EP0906514B1 - Rotor für eine turbomaschine mit in nuten anbringbaren schaufeln sowie schaufel für einen rotor - Google Patents

Rotor für eine turbomaschine mit in nuten anbringbaren schaufeln sowie schaufel für einen rotor Download PDF

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Publication number
EP0906514B1
EP0906514B1 EP97928110A EP97928110A EP0906514B1 EP 0906514 B1 EP0906514 B1 EP 0906514B1 EP 97928110 A EP97928110 A EP 97928110A EP 97928110 A EP97928110 A EP 97928110A EP 0906514 B1 EP0906514 B1 EP 0906514B1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade root
turbomachine
blade
slot
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.)
Expired - Lifetime
Application number
EP97928110A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0906514A1 (de
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/de
Application granted granted Critical
Publication of EP0906514B1 publication Critical patent/EP0906514B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

  • the present invention relates to a rotor for a turbomachine with blades which can be fitted in grooves, the grooves are attached obliquely to the axis of rotation of the rotor, and a blade for a rotor.
  • a rotor for example known from US-A-2 643 853.
  • GB-A-2 237 846 relates to a gas turbine for an aircraft engine, reducing the mass of the turbine rotor to increase safety when operating a maximum speed is described. This mass reduction takes place in that the blade root of a turbine blade two separated by a continuous groove and has spaced parts. These parts of the Blade root are spaced from each other by two partitions, which lead to a spreading of the blade root.
  • the object of the present invention is now that in operation to reduce a strength problem occurring in a rotor and specify a suitable combination of blade root and groove.
  • a rotor for a turbomachine is used to solve this task with the features of claim 1 and with a shovel the features of claim 6.
  • Advantageous features and combinations result from the in the respective dependent claims disclosed features.
  • a preferred embodiment provides that a corresponding adapted area of the blade root and a stiffer in contrast Area of the groove to each other or opposite. Thereby is achieved that the corresponding stiffness of the groove and Blade base correspond so that there is an equalization of the tensions that occur.
  • the flow of force when transmitting power from the blade root in the groove can be designed inexpensively with appropriate adaptation. It is also favorable if the highest occurring in the groove area Voltage, in particular in the area of sharp corners of the groove in the rotor, an area diminished Stiffness of the blade root is present, so that when the Turbomachine no tensions occur, leading to destruction or material fatigue from prolonged operation of the turbomachine to lead.
  • An advantageous and preferred embodiment of the invention is based on a gas turbine compressor, which is a preferred turbomachine for applying the invention, shown.
  • the rotor 1 of the turbomachine is preferably off axially arranged one behind the other, interlocked (Serration), by a tie rod, not shown interconnected rotor disks 1 are formed.
  • FIG. 1 shows a section of a rotor disk 1 with a groove. 2 inserted blades 3.
  • Each blade 3 has areas with different stiffness. Suitable for this is in Blade foot 4 has a recess 5 so that the groove 2, which have an unevenly high rigidity across their groove depth has an adapted rigidity of the blade root 4 opposite. Since one in particular at the sharp corner 6 (see FIG. 2) Groove 2, which is located at the end of the groove, during operation of the gas turbine increased voltages occur in the compressor Area of the blade root 4, the recess 5 is formed on that, at this point, he is slightly compliant. An advantageous one Design of the recess 5 sees this in the form a cutout on the front 8 of the blade root 4 runs out of it at an angle downwards.
  • FIG. 2 shows the rotor disk 1 from FIG. 1 in a top view.
  • the grooves 2 are at an installation angle ⁇ to the axis of rotation the rotor disc 1 attached, due to the adapted Bucket feet 4 can be much larger compared to conventional installation angles. This is especially important for Gas turbines and their compressors with a low mass flow special role. There can be larger blade angles and thus larger installation angles ⁇ may be required. This leads in turn to increased local stresses in the groove 2, especially in the sharp corners 6 stiffness reduced by the increased angle available.
  • the pointed corners 6 are places higher locally Tension. They are the ends of the dashed lines, groove width D located on the inside of the rotor 1. Seen over the groove length L, it is not only in their depth, but also different in their extent Areas of different voltages, therefore different Influence on the strength when the blade root is installed 4 and operation of the turbomachine.
  • Figure 3 shows a blade root 4 according to the invention with indicated Extension of the blade 7 of the blade 3.
  • This has a recess 5 starting at both End faces 8, which are inclined downward from the blade root 4 run out.
  • This reduction in material in the blade root 4 leads to reduced stiffness in areas of the end faces 8 and also in adjacent areas of the blade root 4.
  • Such adapted areas have greater elasticity, so that deformations occurring in operation, especially also the sharp corners 6 can be caught cheaper.
  • 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 that lines of force in the blade root 4 are interrupted and on these places the blade root 4 against loads on Arise on the blade 7 due to the acting blade forces, over the adapted blade root 4 in the middle area the groove length L is deflected and received there via the groove 2 become.
  • FIG. 5 shows a further embodiment of the invention.
  • the built-in blade root 4 has a recess 5 in a rather elongated shape that extends towards the center of the groove depth pulls out of the blade root 4 below.
  • This recess can not only by means of milling but also through a hole or similar machining methods can be achieved.
  • For the purpose of of the invention are not only recesses 5 as adjustments to understand the rigidity of areas of the blade root 4. Rather, all measures that affect the rigidity of a Change blade root in at least one area, applicable. For example, inserting or processing one other material in the blade root possible, which opposite this has a higher elasticity. Is particularly cheap it that in compressors or generally turbomachinery, which in alternating operation, an adjustment of the areas of the blade root 4 to that operating area of the turbomachine is ajar, in which this is mostly driven becomes.
  • the invention creates in this example depending on Size of the recess and slope of the installation angle a reduction of local stresses of 30% and more.
  • the advantage The invention is its low cost, its effectiveness as well as the subsequent rigidity adjustment of blade feet with turbo machines already in operation.
  • Another advantage of the invention is the interchangeability Shovels. This means that shovel feet can be made with and without material reduction be mounted together in a 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)
EP97928110A 1996-06-21 1997-06-09 Rotor für eine turbomaschine mit in nuten anbringbaren schaufeln sowie schaufel für einen rotor Expired - Lifetime EP0906514B1 (de)

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 (de) 1996-06-21 1997-06-09 Rotor für eine turbomaschine mit in nuten anbringbaren schaufeln sowie schaufel für einen rotor

Publications (2)

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

Family

ID=26026814

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97928110A Expired - Lifetime EP0906514B1 (de) 1996-06-21 1997-06-09 Rotor für eine turbomaschine mit in nuten anbringbaren schaufeln sowie schaufel für einen rotor

Country Status (6)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018077589A1 (en) 2016-10-26 2018-05-03 Siemens Aktiengesellschaft Turbine rotor arrangement and method for manufacturing a turbine rotor blade

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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 (de) * 2009-06-23 2011-02-09 Siemens Aktiengesellschaft Laufschaufel für eine axial durchströmbare Turbomaschine
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
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
FR3087479B1 (fr) * 2018-10-23 2022-05-13 Safran Aircraft Engines Aube de turbomachine
US10815799B2 (en) * 2018-11-15 2020-10-27 General Electric Company Turbine blade with radial support, shim and related turbine rotor
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
CN111412183B (zh) * 2020-04-24 2021-05-18 上海应达风机股份有限公司 一种风机叶轮及其加工制造工艺
KR20230081267A (ko) 2021-11-30 2023-06-07 두산에너빌리티 주식회사 터빈 블레이드, 이를 포함하는 터빈 및 가스터빈

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018077589A1 (en) 2016-10-26 2018-05-03 Siemens Aktiengesellschaft Turbine rotor arrangement and method for manufacturing a turbine rotor blade

Also Published As

Publication number Publication date
US6065938A (en) 2000-05-23
EP0906514A1 (de) 1999-04-07
WO1997049921A1 (de) 1997-12-31
DE59705094D1 (de) 2001-11-29
JP2000512707A (ja) 2000-09-26
KR20000022064A (ko) 2000-04-25

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