to exert a compressive force. Finally, the compressive force achieves the effect of moving the turbine blade in the radial direction. As the blade root is inserted into blade holders, counter forces occur. The combination of compressive force and counterforce causes the turbine blade to be effectively held in the blade holder.
  • Another advantage of the invention is that by a rotational movement of the rotating means, which points in an opposite direction, the pressure force can be reduced again and thus solved the securing device of the turbine blade can be, resulting in a non-destructive expansion of the safety device.
  • the pressure means has a movably arranged pressure bar. This makes it possible to design the securing device by a structurally simple construction.
  • a displacement means is arranged on the rotation means such that a rotation of the rotation means leads to a displacement of the displacement means.
  • This is a simple variant for moving a displacement means, which eventually leads to a movement of the pressure beam. Since very high forces can be transmitted via rotational movements, a very high force can be transmitted to the pressure medium via the displacement means and the rotation means, which in turn leads to a high pressure force on the turbine blade root in the radial direction.
  • two displacement means which are designed to be movable, provided. Since, as already mentioned, a high force can be transmitted via a rotary movement, it is advantageous if two displacement means can be provided, which can be formed by the rotational movement to each other. As a result, the transferable pressure force on the turbine blade root in the radial direction increases even further.
  • the pressure bar is designed to be elastic. This makes it possible for a pressure force to be exerted on the turbine blade root in the radial direction during operation.
  • a pressure force acts on the turbine blade root in the radial direction during operation. That means a rigidly set Pressure force on the turbine blade foot would be lower.
  • a resilient pressure beam By a resilient pressure beam, the pressure force on the turbine blade root is maintained over a certain distance, although the turbine blade root moves away from the pressure beam.
  • the securing device is provided for installation in a groove in a blade root and / or in a rotor.
  • a blade attachment 10 is shown by a turbine, not further illustrated, in which a blade root 14 is supported on a blade holder 12 on a rotor of the turbine.
  • the blade root 14 is part of a blade 16, from which an airfoil 18 protrudes substantially radially from the shaft and thus perpendicular to the blade root.
  • the blade root 14 is designed with a fir tree-like profile 20 which is inserted into a curved groove 22 formed in the blade holder 12. At the bottom of the groove 22 is located between the inserted blade root 14 and the blade holder 12 a substantially over the entire length of the groove 22 extending recess 24 in the blade root 14, in which a securing device 30 is inserted.
  • the securing device 30 comprises, as shown in FIG. 3, a rotating means 31.
  • the rotating means 31 can be moved in both rotational directions (clockwise or counterclockwise).
  • the rotating means 31 further includes a first thread 32 and a second thread 33 counter-clockwise made to the first thread 32.
  • On the first thread 32 a first displacement means 34 is arranged.
  • the displacement means 34 has a bore into which the rotation means 31 projects.
  • the displacement means 34 therefore comprises a complementary thread.
  • a second displacement means 35 is arranged on the second thread 33, which, like the first displacement means 34 has a bore with a corresponding thread.
  • the displacement means 34 and 35 are either moved toward or away from each other, depending on which rotational direction the rotation means 31 is moved in.
  • a pressure medium designed as a pressure bar 36 is arranged between the first displacement means 34 and the second displacement means 35. Rotation of the rotating means 31 results in movement of the pressure means in a radial direction 37.
  • the pressure bar 36 may be formed U-shaped, wherein the two legs can be arranged in each case left and right of the rotating means 31.
  • a second pressure bar 38 which may also be U-shaped, is disposed between the first displacement means 34 and the second displacement means 35.
  • the blade 16 can be seen in the installed state.
  • the securing device 30 is arranged in a groove 39, wherein of the securing device 30 substantially only the rotating means 31 can be seen.
  • FIG. 4 shows a cross section through the blade 16 and the blade holder 12.
  • the securing device 10 is mounted in a groove 39.
  • the two pressure beams 38 and 36 are moved in the radial direction 37, whereby a force is exerted by the blade holder 12 on the blade root 14, thereby the turbine blade 16 is held firmly to the blade holder 12.
  • FIG 5 shows an enlarged view of the securing device 30 is shown in FIG 4.
  • the operation and assignment of the reference numerals applies accordingly.
  • the pressure beams 36 and 38 can be arranged at their ends in retaining grooves 40 and 41. This prevents the safety device from slipping out of the groove 39.
  • FIG. 6 shows a perspective view of the securing device 30.
  • the rotating means 31 may be implemented as a square 44 at one end. As a result, tools can be easily arranged on the rotating means 31, so that a rotational movement can be transmitted to the rotating means 31.
  • FIG. 7 shows an alternative embodiment of the securing device 10.
  • the securing device 30 is designed, so to speak, as a jack.
  • the securing device 30 has a first upper rod 50 and a second upper rod 51, which is connected at one end to the first displacement means 36 and the second upper rod 51 is connected to the second displacement means 38.
  • the securing device 30 has a first lower rod 52 and a second lower rod 53.
  • the first lower rod 52 is connected at one end to the first displacement means 36, whereas the second lower rod 53 is connected at one end to the second displacement means 38.
  • the first upper rod 50 and the second upper rod 51 are connected at their other end together to a fitting key 54.
  • the first lower rod 52 and the second lower rod 53 are connected at their end to a lower fitting wedge 55.
  • a rotation of the rotating means 31 leads via the oppositely formed threads 32 and 33 to a movement of the displacement means 36 and 38 to each other or away from each other. If the displacement means 36 and 38 are moved toward each other, the first upper rod 50 and the second upper rod 51 are moved in the radial direction and the first lower rod 52 and the second lower rod 53 are moved in the radial direction 37.
  • the fitting keys 54 and 55 are thus pressed against the blade root 14 and against the blade holder 12 on the one hand.
  • the upper wedge 54 is located on the blade root 14 in a corresponding groove 56.
  • the lower wedge 55 is applied to the blade holder in a corresponding groove 57 at. A displacement of the securing device 10 in the axial direction is thus effectively prevented.
  • the first upper bar 50, the second upper bar 51, the first lower bar 52, and the second lower bar 53 may be attached to the shifting means 36, shifting means 38, to the wedge 54, as well as to the lower fitting wedge 55, by conventional connecting means such as screws or rivets be attached.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06020318A 2006-09-27 2006-09-27 Dispositif de fixation d'une aube de turbine Withdrawn EP1905957A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP06020318A EP1905957A1 (fr) 2006-09-27 2006-09-27 Dispositif de fixation d'une aube de turbine
AT07820448T ATE530734T1 (de) 2006-09-27 2007-09-21 Sicherungsvorrichtung einer turbinenschaufel
EP07820448A EP2066871B1 (fr) 2006-09-27 2007-09-21 Dispositif de fixation d'une aube de turbine
PCT/EP2007/060021 WO2008037661A1 (fr) 2006-09-27 2007-09-21 Dispositif de protection d'une aube de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06020318A EP1905957A1 (fr) 2006-09-27 2006-09-27 Dispositif de fixation d'une aube de turbine

Publications (1)

Publication Number Publication Date
EP1905957A1 true EP1905957A1 (fr) 2008-04-02

Family

ID=37807898

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06020318A Withdrawn EP1905957A1 (fr) 2006-09-27 2006-09-27 Dispositif de fixation d'une aube de turbine
EP07820448A Not-in-force EP2066871B1 (fr) 2006-09-27 2007-09-21 Dispositif de fixation d'une aube de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP07820448A Not-in-force EP2066871B1 (fr) 2006-09-27 2007-09-21 Dispositif de fixation d'une aube de turbine

Country Status (3)

Country Link
EP (2) EP1905957A1 (fr)
AT (1) ATE530734T1 (fr)
WO (1) WO2008037661A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2090750A1 (fr) * 2008-02-14 2009-08-19 Siemens Aktiengesellschaft Rotor de turbomachine, aube rotorique pour un tel rotor de turbomachine, languette de calage et procédé d'assemblage associé
EP2149677A1 (fr) 2008-07-30 2010-02-03 Siemens Aktiengesellschaft Dispositif de fixation destiné à la fixation d'une pale de rotor sur une turbomachine
EP3070269A1 (fr) * 2015-03-12 2016-09-21 Rolls-Royce plc Dispositif de strangulation et de rétention
WO2022079360A1 (fr) * 2020-10-16 2022-04-21 Safran Aircraft Engines Ensemble d'attache pour une aube de turbomachine
EP4045398B1 (fr) * 2019-10-18 2023-08-23 Safran Aircraft Engines Ensemble pour une aube de turbomachine comprenant une attache définissant une alvéole et une cale adaptée pour être reçue dans l'alvéole en même temps qu'un pied de l'aube

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2299060A1 (fr) * 2009-09-17 2011-03-23 Siemens Aktiengesellschaft Fixation des aubes avec dispositif de verrouillage pour aubes de turbines

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE834408C (de) * 1950-11-23 1952-03-20 Maschf Augsburg Nuernberg Ag Vorverspannte axiale Schaufelfussbefestigung fuer Dampf- und Gasturbinen
US2846183A (en) * 1952-07-18 1958-08-05 William C Morgan Retaining devices for turbine blades
US3720481A (en) * 1971-04-28 1973-03-13 Avco Corp Means for forming and securing turbine compressor blades
FR2323908A1 (fr) * 1975-09-11 1977-04-08 Alsthom Cgee Dispositif de blocage d'une piece montee dans une rainure
JPS59192801A (ja) * 1983-04-15 1984-11-01 Hitachi Ltd 着脱容易な動翼固定方法
US5123813A (en) * 1991-03-01 1992-06-23 General Electric Company Apparatus for preloading an airfoil blade in a gas turbine engine

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE602005005988T2 (de) * 2005-08-12 2009-05-20 Siemens Aktiengesellschaft Turbine für eine Wärmekraftanlage mit Haltevorrichtung

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE834408C (de) * 1950-11-23 1952-03-20 Maschf Augsburg Nuernberg Ag Vorverspannte axiale Schaufelfussbefestigung fuer Dampf- und Gasturbinen
US2846183A (en) * 1952-07-18 1958-08-05 William C Morgan Retaining devices for turbine blades
US3720481A (en) * 1971-04-28 1973-03-13 Avco Corp Means for forming and securing turbine compressor blades
FR2323908A1 (fr) * 1975-09-11 1977-04-08 Alsthom Cgee Dispositif de blocage d'une piece montee dans une rainure
JPS59192801A (ja) * 1983-04-15 1984-11-01 Hitachi Ltd 着脱容易な動翼固定方法
US5123813A (en) * 1991-03-01 1992-06-23 General Electric Company Apparatus for preloading an airfoil blade in a gas turbine engine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2090750A1 (fr) * 2008-02-14 2009-08-19 Siemens Aktiengesellschaft Rotor de turbomachine, aube rotorique pour un tel rotor de turbomachine, languette de calage et procédé d'assemblage associé
EP2149677A1 (fr) 2008-07-30 2010-02-03 Siemens Aktiengesellschaft Dispositif de fixation destiné à la fixation d'une pale de rotor sur une turbomachine
EP3070269A1 (fr) * 2015-03-12 2016-09-21 Rolls-Royce plc Dispositif de strangulation et de rétention
US10145250B2 (en) 2015-03-12 2018-12-04 Rolls-Royce Plc Chocking and retaining device
EP4045398B1 (fr) * 2019-10-18 2023-08-23 Safran Aircraft Engines Ensemble pour une aube de turbomachine comprenant une attache définissant une alvéole et une cale adaptée pour être reçue dans l'alvéole en même temps qu'un pied de l'aube
WO2022079360A1 (fr) * 2020-10-16 2022-04-21 Safran Aircraft Engines Ensemble d'attache pour une aube de turbomachine

Also Published As

Publication number Publication date
EP2066871A1 (fr) 2009-06-10
EP2066871B1 (fr) 2011-10-26
ATE530734T1 (de) 2011-11-15
WO2008037661A1 (fr) 2008-04-03

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