EP1215367A2 - Dispositif de fixation des aubes de turbomachine - Google Patents

Dispositif de fixation des aubes de turbomachine Download PDF

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Publication number
EP1215367A2
EP1215367A2 EP01128574A EP01128574A EP1215367A2 EP 1215367 A2 EP1215367 A2 EP 1215367A2 EP 01128574 A EP01128574 A EP 01128574A EP 01128574 A EP01128574 A EP 01128574A EP 1215367 A2 EP1215367 A2 EP 1215367A2
Authority
EP
European Patent Office
Prior art keywords
blades
fixing device
wedge element
fastening groove
rotor
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
EP01128574A
Other languages
German (de)
English (en)
Other versions
EP1215367B1 (fr
EP1215367A3 (fr
Inventor
Rene Bachofner
Wolfgang Kappis
Pavel Dr. Rihak
Ferdinand Thüringer
Ulrich Waltke
Hans Dr. Wettstein
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Alstom Power NV
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 Alstom Technology AG, Alstom Power NV filed Critical Alstom Technology AG
Publication of EP1215367A2 publication Critical patent/EP1215367A2/fr
Publication of EP1215367A3 publication Critical patent/EP1215367A3/fr
Application granted granted Critical
Publication of EP1215367B1 publication Critical patent/EP1215367B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/37—Impeller making apparatus
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the invention relates to a fixing device for blading a Fluid machine, in which a number of blades along a fastening groove introduced and between at least two within the mounting groove An intermediate assembly gap is provided adjacent to the blades two insert elements designed as end halves, which in the Assembly gap can be used and one each to the width of the Intermediate assembly gap have adjusted width and a between them Include a gap into which a wedge element can be inserted that can be wedged in this way is that both end halves are non-positively by the wedge element inside the Fastening groove are fixed.
  • Blades of the above type relate to guidance, but in particular Blades within turbomachines, such as the compressors or Turbine stage of a gas turbine plant.
  • the explanations below preferably refer to blades running along a mounting groove that is provided within the rotor of a turbomachine and this along its Circumferential circumferences are fixed and depending on the respective Position the flow conditions in a suitable manner and opposite possible misalignments occurring during the operation of the Turbo machines but especially against complete detachment from the The fastening groove must be reliably secured. That in relation to the blades too Measures as described below can also be taken also on those in the fixed housing components of turbomachinery integrated guide vanes find application.
  • Known security measures against self-releasing individual blades from the mounting groove generally refer to reducing the clearance between two adjacent blade feet within the fastening groove in the circumferential direction.
  • FIG. 2a shows a cross section through a Fastening groove 1, which is incorporated within a rotor 2.
  • the so-called rotor closure 4 is radial between the two blades 31, 32 in the mounting groove 1 inserted.
  • the rotor end 4 consists, as in Figure 2b in Individual emerges from two so-called closing halves 41, 42 and a wedge element 43.
  • the sides of the closing halves 41, 42 facing the fastening groove 1 are for a positive and positive engagement with the inner contour of the Fastening groove 1 designed accordingly.
  • both end halves 41, 42 When inserted within the Fastening groove 1, both end halves 41, 42 include an intermediate gap 5, in which the wedge element 43 can be inserted radially.
  • the End halves 41, 42 In the upper area, the End halves 41, 42 have a corresponding recess 6 (see Fig. 2b), the each resembles half a heart shape, in the retaining tab 44 of the wedge element 43 as shown in Figure 2a, be spread permanently to both end halves 41, 42 to press permanently against the inner contour of the fastening groove 1.
  • a fixing device according to the preamble of Claim 1, see for example a generic fixing device under Reference to Figures 2a - 2c, designed such that the wedge element at least one connecting element to the side of a blade and at least one of the two blades adjacent to the wedge element one to the Connection element provides corresponding counter-contour, so that Wedge element and the blade an intimate positive connection with each other received.
  • the idea underlying the invention is to create an intimate one Positive connection between the wedge element and at least one directly adjacent blade so that there are no relative displacements between the Blade and the wedge element and connected to the entire rotor tail can occur, whereby the risk potential described above be decisively restricted with regard to the detachment of the wedge element can.
  • the wedge element is direct with both adjacent blades via respective positive connection elements connected.
  • Figure 1a shows a plan view of a composite consisting of two within one Fastening groove (not shown) inserted blades 31, 32 and one rotor end located between the blades 31, 32 4.
  • the rotor end 4 has a wedge element 43, which on its rotor blades 31, 32 facing sides each designed as a dovetail Has connecting element 45, each in one, within the blades 31, 32 incorporated counter contour 46 engages positively and non-positively.
  • the counter contours are 46 clearly visible within the blades 31, 32.
  • To assemble the rotor tail 4 designed according to the invention are first the End halves 41, 42 in the intermediate gap between the blades 31, 32 inserted radially into the mounting groove. Then that will Wedge element 43 designed according to the invention also radially both in the Intermediate gap between the two closing halves 41, 42 as well as within the opposite counter contours 46 of the blades 31, 32 radially introduced.
  • the two adjacent blades 31, 32 by the Wedge element 43 mechanically connected to one another. Is the wedge element 43 completely sunk between the end halves 41, 42, so the retaining tabs 44 of the wedge element 43 in the heart-shaped recesses 6 with the help a suitable tool.
  • connection profiles are also conceivable, for example Hammer profiles of all kinds as well as fir tree profiles.
  • the Counter contour 46 within the blade root of the individual moving blades 31, 32 brought in.
  • the counter contour 46 does not necessarily extend over the total depth of the blade root.
  • Figure 1c is a side view of the rotor tail designed according to the invention 4 shown.
  • Wedge element 43 which is designed according to the invention as a dovetail Connecting element 45, which according to the embodiment in Figure 1c extends the entire length of the blade root.
  • the wedge element 43 has two retaining tabs 44 which fit into the corresponding one Engage recess 6 within the blades 41, 42.

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)
EP01128574A 2000-12-16 2001-11-30 Dispositif de fixation des aubes de turbomachine Expired - Lifetime EP1215367B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10062908 2000-12-16
DE10062908 2000-12-16

Publications (3)

Publication Number Publication Date
EP1215367A2 true EP1215367A2 (fr) 2002-06-19
EP1215367A3 EP1215367A3 (fr) 2004-01-21
EP1215367B1 EP1215367B1 (fr) 2006-12-27

Family

ID=7667528

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01128574A Expired - Lifetime EP1215367B1 (fr) 2000-12-16 2001-11-30 Dispositif de fixation des aubes de turbomachine

Country Status (3)

Country Link
US (1) US6647602B2 (fr)
EP (1) EP1215367B1 (fr)
DE (2) DE10134611A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1457642A2 (fr) * 2003-03-11 2004-09-15 Alstom Technology Ltd Dispositif de fixation d'aubes sur un rotor
EP1698758A2 (fr) * 2005-02-23 2006-09-06 ALSTOM Technology Ltd Fermeture de rotor à fente axiale
US7367778B2 (en) 2005-02-23 2008-05-06 Alstom Technology Ltd. Rotor end piece
WO2016195657A1 (fr) * 2015-06-02 2016-12-08 Siemens Aktiengesellschaft Ensemble entretoise de blocage entre des structures d'aube de compresseur dans un moteur à turbine

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10346239A1 (de) 2003-10-06 2005-04-21 Alstom Technology Ltd Baden Verfahren zur Fixierung für die Beschaufelung einer Strömungsmaschine und Fixiervorrichtung
US7435055B2 (en) * 2005-03-29 2008-10-14 Siemens Power Generation, Inc. Locking spacer assembly for a turbine engine
EP1803899A1 (fr) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Ensemble de verrouillage d'aube pour une turbomachine
EP1803900A1 (fr) 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Ensemble de fermeture pour clore l'interstice restant entre la première et la dernière des aubes d'un anneau aubagé disposées dans la rainure circonférencielle d'une turbomachine, et turbomachine correspondante
US8523529B2 (en) * 2009-11-11 2013-09-03 General Electric Company Locking spacer assembly for a circumferential entry airfoil attachment system
US20110255978A1 (en) * 2010-04-16 2011-10-20 Brian Denver Potter Locking Assembly For Circumferential Attachments
US9175572B2 (en) * 2012-04-16 2015-11-03 General Electric Company Turbomachine blade mounting system
US9341071B2 (en) * 2013-10-16 2016-05-17 General Electric Company Locking spacer assembly
EP3115554A1 (fr) * 2015-07-09 2017-01-11 Siemens Aktiengesellschaft Système d'aube avec des éléments de support élastiques pour une turbomachine thermique
US10465699B2 (en) 2017-01-26 2019-11-05 DOOSAN Heavy Industries Construction Co., LTD Compressor blade locking mechanism in disk with tangential groove
US10519970B2 (en) 2017-02-09 2019-12-31 DOOSAN Heavy Industries Construction Co., LTD Compressor blade locking mechanism in disk with tangential groove
WO2019190494A1 (fr) 2018-03-28 2019-10-03 Siemens Aktiengesellschaft Ensemble entretoise de verrouillage, ensemble lame correspondant, procédé d'installation d'une entretoise de verrouillage
CN111954751B (zh) 2018-04-18 2022-06-21 西门子能源全球两合公司 锁定间隔器组件、相对应的叶片组件、用于安装锁定间隔器的方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE812337C (de) * 1948-09-17 1951-08-27 Hermann Oestrich Dr Ing Schlussstueck fuer die Beschaufelung der Trommellaeufer von Kreiselradmaschinen

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3721506A (en) * 1971-05-25 1973-03-20 Gen Electric Split-nut blade locking assembly
DE19654471B4 (de) * 1996-12-27 2006-05-24 Alstom Rotor einer Strömungsmaschine
DE19728345A1 (de) * 1997-07-03 1999-01-07 Asea Brown Boveri Kraft- und formschlüssige Verbindung von rotierenden Bauteilen
EP1124038A1 (fr) * 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Aubage de turbine
US6439841B1 (en) * 2000-04-29 2002-08-27 General Electric Company Turbine frame assembly
US6517313B2 (en) * 2001-06-25 2003-02-11 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
US6582195B2 (en) * 2001-06-27 2003-06-24 General Electric Company Compressor rotor blade spacer apparatus

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE812337C (de) * 1948-09-17 1951-08-27 Hermann Oestrich Dr Ing Schlussstueck fuer die Beschaufelung der Trommellaeufer von Kreiselradmaschinen

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1457642A2 (fr) * 2003-03-11 2004-09-15 Alstom Technology Ltd Dispositif de fixation d'aubes sur un rotor
EP1457642A3 (fr) * 2003-03-11 2006-07-26 Alstom Technology Ltd Dispositif de fixation d'aubes sur un rotor
US7192256B2 (en) 2003-03-11 2007-03-20 Alstom Technology Ltd. Rotor end piece
CN1534167B (zh) * 2003-03-11 2010-05-26 阿尔斯托姆科技有限公司 转子末端
EP1698758A2 (fr) * 2005-02-23 2006-09-06 ALSTOM Technology Ltd Fermeture de rotor à fente axiale
US7338258B2 (en) 2005-02-23 2008-03-04 Alstom Technology Ltd. Axially separate rotor end piece
US7367778B2 (en) 2005-02-23 2008-05-06 Alstom Technology Ltd. Rotor end piece
EP1698758A3 (fr) * 2005-02-23 2013-03-27 Alstom Technology Ltd Fermeture de rotor à fente axiale
WO2016195657A1 (fr) * 2015-06-02 2016-12-08 Siemens Aktiengesellschaft Ensemble entretoise de blocage entre des structures d'aube de compresseur dans un moteur à turbine

Also Published As

Publication number Publication date
US6647602B2 (en) 2003-11-18
DE10134611A1 (de) 2002-06-27
EP1215367B1 (fr) 2006-12-27
US20020127105A1 (en) 2002-09-12
EP1215367A3 (fr) 2004-01-21
DE50111726D1 (de) 2007-02-08

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