EP1507960B1 - Beschaufelte Rotorscheibe einer Turbomaschine - Google Patents

Beschaufelte Rotorscheibe einer Turbomaschine Download PDF

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Publication number
EP1507960B1
EP1507960B1 EP03756014.1A EP03756014A EP1507960B1 EP 1507960 B1 EP1507960 B1 EP 1507960B1 EP 03756014 A EP03756014 A EP 03756014A EP 1507960 B1 EP1507960 B1 EP 1507960B1
Authority
EP
European Patent Office
Prior art keywords
fact
elastic
platforms
wheel
zone
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
EP03756014.1A
Other languages
English (en)
French (fr)
Other versions
EP1507960A1 (de
Inventor
Chantal Giot
Marc Marchi
Christian Gosselin
Eric Bil
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1507960A1 publication Critical patent/EP1507960A1/de
Application granted granted Critical
Publication of EP1507960B1 publication Critical patent/EP1507960B1/de
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
    • F01D5/3007—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
    • 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
    • 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
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the upper wall 19 of the liner is spread over its greater extent from the lower face of the platform 34, as is visible on the figure 5 , the shirt 10 tilting about an axis intersecting the plane of the figure 5 at the point referenced 44 and located in the vicinity of the downstream flared edge 13.
  • the protrusion 43 of the upstream radial wall 35 makes it possible to limit the sliding of the elastic zone 18, and to retain the liner 10 in the upper zone of the cavity 37.

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)

Claims (6)

  1. Beschaufeltes Rad einer Turbomaschine, umfassend eine Scheibe (31), die an ihrem Umfang eine Vielzahl von im Wesentlichen axialen Vertiefungen aufweist, eine Vielzahl von Schaufeln (33), deren Füße in den Vertiefungen gehalten sind und die Plattformen (34), welche dazu bestimmt sind, auf der radial inneren Seite den Gasstromkanal (F) zu begrenzen, sowie stromaufwärtige (35) und stromabwärtige (36) Radialwände, welche sich von den Plattformen (34) aus in Richtung des Umfangs der Scheibe erstrecken, aufweisen, Zwischenschaufelhohlräume (37), welche durch die Plattformen und den Umfang der Scheibe begrenzt sind, und Vorrichtungen zum Abdichten der Zwischenschaufelräume, welche in Form von Ummantelungen (10) ausgebildet sind, die radial nach innen erweiterte Ränder (12, 13, 14, 15) aufweisen und in den Hohlräumen (37) an den Wänden der Plattformen von zwei benachbarten Schaufeln angeordnet sind, dadurch gekennzeichnet, dass jede Ummantelung (10) an einem ihrer erweiterten Ränder (12), stromaufwärtigen oder stromabwärtigen, einen elastischen Bereich (18) aufweist und die an diesen Rand angrenzenden Radialwände (35) an die Plattformen (34) durch Innenflächen (39) angeschlossen sind, die gegenüber einer Radialebene geneigt sind und an denen der elastische Bereich (18) in Anlage ist, derart, dass der elastische Bereich im Falle eines Stopps der Rotation des Rades radial nach innen und unter der Wirkung der Fliehkräfte radial nach außen gleiten kann, um die Ummantelung (10) so zu beaufschlagen, dass sie sich axial in Richtung der von dem elastischen Bereich (18) entfernten Radialwände (36) bewegt, um die Dichtigkeit in diesem Bereich zu verbessern,
    dadurch gekennzeichnet, dass die elastischen Bereiche (18) umfangseitig durch zwei Einschnitte (16, 17), welche in dem entsprechenden erweiterten Rand (12) der Ummantelungen (10) ausgebildet sind, begrenzt sind.
  2. Rad nach Anspruch 1, dadurch gekennzeichnet, dass die Radialwände (36), welche von den elastischen Bereichen entfernt sind, Anschläge (42) umfassen, um die Axialbewegung der Ummantelungen (10) unter der Wirkung der Fliehkräfte zu begrenzen.
  3. Rad nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass die Seitenwände (36), welche an die elastischen Bereiche (18) angrenzen, Anschläge (42) umfassen, um das Einwärtsgleiten der elastischen Bereiche zu begrenzen.
  4. Rad nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass der elastische Bereich (18) an dem stromaufwärtigen Rand vorgesehen ist.
  5. Rad nach Anspruch 4, dadurch gekennzeichnet, dass es sich um ein beschaufeltes Turbinenrad handelt.
  6. Rad nach Anspruch 5, dadurch gekennzeichnet, dass der Winkel α der geneigten Fläche (39) größer als die Neigung der Plattform gegenüber der Rotationsachse der Turbomaschine ist.
EP03756014.1A 2002-05-30 2003-05-28 Beschaufelte Rotorscheibe einer Turbomaschine Expired - Lifetime EP1507960B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0206599 2002-05-30
FR0206599A FR2840352B1 (fr) 2002-05-30 2002-05-30 Maitrise de la zone de fuite sous plate-forme d'aube
PCT/FR2003/001611 WO2003102380A1 (fr) 2002-05-30 2003-05-28 Maitrise de la zone de fuite sous plate-forme d'aube

Publications (2)

Publication Number Publication Date
EP1507960A1 EP1507960A1 (de) 2005-02-23
EP1507960B1 true EP1507960B1 (de) 2017-03-08

Family

ID=29558830

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03756014.1A Expired - Lifetime EP1507960B1 (de) 2002-05-30 2003-05-28 Beschaufelte Rotorscheibe einer Turbomaschine

Country Status (9)

Country Link
US (1) US7214034B2 (de)
EP (1) EP1507960B1 (de)
JP (1) JP2005528550A (de)
AU (1) AU2003249424A1 (de)
CA (1) CA2487471C (de)
FR (1) FR2840352B1 (de)
RU (1) RU2313671C2 (de)
UA (1) UA81764C2 (de)
WO (1) WO2003102380A1 (de)

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2874402B1 (fr) * 2004-08-23 2006-09-29 Snecma Moteurs Sa Aube de rotor d'un compresseur ou d'une turbine a gaz
GB0804260D0 (en) * 2008-03-07 2008-04-16 Rolls Royce Plc Annulus filler
US8070448B2 (en) * 2008-10-30 2011-12-06 Honeywell International Inc. Spacers and turbines
PL2406464T3 (pl) * 2009-03-09 2015-11-30 Ge Avio Srl Wirnik do maszyn wirnikowych
GB201016597D0 (en) * 2010-10-04 2010-11-17 Rolls Royce Plc Turbine disc cooling arrangement
US9133855B2 (en) 2010-11-15 2015-09-15 Mtu Aero Engines Gmbh Rotor for a turbo machine
ES2710516T3 (es) * 2010-11-17 2019-04-25 MTU Aero Engines AG Rotor para una turbomáquina, turbomáquina correspondiente y procedimiento de fabricación, reparación o revisión
FR2972482B1 (fr) * 2011-03-07 2016-07-29 Snecma Etage de turbine pour turbomachine d'aeronef, presentant une etancheite amelioree entre le flasque aval et les aubes de la turbine, par maintien mecanique
FR2974387B1 (fr) * 2011-04-19 2015-11-20 Snecma Roue de turbine pour une turbomachine
EP2551464A1 (de) * 2011-07-25 2013-01-30 Siemens Aktiengesellschaft Schaufelanordnung mit Abdichtelement aus Metallschaum
FR2981979B1 (fr) * 2011-10-28 2013-11-29 Snecma Roue de turbine pour une turbomachine
FR2986557B1 (fr) * 2012-02-02 2015-09-25 Snecma Optimisation des points d'appui des echasses d'aubes mobiles dans un procede d'usinage de ces aubes
US10247023B2 (en) * 2012-09-28 2019-04-02 United Technologies Corporation Seal damper with improved retention
US20140271205A1 (en) * 2013-03-12 2014-09-18 Solar Turbines Incorporated Turbine blade pin seal
WO2014160641A1 (en) * 2013-03-25 2014-10-02 United Technologies Corporation Rotor blade with l-shaped feather seal
FR3006364B1 (fr) * 2013-05-30 2018-07-13 Safran Aircraft Engines Roue de turbomachine, notamment pour turbine basse pression
EP2881544A1 (de) 2013-12-09 2015-06-10 Siemens Aktiengesellschaft Schaufelprofil für eine Gasturbine und zugehörige Anordnung
FR3027950B1 (fr) * 2014-11-04 2019-10-18 Safran Aircraft Engines Roue de turbine pour une turbomachine
FR3027949B1 (fr) * 2014-11-04 2019-07-26 Safran Aircraft Engines Roue de turbine pour une turbomachine
US10030523B2 (en) * 2015-02-13 2018-07-24 United Technologies Corporation Article having cooling passage with undulating profile
US9822644B2 (en) 2015-02-27 2017-11-21 Pratt & Whitney Canada Corp. Rotor blade vibration damper
EP3438410B1 (de) * 2017-08-01 2021-09-29 General Electric Company Dichtungssystem für eine rotationsmaschine
FR3090030B1 (fr) 2018-12-12 2020-11-20 Safran Aircraft Engines Dispositif de maintien pour le démontage d’une roue à aubes de turbomachine et procédé l’utilisant
FR3092863B1 (fr) 2019-02-15 2021-01-22 Safran Aircraft Engines Roue de turbine pour turbomachine d’aéronef comprenant des organes d’étanchéité de cavités inter-aubes
US11365642B2 (en) * 2020-04-09 2022-06-21 Raytheon Technologies Corporation Vane support system with seal
US11773731B2 (en) * 2022-01-04 2023-10-03 Rtx Corporation Bathtub damper seal arrangement for gas turbine engine
FR3141720A1 (fr) 2022-11-04 2024-05-10 Safran Aircraft Engines organe d’étanchéité pour une aube mobile

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US2999631A (en) * 1958-09-05 1961-09-12 Gen Electric Dual airfoil
FR2503247B1 (fr) * 1981-04-07 1985-06-14 Snecma Perfectionnements aux etages de turbine a gaz de turboreacteurs munis de moyens de refroidissement par air du disque de la roue de la turbine
US4505642A (en) * 1983-10-24 1985-03-19 United Technologies Corporation Rotor blade interplatform seal
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5228835A (en) * 1992-11-24 1993-07-20 United Technologies Corporation Gas turbine blade seal
US5460489A (en) * 1994-04-12 1995-10-24 United Technologies Corporation Turbine blade damper and seal
FR2722240B1 (fr) * 1994-07-06 1996-08-14 Snecma Joint metallique a levre et turbomachine equipee de ce joint
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal

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Also Published As

Publication number Publication date
RU2313671C2 (ru) 2007-12-27
UA81764C2 (uk) 2008-02-11
FR2840352B1 (fr) 2005-12-16
CA2487471A1 (fr) 2003-12-11
EP1507960A1 (de) 2005-02-23
RU2004138597A (ru) 2005-08-10
CA2487471C (fr) 2011-07-12
JP2005528550A (ja) 2005-09-22
AU2003249424A1 (en) 2003-12-19
WO2003102380A1 (fr) 2003-12-11
US7214034B2 (en) 2007-05-08
US20050175463A1 (en) 2005-08-11
FR2840352A1 (fr) 2003-12-05

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