EP1643082A1 - Fixation d'aubes de turbine - Google Patents

Fixation d'aubes de turbine Download PDF

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Publication number
EP1643082A1
EP1643082A1 EP04023350A EP04023350A EP1643082A1 EP 1643082 A1 EP1643082 A1 EP 1643082A1 EP 04023350 A EP04023350 A EP 04023350A EP 04023350 A EP04023350 A EP 04023350A EP 1643082 A1 EP1643082 A1 EP 1643082A1
Authority
EP
European Patent Office
Prior art keywords
wedge
blade
groove
blade root
attachment 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.)
Withdrawn
Application number
EP04023350A
Other languages
German (de)
English (en)
Inventor
Derek Hopkinson
Christoph Dr. Richter
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 EP04023350A priority Critical patent/EP1643082A1/fr
Publication of EP1643082A1 publication Critical patent/EP1643082A1/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Withdrawn legal-status Critical Current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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • 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
    • F05D2250/60—Structure; Surface texture
    • 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
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F05D2250/611—Structure; Surface texture corrugated undulated
    • 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
    • F05D2250/70—Shape
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to a blade attachment of a turbine, in particular a steam or gas turbine, with a blade holder on which a blade root of a blade is inserted in a groove.
  • Blade fasteners of the above type are typically used to attach blades to a shaft of the turbine, which then rotate at high speed as the shaft rotates. Due to the fast rotation of the shaft, 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 also 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.
  • the invention has for its object to provide a blade mounting a turbine of the type mentioned, in which over a long period of operation, a precise and low-vibration mounting of blades in associated blade holders is made sure.
  • the object is achieved according to the invention with a generic blade attachment, in which between the blade root and the blade holder a substantially over the entire length of the groove extending wedge is used, which is made of a material or in a form with which he / in Transverse direction of the groove acts as a spring element.
  • a resilient pretension is produced on the blade root substantially over the entire length of the groove, by providing a retaining element through the material or the shape of the wedge, which has a low spring constant transversely to the groove. This low spring rate assures the presence of holding forces in the groove both under conditions in which the blade root moves radially and in thermal variations of the shaft or rotor of the turbine or blade.
  • vibrations of the blade are avoided on the blade root, whereby the risk of mechanical damage and the formation of corrosion is reduced. Furthermore, the tendency for movement of the blade root within the groove is reduced.
  • the wedge according to the invention in particular in the radial direction, the desired clamping forces and holding forces are achieved even at high shaft speed, the wedge according to the invention should be advantageously used on the underside of the blade root.
  • the said effect as a spring element can be varied constructively well by the wedge according to the invention is designed at least on one side with a textured surface.
  • the textured surface can be elastically deformed upon insertion of the wedge, thereby creating a resilient bias of the wedge in the groove. This effect is particularly pronounced in that the wedge according to the invention is designed on opposite sides with a structured surface.
  • the said spring effect in the transverse direction of the groove and in particular in the radial direction of the associated turbine shaft can also be advantageously achieved by shaping the wedge with which the wedge is selectively compressed during insertion into the groove in the longitudinal direction of the groove and thereby biased in the transverse direction of the groove.
  • a shape that is relatively easy to produce for the wedge is a wave form in the longitudinal direction of the wedge, which can be produced at least in sections by a comparatively inexpensive pressing process.
  • the wedge according to the invention may be given a zig-zag shape, at least in sections, in the longitudinal direction.
  • Such a shape typically has a somewhat higher transverse stiffness of the wedge compared to a waveform.
  • a wedge-shaped recess for receiving and guiding the wedge in the longitudinal direction of the groove is advantageously provided on the blade fastening according to the invention.
  • Such a guide is particularly advantageous in grooves, which are not purely straight, but curved.
  • the wedge inclination of said recess corresponds, at least in sections, to the wedge inclination of the wedge itself.
  • the wedge advantageously at at least one of its ends on a supernatant, with the outside of the blade root a positive support for the wedge and / or the blade root itself is created on the blade holder.
  • Such supernatant prevents movement of the blade root within the groove in its longitudinal direction and also leads to a determination of the position of the wedge.
  • the supernatant is also advantageously provided at both ends of the wedge according to the invention, so that migration of the blade root within the groove is prevented towards both groove ends.
  • said projection is also advantageously designed such that it is bent over a section of the blade root and a section of the blade holder essentially in the transverse direction of the groove. So the Furthermore, the wedge according to the invention is not loaded by a possible wandering of the blade root to train, the supernatant should be bent such that the supernatant itself is fixed non-positively or positively on the blade holder. Such a determination is possible, for example, by the supernatant is twice bent pushed into a recess of the blade holder.
  • the blade attachment according to the invention over a large spring travel, tension forces are generated and thus permanent retention of the blade root within the associated groove is achieved even with rotation of the associated turbine shaft. Because only a single wedge element is required for the solution according to the invention, it can be produced and mounted very inexpensively. It usually requires no measurements or adjustments of the inventively designed wedge and the surrounding components.
  • the wedge designed according to the invention can also be disassembled comparatively easily again, because it is e.g. is stretched by pulling in the longitudinal direction of the groove and thereby reduces its resilient bias in the transverse direction of the groove.
  • the wedge according to the invention generates holding forces, in particular in the radial as well as in the axial direction, this being done with only a single component.
  • 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 shaft 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 perpendicularly from the blade root 14.
  • 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 is a substantially over the entire length of the groove 22 extending wedge-shaped recess 24 in the blade root 14, in which a wedge 26 is inserted.
  • the wedge 26 serves to fix the blade root 14 within the blade holder 12 and is intended to generate holding forces, in particular, when the blade root 14 is strongly urged in the radial direction due to a high rotational speed of the shaft and resulting high centrifugal forces on the blade 18.
  • This holding function of the wedge 26 is ensured by the fact that it is formed of a metallic base material, such as a spring steel and designed over its longitudinal extent with a waveform.
  • the waveform leads on two opposite sides of the wedge 26 each to a structured surface, which individually considered webs and Have depressions.
  • the webs of this type are pressed against the adjacent components in such a way that a resilient pretension is generated with the wedge 26, in particular in the transverse direction of the groove 22.
  • This bias is maintained over a comparatively large spring travel away, so that the wedge 26 acts on the blade root 14 substantially over the entire length of the groove 22 away as a spring element.
  • the wedge 26 is each formed with a non-corrugated protrusion 28, which, as illustrated in Fig. 4, each pressed into a formed on the blade holder 12 recess 30 and then bent in the direction of the blade root 14. With the supernatants 28 thus inserted into the depressions 30, it is prevented that the wedge 26 is pulled out of the recess 24 within the groove 22 in the event of a possible tendency of the blade root 14 to migrate. By pulling on the wedge 26 namely its resilient bias would be reduced, reduces its holding power and thus the migration tendency of the blade root 14 may even be promoted.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04023350A 2004-09-30 2004-09-30 Fixation d'aubes de turbine Withdrawn EP1643082A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04023350A EP1643082A1 (fr) 2004-09-30 2004-09-30 Fixation d'aubes de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04023350A EP1643082A1 (fr) 2004-09-30 2004-09-30 Fixation d'aubes de turbine

Publications (1)

Publication Number Publication Date
EP1643082A1 true EP1643082A1 (fr) 2006-04-05

Family

ID=34926803

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04023350A Withdrawn EP1643082A1 (fr) 2004-09-30 2004-09-30 Fixation d'aubes de turbine

Country Status (1)

Country Link
EP (1) EP1643082A1 (fr)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1860280A1 (fr) * 2006-04-07 2007-11-28 Siemens Aktiengesellschaft Dispositif de verrouillage d'une aube de turbine comprenant un élément de verrouillage
EP1892380A1 (fr) * 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Fixation d'aubes de turbine
DE102008013118A1 (de) * 2008-03-07 2009-09-10 Man Diesel Se Anordnung zum Befestigen von Turbinenschaufeln
EP2112328A1 (fr) * 2008-04-21 2009-10-28 Siemens Aktiengesellschaft Rotor pour une turbomachine
CN104285041A (zh) * 2012-06-15 2015-01-14 三菱日立电力系统株式会社 叶根弹簧插入夹具以及叶根弹簧插入方法
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
US20150330235A1 (en) * 2013-10-18 2015-11-19 Siemens Energy, Inc. Variable dual spring blade root support for gas turbines
EP3650652A1 (fr) 2018-11-08 2020-05-13 Doosan Skoda Power S.r.o. Fixation d'aube de turbine avec pied en forme d'arbre au rotor de turbine avec cale déformable et élément de fixation
CN111472845A (zh) * 2020-05-27 2020-07-31 上海尚实能源科技有限公司 一种涡桨发动机用涡轮盘与叶片锁紧机构
EP4006305A3 (fr) * 2020-11-20 2022-07-20 Solar Turbines Incorporated Couplage de rigidité et amortissement des vibrations pour carénage d'aube de turbine
US11401945B2 (en) 2020-08-19 2022-08-02 Doosan Enerbility Co., Ltd. Compressor blade assembly structure, gas turbine having same, and compressor blade assembly method
US20220268164A1 (en) * 2019-07-19 2022-08-25 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
FR3139159A1 (fr) * 2022-08-31 2024-03-01 Safran Aircraft Engines Roue de turbine comprenant un dispositif de maintien radial de pieds d’aube dans les alveoles d’un disque de rotor

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2942842A (en) * 1956-06-13 1960-06-28 Gen Motors Corp Turbine blade lock
DE1551211A1 (de) * 1966-07-20 1970-02-12 Siemens Ag Loesbare Laufschaufelbefestigung mit Stemmverbindung
DE3236021A1 (de) * 1981-11-10 1983-05-19 BBC Aktiengesellschaft Brown, Boveri & Cie., 5401 Baden, Aargau Mit schaufeln versehener turbinenrotorkoerper
JPS61129405A (ja) * 1984-11-28 1986-06-17 Hitachi Ltd タ−ビン動翼固定方法
US5584659A (en) * 1994-08-29 1996-12-17 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Device for fixing turbine blades and for eliminating rotor balance errors in axially flow-through compressors or turbines of gas turbine drives
DE19823157A1 (de) * 1998-05-23 1999-11-25 Asea Brown Boveri Einrichtung zur Befestigung der Laufschaufeln axial durchströmter Turbomaschinen
WO2003100220A1 (fr) * 2002-05-24 2003-12-04 Abb Turbo Systems Ag Dispositif de securite axial pour aubes mobiles
US20040062653A1 (en) * 2002-09-27 2004-04-01 Franco Di Paola Blade retention scheme using a retention tab

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2942842A (en) * 1956-06-13 1960-06-28 Gen Motors Corp Turbine blade lock
DE1551211A1 (de) * 1966-07-20 1970-02-12 Siemens Ag Loesbare Laufschaufelbefestigung mit Stemmverbindung
DE3236021A1 (de) * 1981-11-10 1983-05-19 BBC Aktiengesellschaft Brown, Boveri & Cie., 5401 Baden, Aargau Mit schaufeln versehener turbinenrotorkoerper
JPS61129405A (ja) * 1984-11-28 1986-06-17 Hitachi Ltd タ−ビン動翼固定方法
US5584659A (en) * 1994-08-29 1996-12-17 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Device for fixing turbine blades and for eliminating rotor balance errors in axially flow-through compressors or turbines of gas turbine drives
DE19823157A1 (de) * 1998-05-23 1999-11-25 Asea Brown Boveri Einrichtung zur Befestigung der Laufschaufeln axial durchströmter Turbomaschinen
WO2003100220A1 (fr) * 2002-05-24 2003-12-04 Abb Turbo Systems Ag Dispositif de securite axial pour aubes mobiles
US20040062653A1 (en) * 2002-09-27 2004-04-01 Franco Di Paola Blade retention scheme using a retention tab

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 010, no. 323 (M - 531) 5 November 1986 (1986-11-05) *

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1860280A1 (fr) * 2006-04-07 2007-11-28 Siemens Aktiengesellschaft Dispositif de verrouillage d'une aube de turbine comprenant un élément de verrouillage
EP1892380A1 (fr) * 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Fixation d'aubes de turbine
WO2008022890A1 (fr) * 2006-08-25 2008-02-28 Siemens Aktiengesellschaft fixation d'aube de turbine
US8192167B2 (en) 2006-08-25 2012-06-05 Siemens Aktiengesellschaft Blade fastening means of a turbine
CN101506475B (zh) * 2006-08-25 2013-01-23 西门子公司 透平叶片锁紧装置
DE102008013118A1 (de) * 2008-03-07 2009-09-10 Man Diesel Se Anordnung zum Befestigen von Turbinenschaufeln
JP2009216096A (ja) * 2008-03-07 2009-09-24 Man Diesel Se タービン翼を固定するための構造
DE102008013118B4 (de) * 2008-03-07 2014-03-27 Man Diesel & Turbo Se Anordnung zum Befestigen von Turbinenschaufeln
EP2112328A1 (fr) * 2008-04-21 2009-10-28 Siemens Aktiengesellschaft Rotor pour une turbomachine
CN104285041A (zh) * 2012-06-15 2015-01-14 三菱日立电力系统株式会社 叶根弹簧插入夹具以及叶根弹簧插入方法
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
US20150330235A1 (en) * 2013-10-18 2015-11-19 Siemens Energy, Inc. Variable dual spring blade root support for gas turbines
US9739160B2 (en) 2013-10-18 2017-08-22 Siemens Aktiengesellschaft Adjustable blade root spring for turbine blade fixation in turbomachinery
US9909431B2 (en) * 2013-10-18 2018-03-06 Siemens Energy, Inc. Variable dual spring blade root support for gas turbines
EP3650652A1 (fr) 2018-11-08 2020-05-13 Doosan Skoda Power S.r.o. Fixation d'aube de turbine avec pied en forme d'arbre au rotor de turbine avec cale déformable et élément de fixation
US20220268164A1 (en) * 2019-07-19 2022-08-25 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
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
CN111472845A (zh) * 2020-05-27 2020-07-31 上海尚实能源科技有限公司 一种涡桨发动机用涡轮盘与叶片锁紧机构
US11401945B2 (en) 2020-08-19 2022-08-02 Doosan Enerbility Co., Ltd. Compressor blade assembly structure, gas turbine having same, and compressor blade assembly method
EP4006305A3 (fr) * 2020-11-20 2022-07-20 Solar Turbines Incorporated Couplage de rigidité et amortissement des vibrations pour carénage d'aube de turbine
FR3139159A1 (fr) * 2022-08-31 2024-03-01 Safran Aircraft Engines Roue de turbine comprenant un dispositif de maintien radial de pieds d’aube dans les alveoles d’un disque de rotor

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