EP0705959A2 - Configuration du pied d'aube de turbomachine - Google Patents

Configuration du pied d'aube de turbomachine Download PDF

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Publication number
EP0705959A2
EP0705959A2 EP95810586A EP95810586A EP0705959A2 EP 0705959 A2 EP0705959 A2 EP 0705959A2 EP 95810586 A EP95810586 A EP 95810586A EP 95810586 A EP95810586 A EP 95810586A EP 0705959 A2 EP0705959 A2 EP 0705959A2
Authority
EP
European Patent Office
Prior art keywords
blade
notches
rotor
curve radius
load
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Withdrawn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
EP95810586A
Other languages
German (de)
English (en)
Other versions
EP0705959A3 (fr
Inventor
Uy-Liem Dr. Nguyen
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.)
ABB AG Germany
Original Assignee
ABB Management 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 ABB Management AG filed Critical ABB Management AG
Publication of EP0705959A2 publication Critical patent/EP0705959A2/fr
Publication of EP0705959A3 publication Critical patent/EP0705959A3/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Withdrawn legal-status Critical Current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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the invention relates to a bladed rotor of a turbomachine, in which the blade roots and the blade grooves are shaped like a fir tree with a plurality of notches and serrations, as a result of which several obliquely running load-bearing surfaces are formed, the notches adjoining the load-bearing surfaces essentially in the blade root and in the blade groove can be described by a first curve radius and a second curve radius.
  • Such bladed rotors are known from GB-A-2011522.
  • Each blade has notches and tines in its foot area, which hook into the correspondingly shaped tines and notches in the longitudinal grooves of the rotor.
  • the notches are described by two radii, a larger outer and a smaller inner radius.
  • the larger radius of the rotor is located radially to the outside of the rotor axis. At the shovel the larger radius lies radially inwards to the rotor axis.
  • a narrow gap is subsequently formed between the blade and the rotor on the supporting surfaces.
  • This gap has the effect of a capillary, which can cause corrosion and pitting after the load-bearing surfaces. This can lead to premature fatigue fractures in the blade root or in the groove of the rotor.
  • abrasion particles generated during operation of the rotor can get into the gaps, remain there and possibly destroy protective layers applied to the surfaces.
  • the invention has for its object to avoid premature fatigue fractures due to corrosion in the fir tree-shaped fastening in a bladed rotor of the type mentioned and to optimize the voltage profiles.
  • this is achieved in that the first curve radius adjoining the load-bearing surface is smaller than the second curve radius and that the opening angle between a tangent, which lies on the circular arc described by the first curve radius at the end point of the load-bearing surface, and the load-bearing surface is forty degrees.
  • the advantages of the invention include the fact that the capillary effect in the vicinity of the supporting surface is eliminated. Abrasion particles are no longer retained and cannot cause any damage to the applied protective layers. Tensions in the connection to the load-bearing surface are reduced and the service life of the components is increased.
  • the opening angle is chosen to be as large as possible in order to reduce stresses following the supporting surface.
  • a drum rotor 1 is provided with blades 5.
  • the blades 5 consist of blade 4 and blade root 3.
  • the blades are inserted with the blade roots 3 in axially parallel, longitudinally extending blade grooves 2 of the drum rotor 1.
  • the blade root 3 is in the form of a fir tree with a plurality of notches 10 and teeth 11. Accordingly, the blade grooves 2 in the drum rotor 1 are formed with teeth 20 and notches 21. If the rotor is rotated, the rotor blades 5 are accelerated radially outward, being held back by the drum rotor 1 by the fir tree-shaped fastening.
  • a bearing surface F which is created during the rotation of the drum rotor 1 by the centrifugal acceleration of the rotor blades 5, is arranged between a notch 10 and a notch 21.
  • the bearing surface F is described by its end points A and B and by its tilt angle 12 to a parallel 6 to the longitudinal axis 7 (FIG. 1) of the moving blade.
  • the tilt angle 12 is usually forty to fifty degrees.
  • the notches 21 of the drum rotor 1 and the notches 10 of the moving blades 5 are rotationally symmetrical.
  • Points C, D, E and H are defined along the notch 21 and are used to describe the geometry of the notch.
  • a straight line T is laid through the end point A of the load-bearing surface F such that it includes an opening angle W with the load-bearing surface. For manufacturing reasons, the angle W is sixty degrees here.
  • the Straight line T serves as a tangent for an arc 22 with a radius R1 and point A as an element of the arc AC.
  • the center of the circular arc AC 22 thus lies on a perpendicular to the tangent T through the point A.
  • the end point of the circular arc AC lies in C, where a straight line CD 23 tangentially adjoins the circular arc AC 22.
  • the straight line CD is also tangential to a circular arc DE 24, which is defined by the radius R2.
  • the center point of the circular arc DE thus lies on a perpendicular to the straight line CD 23 through the point D.
  • the radius R2 is larger than the radius R1.
  • a straight line EH 25 connects tangentially to the circular arc DE.
  • this straight line EH changes into a straight line 26 of the point 20.
  • the straight line 26 is tilted counterclockwise with the tilt angle 12 against the parallel 6 to the longitudinal axis 7 of the rotor blade.
  • the opening angle can, if the manufacturing conditions allow, advantageously be chosen even larger.
  • the shape of the notch can also be designed without straight sections or with a combination of straight sections with curved sections. The decisive factor here is always the optimization of the stress curve.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP95810586A 1994-10-01 1995-09-20 Configuration du pied d'aube de turbomachine Withdrawn EP0705959A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4435268A DE4435268A1 (de) 1994-10-01 1994-10-01 Beschaufelter Rotor einer Turbomaschine
DE4435268 1994-10-01

Publications (2)

Publication Number Publication Date
EP0705959A2 true EP0705959A2 (fr) 1996-04-10
EP0705959A3 EP0705959A3 (fr) 1998-01-07

Family

ID=6529803

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810586A Withdrawn EP0705959A3 (fr) 1994-10-01 1995-09-20 Configuration du pied d'aube de turbomachine

Country Status (4)

Country Link
US (1) US5554005A (fr)
EP (1) EP0705959A3 (fr)
JP (1) JPH08100603A (fr)
DE (1) DE4435268A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0889202A3 (fr) * 1997-07-02 2000-02-02 Asea Brown Boveri AG Connexion

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6033185A (en) * 1998-09-28 2000-03-07 General Electric Company Stress relieved dovetail
GB2442968B (en) * 2006-10-20 2009-08-19 Rolls Royce Plc A turbomachine rotor blade and a turbomachine rotor
US20080232972A1 (en) * 2007-03-23 2008-09-25 Richard Bouchard Blade fixing for a blade in a gas turbine engine
US8047797B2 (en) * 2007-07-16 2011-11-01 Nuovo Pignone Holdings, S.P.A. Steam turbine and rotating blade
US8038404B2 (en) * 2007-07-16 2011-10-18 Nuovo Pignone Holdings, S.P.A. Steam turbine and rotating blade
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
DE102007051838A1 (de) * 2007-10-30 2009-05-07 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenschaufelfuß
US8047796B2 (en) * 2007-11-16 2011-11-01 General Electric Company Dovetail attachment for use with turbine assemblies and methods of assembling turbine assemblies
US20090285690A1 (en) * 2008-05-19 2009-11-19 Brown Clayton D Axial blade slot pressure face with undercut
EP2546465A1 (fr) 2011-07-14 2013-01-16 Siemens Aktiengesellschaft Pied d'aube, aube, disque de rotor et ensemble de turbomachine associés
US9359905B2 (en) 2012-02-27 2016-06-07 Solar Turbines Incorporated Turbine engine rotor blade groove
US10072507B2 (en) 2012-10-25 2018-09-11 United Technologies Corporation Redundant airfoil attachment
EP2762676A1 (fr) * 2013-02-04 2014-08-06 Siemens Aktiengesellschaft Aube rotorique de turbomachine, disque de rotor de turbomachine, rotor de turbomachine et moteur à turbine à gaz ayant des surfaces de contact du pied et de la rainure d'aube à angles différents
EP2860361B1 (fr) 2013-10-08 2017-03-01 MTU Aero Engines GmbH Support d'élément et turbomachine
GB201416505D0 (en) * 2014-09-18 2014-11-05 Rolls Royce Plc Gas turbine engine
JP2016223310A (ja) * 2015-05-27 2016-12-28 三菱日立パワーシステムズ株式会社 タービンおよびタービン運用方法
JP6521273B2 (ja) * 2015-08-21 2019-05-29 三菱重工コンプレッサ株式会社 蒸気タービン
EP3159483A1 (fr) * 2015-10-22 2017-04-26 Siemens Aktiengesellschaft Dispositif de fixation d'aubes mobiles d'une turbomachine thermique
JP6785555B2 (ja) * 2016-01-15 2020-11-18 三菱パワー株式会社 動翼のタービンロータへの組付方法
US10895160B1 (en) * 2017-04-07 2021-01-19 Glenn B. Sinclair Stress relief via unblended edge radii in blade attachments in gas turbines
CN107143380B (zh) * 2017-05-27 2019-04-02 中国航发湖南动力机械研究所 燃气涡轮盘榫槽设计方法、燃气涡轮盘及航空发动机
JP7385992B2 (ja) * 2018-12-28 2023-11-24 川崎重工業株式会社 回転体の動翼およびディスク
DE102022202368A1 (de) * 2022-03-10 2023-09-14 Siemens Energy Global GmbH & Co. KG Nutdesign einer Scheibe für eine Turbinenschaufel, Rotor und ein Verfahren
US12055069B2 (en) * 2022-09-20 2024-08-06 Siemens Energy, Inc. System and method for reducing blade hook stress in a turbine blade
US12305533B2 (en) * 2023-06-23 2025-05-20 Pratt & Whitney Canada Corp. Turbine rotor dovetail structure with splines

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2011522A (en) 1977-12-28 1979-07-11 Gotto R J Sparking-plug lock

Family Cites Families (12)

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Publication number Priority date Publication date Assignee Title
DE859838C (de) * 1951-04-07 1952-12-15 Maschf Augsburg Nuernberg Ag Maschinenbauteile aus keramischen Werkstoffen
US4191509A (en) * 1977-12-27 1980-03-04 United Technologies Corporation Rotor blade attachment
GB2030657B (en) * 1978-09-30 1982-08-11 Rolls Royce Blade for gas turbine engine
JPS58167807A (ja) * 1982-03-29 1983-10-04 Hitachi Ltd タ−ボ機械のブレ−ド取付構造
US4692976A (en) * 1985-07-30 1987-09-15 Westinghouse Electric Corp. Method of making scalable side entry turbine blade roots
US4824328A (en) * 1987-05-22 1989-04-25 Westinghouse Electric Corp. Turbine blade attachment
GB2238581B (en) * 1989-11-30 1994-01-12 Rolls Royce Plc Improved attachment of a gas turbine engine blade to a turbine rotor disc
US5152669A (en) * 1990-06-26 1992-10-06 Westinghouse Electric Corp. Turbomachine blade fastening
US5141401A (en) * 1990-09-27 1992-08-25 General Electric Company Stress-relieved rotor blade attachment slot
US5147180A (en) * 1991-03-21 1992-09-15 Westinghouse Electric Corp. Optimized blade root profile for steam turbine blades
US5160242A (en) * 1991-05-31 1992-11-03 Westinghouse Electric Corp. Freestanding mixed tuned steam turbine blade
US5176500A (en) * 1992-03-24 1993-01-05 Westinghouse Electric Corp. Two-lug side-entry turbine blade attachment

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2011522A (en) 1977-12-28 1979-07-11 Gotto R J Sparking-plug lock

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0889202A3 (fr) * 1997-07-02 2000-02-02 Asea Brown Boveri AG Connexion

Also Published As

Publication number Publication date
DE4435268A1 (de) 1996-04-04
US5554005A (en) 1996-09-10
JPH08100603A (ja) 1996-04-16
EP0705959A3 (fr) 1998-01-07

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