EP0906514A1 - Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor - Google Patents

Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor

Info

Publication number
EP0906514A1
EP0906514A1 EP97928110A EP97928110A EP0906514A1 EP 0906514 A1 EP0906514 A1 EP 0906514A1 EP 97928110 A EP97928110 A EP 97928110A EP 97928110 A EP97928110 A EP 97928110A EP 0906514 A1 EP0906514 A1 EP 0906514A1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade root
blade
groove
turbomachine
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
EP97928110A
Other languages
German (de)
English (en)
Other versions
EP0906514B1 (fr
Inventor
Carsten Bartsch
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
Publication of EP0906514A1 publication Critical patent/EP0906514A1/fr
Application granted granted Critical
Publication of EP0906514B1 publication Critical patent/EP0906514B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings

Definitions

  • Rotor for a turbo machine with blades which can be fitted in grooves and blade for a rotor
  • the present invention relates to a rotor for a turbomachine with blades which can be fitted in grooves, the grooves being arranged obliquely to the axis of rotation of the rotor, and a blade for a rotor.
  • the object of the present invention is now to reduce the strength problems occurring during the operation of a rotor and to specify a suitable combination of blade root and groove.
  • a rotor for a turbomachine with the features of claim 1 and a blade with the features of claim 6 serve to achieve this object.
  • Advantageous features and combinations result from the features disclosed in the respective dependent claims.
  • a rotor according to the invention with blades which can be fitted in grooves, in which the grooves are inclined to the axis of rotation of the rotor are attached, has at least a part of its blades a blade root with at least two areas with different stiffness, which are adapted, preferably adjusted, to different areas of the stiffness of the groove into which the blade root can be attached.
  • a preferred embodiment provides that a correspondingly adapted region of the blade root and a region of the groove that is stiffer in comparison lie opposite or opposite one another. This ensures that the corresponding stiffness of the groove and
  • Blade root correspond so that there is an overall equalization of the stresses that occur.
  • the flow of force during the transmission of force from the blade root into the groove can be designed inexpensively with a corresponding adaptation. It is also expedient if there is a region of reduced stiffness of the blade root in the groove area of the highest occurring stress, in general in particular in the area of the pointed corners of the groove in the rotor, so that no stresses occur during operation of the turbomachine which could destroy or Material fatigue leads to prolonged operation of the turbomachine.
  • FIG. 1 shows a cross section of a rotor with blades adapted and used according to the invention
  • FIG. 2 shows the rotor from FIG. 1 in a top view without inserted blades
  • FIG. 3 shows a blade root according to the invention
  • FIG. 4 shows the blade root from FIG. 3 used in a rotor disk
  • FIG. 5 shows another foot used according to the invention.
  • the rotor 1 of the turbomachine is preferably formed from rotor disks 1 which are arranged axially one behind the other and are toothed together (Hirth toothing) and are connected to one another by a tie rod, not shown.
  • FIG. 1 shows a section of a rotor disk 1 with blades 3 inserted in grooves 2.
  • Each blade 3 has areas with different stiffness.
  • a recess 5 is made in the blade root 4 in such a way that the groove 2, which has an unevenly high rigidity over its groove depth, is opposite an adapted rigidity of the blade root 4. Since, in particular at the sharp corner 6 (see FIG. 2) of a groove 2, which lies at the end of the groove, increased voltages occur during operation of the gas turbine compressor, in this area the blade root 4 has the recess 5 in such a way that it is connected to it Body is slightly compliant.
  • An advantageous embodiment of the recess 5 provides this in the form of a cutout, which runs obliquely downwards on the end face 8 of the blade root 4.
  • FIG. 2 shows the rotor disk 1 from FIG. 1 in a top view.
  • the grooves 2 are made at an installation angle ⁇ to the axis of rotation of the rotor disk 1, which can be much larger than conventional installation angles due to the adapted blade feet 4. This is particularly important for gas turbines and their compressors with a low mass flow. There larger blade angles and thus larger installation angles ß may be required. This leads in turn to increased local stresses in the groove 2, since there are reduced stiffnesses in particular in the pointed corners 6 due to the increased angles.
  • the pointed corners 6 are places of local high tension. They are shown as the ends of the groove width D indicated in dashed lines and lying inside the rotor disk 1. Seen over the groove length L, it has different ranges of different stresses not only in its depth but also in its extent, which therefore have a different influence on the strength when the blade root 4 is installed and the operation of the turbomachine.
  • FIG. 3 shows a blade root 4 according to the invention with an indicated extension of the blade leaf 7 of the blade 3.
  • This has a recess 5, starting at both end faces 8, which run out of the blade root 4 at an angle downwards.
  • This reduction in material in the blade root 4 leads to a reduced stiffness in areas of the end faces 8 and also in adjacent areas of the blade root 4. Areas adapted in this way have greater elasticity, so that deformations occurring during operation, in particular also at the pointed corners 6, are more favorable to be caught.
  • FIG. 4 shows the blade 3 from FIG. 3 in the installed state.
  • the reduction in material 5 in the blade root 4 leads to the fact that lines of force in the blade root 4 are interrupted and at these points the blade root 4 with respect to loads which arise due to the effective blade forces on the blade blade 7, via the adapted blade root 4 in the central region of the groove length L deflected and received there via the groove 2.
  • FIG. 5 shows a further embodiment of the invention.
  • the built-in blade root 4 has a recess 5 in a rather elongated shape, which pulls downwards out of the blade root 4 towards the center of the groove depth.
  • This recess can not only be achieved by milling, but also by means of a hole or similar machining methods.
  • recesses 5 are to be understood as adaptations to the rigidity of regions of the blade root 4.
  • all measures that change the rigidity of a blade root in at least one area can be used.
  • the invention creates a reduction of local stresses of 30% and more, depending on the size of the recess and the inclination of the installation angle.
  • the advantage of the invention is its low cost, its effectiveness and also the subsequent rigidity adjustment of blade bases in turbo machines that have already been put into operation.
  • Another advantage of the invention is the interchangeability of the blades. In this way, blade feet with and without material reduction can also be mounted together in one rotor disk.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un rotor (1) pour une turbomachine avec des pales (3) à monter dans des rainures (2) inclinées par rapport à l'axe de rotation du rotor. Au moins une base (4) de la pale comprend deux zones de rigidités diverses adaptées à des zones de la rainure (2), dans laquelle la base (4) de la pale est insérée, lesdites zones présentant également des rigidités diverses, de préférence équivalentes à celles de la pale. L'invention concerne également une pale (3) pour un rotor (1). L'invention est particulièrement utile dans des compresseurs de turbines à gaz et permet de réduire fortement les contraintes locales exercées sur les rainures.
EP97928110A 1996-06-21 1997-06-09 Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor Expired - Lifetime EP0906514B1 (fr)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
DE19624924 1996-06-21
DE19624924 1996-06-21
DE19642537 1996-10-15
DE19642537 1996-10-15
PCT/DE1997/001159 WO1997049921A1 (fr) 1996-06-21 1997-06-09 Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor

Publications (2)

Publication Number Publication Date
EP0906514A1 true EP0906514A1 (fr) 1999-04-07
EP0906514B1 EP0906514B1 (fr) 2001-10-24

Family

ID=26026814

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97928110A Expired - Lifetime EP0906514B1 (fr) 1996-06-21 1997-06-09 Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor

Country Status (6)

Country Link
US (1) US6065938A (fr)
EP (1) EP0906514B1 (fr)
JP (1) JP2000512707A (fr)
KR (1) KR20000022064A (fr)
DE (1) DE59705094D1 (fr)
WO (1) WO1997049921A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1136654A1 (fr) * 2000-03-21 2001-09-26 Siemens Aktiengesellschaft Aube rotorique de turbine
FR3087479A1 (fr) * 2018-10-23 2020-04-24 Safran Aircraft Engines Aube de turbomachine

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US6439851B1 (en) * 2000-12-21 2002-08-27 United Technologies Corporation Reduced stress rotor blade and disk assembly
US6428279B1 (en) * 2000-12-22 2002-08-06 General Electric Company Low windage loss, light weight closure bucket design and related method
US6846159B2 (en) 2002-04-16 2005-01-25 United Technologies Corporation Chamfered attachment for a bladed rotor
US6769877B2 (en) 2002-10-18 2004-08-03 General Electric Company Undercut leading edge for compressor blades and related method
EP1426553A1 (fr) * 2002-12-03 2004-06-09 Techspace Aero S.A. Réduction de la masse d'aubes mobiles
US7121803B2 (en) * 2002-12-26 2006-10-17 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US20040213672A1 (en) * 2003-04-25 2004-10-28 Gautreau James Charles Undercut leading edge for compressor blades and related method
US6902376B2 (en) * 2002-12-26 2005-06-07 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
SE526255C2 (sv) * 2003-03-14 2005-08-09 Sandvik Intellectual Property Verktyg och indexerbart skär för finsvarvning av rotationssymmetriska spår i arbetsstycken
DE10357134A1 (de) 2003-12-06 2005-06-30 Alstom Technology Ltd Rotor für einen Verdichter
US7252481B2 (en) * 2004-05-14 2007-08-07 Pratt & Whitney Canada Corp. Natural frequency tuning of gas turbine engine blades
US7156621B2 (en) * 2004-05-14 2007-01-02 Pratt & Whitney Canada Corp. Blade fixing relief mismatch
JP4869616B2 (ja) * 2005-04-01 2012-02-08 株式会社日立製作所 蒸気タービン動翼と蒸気タービンロータ及びそれを用いた蒸気タービン並びにその発電プラント
JP4584102B2 (ja) * 2005-09-30 2010-11-17 株式会社日立製作所 タービンロータと逆クリスマスツリー型タービン動翼及びそれを用いた低圧蒸気タービン並びに蒸気タービン発電プラント
FR2900989B1 (fr) * 2006-05-12 2008-07-11 Snecma Sa Ensemble pour compresseur de moteur d'aeronef comprenant des aubes a attache marteau a pied incline
FR2903138B1 (fr) * 2006-06-28 2017-10-06 Snecma Aube mobile et disque de rotor de turbomachine, et dispositif d'attache d'une telle aube sur un tel disque
FR2905139B1 (fr) * 2006-08-25 2012-09-28 Snecma Aube de rotor d'une turbomachine
FR2911632B1 (fr) 2007-01-18 2009-08-21 Snecma Sa Disque de rotor de soufflante de turbomachine
US8313289B2 (en) 2007-12-07 2012-11-20 United Technologies Corp. Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates
US8075280B2 (en) * 2008-09-08 2011-12-13 Siemens Energy, Inc. Composite blade and method of manufacture
JP5395455B2 (ja) * 2009-02-20 2014-01-22 三菱重工業株式会社 軸流圧縮機用動翼
EP2282010A1 (fr) 2009-06-23 2011-02-09 Siemens Aktiengesellschaft Aube de rotor pour une turbomachine à flux axial
FR2981132B1 (fr) * 2011-10-10 2013-12-06 Snecma Ensemble pour turbomachine a refroidissement de disque
FR3001646B1 (fr) * 2013-02-01 2015-09-11 Turbomeca Broche et procede de brochage d alveoles pour des pieces telles que des disques de rotor de turbine ou des disques de compresseur de turbomachine
JP2016035209A (ja) * 2014-08-01 2016-03-17 三菱日立パワーシステムズ株式会社 軸流圧縮機、及び軸流圧縮機を備えたガスタービン
GB2529681B (en) * 2014-08-29 2019-02-20 Rolls Royce Plc Gas turbine engine rotor arrangement
CN104265377B (zh) * 2014-09-16 2016-01-20 上海金通灵动力科技有限公司 一种降低纵树型轮毂型线处应力的结构
US9896947B2 (en) * 2014-12-15 2018-02-20 United Technologies Corporation Turbine airfoil attachment with multi-radial serration profile
US10400784B2 (en) * 2015-05-27 2019-09-03 United Technologies Corporation Fan blade attachment root with improved strain response
US20180112544A1 (en) 2016-10-26 2018-04-26 Siemens Aktiengesellschaft Turbine rotor blade, turbine rotor arrangement and method for manufacturing a turbine rotor blade
FR3062875B1 (fr) * 2017-02-10 2021-07-02 Safran Aircraft Engines Aube mobile de turbomachine comprenant des evidements dans le pied
JP7031270B2 (ja) * 2017-12-08 2022-03-08 株式会社リコー 検査装置、検査システム及び検査方法
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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
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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1136654A1 (fr) * 2000-03-21 2001-09-26 Siemens Aktiengesellschaft Aube rotorique de turbine
WO2001071166A1 (fr) * 2000-03-21 2001-09-27 Siemens Aktiengesellschaft Aube mobile de turbine
FR3087479A1 (fr) * 2018-10-23 2020-04-24 Safran Aircraft Engines Aube de turbomachine
US11156107B2 (en) 2018-10-23 2021-10-26 Safran Aircraft Engines Turbomachine blade

Also Published As

Publication number Publication date
WO1997049921A1 (fr) 1997-12-31
US6065938A (en) 2000-05-23
KR20000022064A (ko) 2000-04-25
DE59705094D1 (de) 2001-11-29
JP2000512707A (ja) 2000-09-26
EP0906514B1 (fr) 2001-10-24

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