EP1284339A1 - Anneau de rétention et d'étanchéité pour un rotor d'une turbine à gaz - Google Patents

Anneau de rétention et d'étanchéité pour un rotor d'une turbine à gaz Download PDF

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Publication number
EP1284339A1
EP1284339A1 EP01119560A EP01119560A EP1284339A1 EP 1284339 A1 EP1284339 A1 EP 1284339A1 EP 01119560 A EP01119560 A EP 01119560A EP 01119560 A EP01119560 A EP 01119560A EP 1284339 A1 EP1284339 A1 EP 1284339A1
Authority
EP
European Patent Office
Prior art keywords
ring system
grooves
segments
ring segments
cover ring
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Withdrawn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
EP01119560A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
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 EP01119560A priority Critical patent/EP1284339A1/fr
Priority to PCT/EP2002/008892 priority patent/WO2003016679A1/fr
Publication of EP1284339A1 publication Critical patent/EP1284339A1/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Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • the present invention relates to a cover ring system for Blade disks of gas turbines.
  • Blade disks in the sense of the present invention relates refer to all types of blade arrangements, i.e. disks, Wreaths, support ring systems and the like. Still is embodied and characterized the invention in relation to gas turbines, however, that refers to corresponding energy-producing Turbomachinery.
  • the blade disks are radial disk bores for supplying cooling air arranged.
  • Front and / or rear cover plates are used for sealing and locking pins or locking plates secure the blades against axial displacement. This structure enables maintenance and replacement work individual blades or groups of blades, without the rotor unstacking.
  • the invention has for its object to provide a cover ring system for blade disks of gas turbines, with which the required functions, namely blade shear, cooling air supply and seal can be performed and which carry out maintenance and replacement work on individual blades or blade groups without Unstacking of the runner enables.
  • the invention proposes a cover ring system for blade disks of gas turbines, consisting of ring segments with grooves arranged in the end edge surfaces, and of strip-shaped sealing plates, the ring segments being left in these blades with gaps between adjacent segments on a blade disk Axial displacement can be securely positioned and even secured against radial displacement, and the sealing plates can be inserted and fixed in the grooves of adjacent ring segments in a sealing manner.
  • ring segments that are separate on the blade disc can be arranged, causes at the separation points Gap additionally sealed by sealing plates become.
  • the ring segments are essentially mutually related same and have one from the inner to the outer circumference Axial direction extending cross section, d. i.e., are in Contoured axial direction. Thus, cooling air holes and Guided tours are trained.
  • the segments have ribs.
  • Insertion of the ring segment on the disc is then done by radial Push inwards, push the segment axially to the disc and pulling radially outwards to catch.
  • Dismantling is done by pushing radially inwards for the end hook, pull it off axially until the notch is released Hooking and then radial removal of the segments.
  • the End edges of the ring segments are formed grooves.
  • Adjoining ring segments are then inserted.
  • a plurality of grooves are advantageous trained who intersect.
  • the sealing plates to be inserted thus cross each other.
  • the grooves led to an outer surface to push in and pull out of the sealing plates in the gap area to be able to.
  • the sealing plates according to the invention in their dimensions the groove lengths on the one hand and the gap widths on the other. That is, the sealing plates are so wide that they Cover gaps can be inserted into the grooves of adjacent segments are, and so long that they are complete without protruding are mountable. Furthermore, the sealing plates according to an advantageous proposal of the invention notches to cross over when inserting into intersecting grooves to enable the sealing plates, so that the Secure the sealing plates to one another.
  • the invention makes it simple and economical to set up Cover ring system for blade disks of gas turbines provided, which on the one hand with very few parts on the other hand the possibilities of blade cooling, the bucket lock and the seal combine and nevertheless maintenance and exchange work on individual Allow blades or blade groups without destacking the rotor. Because of the use of very few parts have significant economic advantages over all known solutions.
  • the ring segment 1 shown in Fig. 1 has an outer circumference 2 and an inner circumference 3. In between is the ring area with an axial extension 4, d. H. a sufficient one Thickness on the one hand and a desired contouring on the other hand for the desired purpose of flow guidance.
  • ribs 5 are on one surface of the ring segment. Furthermore, the Ring segments over front edges 6 and 7.
  • segment course following groove 8 formed, which is an undercut Groove acts to hook in this way a corresponding hook ring of a disc, not shown to enable.
  • Grooves 10, 11, 12 and 13 are formed in the front edges 6 and 7, that intersect at appropriate points and moreover, if reasonable, opened to the surface are carried out. These opening areas are exemplary designated 14, 15, 16. But there are also other opening areas in the area of other grooves or in other places.
  • FIG. 2 schematically shows how two ring segments 1 on a disc 17 leaving a gap 18 are positioned.
  • 3a to 3d show exemplary embodiments for sealing sheets, which together form a system in the adjacent grooves Ring segments are insertable, in such a way that they secure each other.
  • the Sealing plates 19, 20, 21 and 22 notches 23, 24, 25, 26 and, if necessary, others.
  • the arrangement of the sealing plates is purely schematic in FIG. 4 shown in the grooves of a ring segment 1 shown.
  • the sheets 20, 21 are attached, then the sheets 19 and 22.
  • the sheet 22 is in the area 27 provided with a bend and thus secured to the ring segment.
  • the sheet 21 at least partially covers the bore 9 and thus secures the attached safety bolt, not shown against axial movement or against falling out.
  • the overall system of mutually securing individual elements can be assembled in the simplest way.
  • a ring segment becomes radially parallel to a disc shifted inwards, then pressed axially against the disc and then pulled radially outward to align with the Groove 8 on a corresponding hook element of the disc snag.
  • a locking pin not shown in the hole 9 inserted in a corresponding Bore of the disc, not shown, to be used.
  • further locking pins in comparable Bores of the ring segment used and finally assembled the remaining ring segments.
  • the sealing plates secure each other and finally the last sealing plate with a bend secured.
  • Securing bolt secured. It is therefore a complete one Sealing ring, the blades in the area of the blade grooves securing and created for the supply of cooling air.
  • the exemplary embodiment described serves only for explanation and is not restrictive.
  • the shape of the sealing plates, their latches and the securing of the Sheets can be changed according to needs.
  • V-shaped gaps arise and the locking washers accordingly have trapezoidal surface contours.
  • the fuse can also be done with securing elements and the like.
  • the notches can also be designed as required his.
  • the securing of the disks can vary be, the one inserted into the through hole Locking pin represents an embodiment which can be changed as required.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01119560A 2001-08-14 2001-08-14 Anneau de rétention et d'étanchéité pour un rotor d'une turbine à gaz Withdrawn EP1284339A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP01119560A EP1284339A1 (fr) 2001-08-14 2001-08-14 Anneau de rétention et d'étanchéité pour un rotor d'une turbine à gaz
PCT/EP2002/008892 WO2003016679A1 (fr) 2001-08-14 2002-08-08 Anneau de fixation segmente pour les pales d'une turbine et procede pour monter et demonter ledit anneau de fixation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01119560A EP1284339A1 (fr) 2001-08-14 2001-08-14 Anneau de rétention et d'étanchéité pour un rotor d'une turbine à gaz

Publications (1)

Publication Number Publication Date
EP1284339A1 true EP1284339A1 (fr) 2003-02-19

Family

ID=8178325

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01119560A Withdrawn EP1284339A1 (fr) 2001-08-14 2001-08-14 Anneau de rétention et d'étanchéité pour un rotor d'une turbine à gaz

Country Status (2)

Country Link
EP (1) EP1284339A1 (fr)
WO (1) WO2003016679A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1703082A1 (fr) * 2005-02-23 2006-09-20 Rolls-Royce Plc Plaque latérale
EP1944471A1 (fr) * 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'une rotor de turbine
US7465149B2 (en) 2006-03-14 2008-12-16 Rolls-Royce Plc Turbine engine cooling
EP2182170A1 (fr) * 2008-10-30 2010-05-05 Siemens Aktiengesellschaft Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
CN102116180A (zh) * 2010-01-05 2011-07-06 通用电气公司 涡轮密封板组件
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9366151B2 (en) * 2012-05-07 2016-06-14 General Electric Company System and method for covering a blade mounting region of turbine blades
TWI696751B (zh) * 2016-12-13 2020-06-21 日商三菱日立電力系統股份有限公司 燃氣渦輪機的分解組裝方法、密封板組裝體、燃氣渦輪機輥、然氣渦輪機及燃氣渦輪機的製造方法
MX2019006639A (es) 2016-12-13 2019-08-01 Mitsubishi Hitachi Power Sys Metodo para desmontar/montar turbina de gas, montaje de placa selladora y rotor de turbina de gas.
EP3536907B1 (fr) 2016-12-13 2021-03-31 Mitsubishi Power, Ltd. Procédé de désassemblage/assemblage de turbine à gaz, rotor de turbine à gaz et turbine à gaz

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2998959A (en) * 1955-09-29 1961-09-05 Rolls Royce Bladed rotor of axial-flow fluid machine with means to retain blades in position on rotor
US3043562A (en) * 1961-04-10 1962-07-10 Gen Electric Combination sealing and restraining member for long-shank turbo-machine buckets
US3137478A (en) * 1962-07-11 1964-06-16 Gen Electric Cover plate assembly for sealing spaces between turbine buckets
DE1258662B (de) * 1964-10-28 1968-01-11 Goerlitzer Maschb Veb Deckscheibe fuer die Kuehlgasfuehrung von Gasturbinenlaeufern
DE2908242A1 (de) * 1978-03-08 1979-09-13 Snecma Ringfoermiger flansch fuer einen laeufer einer stroemungsmaschine
WO2000057031A1 (fr) * 1999-03-19 2000-09-28 Siemens Aktiengesellschaft Rotor de turbine a gaz dote d'une aube a refroidissement interne

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3300179A (en) * 1966-04-22 1967-01-24 Gen Motors Corp Blade stalk cover plate
GB2244100A (en) * 1990-05-16 1991-11-20 Rolls Royce Plc Retaining gas turbine rotor blades
US6234756B1 (en) * 1998-10-26 2001-05-22 Allison Advanced Development Company Segmented ring blade retainer

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2998959A (en) * 1955-09-29 1961-09-05 Rolls Royce Bladed rotor of axial-flow fluid machine with means to retain blades in position on rotor
US3043562A (en) * 1961-04-10 1962-07-10 Gen Electric Combination sealing and restraining member for long-shank turbo-machine buckets
US3137478A (en) * 1962-07-11 1964-06-16 Gen Electric Cover plate assembly for sealing spaces between turbine buckets
DE1258662B (de) * 1964-10-28 1968-01-11 Goerlitzer Maschb Veb Deckscheibe fuer die Kuehlgasfuehrung von Gasturbinenlaeufern
DE2908242A1 (de) * 1978-03-08 1979-09-13 Snecma Ringfoermiger flansch fuer einen laeufer einer stroemungsmaschine
WO2000057031A1 (fr) * 1999-03-19 2000-09-28 Siemens Aktiengesellschaft Rotor de turbine a gaz dote d'une aube a refroidissement interne

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1703082A1 (fr) * 2005-02-23 2006-09-20 Rolls-Royce Plc Plaque latérale
US7465149B2 (en) 2006-03-14 2008-12-16 Rolls-Royce Plc Turbine engine cooling
EP1944471A1 (fr) * 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'une rotor de turbine
CN101220756B (zh) * 2007-01-09 2010-11-03 西门子公司 涡轮机转子的轴向转子部段
EP2182170A1 (fr) * 2008-10-30 2010-05-05 Siemens Aktiengesellschaft Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
CN102116180A (zh) * 2010-01-05 2011-07-06 通用电气公司 涡轮密封板组件
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Also Published As

Publication number Publication date
WO2003016679A1 (fr) 2003-02-27

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