EP0081416A1 - Dispositif d'amortissement des aubes d'une soufflante de turbomachine - Google Patents

Dispositif d'amortissement des aubes d'une soufflante de turbomachine Download PDF

Info

Publication number
EP0081416A1
EP0081416A1 EP82402165A EP82402165A EP0081416A1 EP 0081416 A1 EP0081416 A1 EP 0081416A1 EP 82402165 A EP82402165 A EP 82402165A EP 82402165 A EP82402165 A EP 82402165A EP 0081416 A1 EP0081416 A1 EP 0081416A1
Authority
EP
European Patent Office
Prior art keywords
blades
disc
wedge
platforms
stilts
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Withdrawn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
EP82402165A
Other languages
German (de)
English (en)
French (fr)
Inventor
Alexandre Forestier
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0081416A1 publication Critical patent/EP0081416A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the present invention relates to a device for damping the blades of a turbomachine fan.
  • a pneumatic damping device is used according to the invention.
  • the shim consists of a bellows-shaped hollow body provided with an axial stop means, said body being inflated after assembly, by so that it occupies the entire space between the platforms of the blades, the stilts of the blades and the teeth of the disc.
  • the pneumatic block eliminates almost all of the air leaks which pass under the platforms.
  • FIGs 1 and 2 there are shown two consecutive blades 1 and the of a fan whose feet 2, 2a are arranged in cells 3, 3a of a disc 4 with the interposition of rigid wedges 5, 5a.
  • a shim 9 inflatable In the space 15 delimited by two half-platforms 6, 6a of the vanes 1, the, the stilts 7, 7a of these vanes and the top of a tooth 8 of the disc 4 comprised between these two vanes, is arranged a shim 9 inflatable.
  • the wedge shown in Figures 3 and 4 consists of an inflatable hollow body having two flat faces, one 10a is supported on the ends of the teeth of the disc and the other 10 on the two half-platforms 6, 6a of the neighboring blades 1, la, these faces being connected together by a folding wall 11 giving the wedge the shape of a bellows.
  • the material used for the inflatable wedge 9 can be made of flexible elastomeric material with significant elongation, preferably reinforced, for example with a canvas.
  • a stop is provided to limit the axial displacement of the wedge.
  • the wedge 9 has two arms 12, 13 at the front, which come to bear on the front face of stilts 7, 7a and stop the wedge axially.
  • a valve 14 making it possible to inflate said wedge. If the disc or the blades have a rear mechanical stop, the axial stop means of the pneumatic block is then constituted by this mechanical stop. In this case, we can remove the arms 12 and 13 (obviously keeping the valve).
  • the shim 9 is introduced from front to back into the space 15 in its flattened shape shown in FIG. 3 then it is inflated to present the appearance of Figure 4; the inflation pressure can, for example, be of the order of 5 bars.
  • the wedge 9 then occupies all the prismatic space 15 located below the platforms 6, 6a of the blades and it pushes said platforms radially upwards; in addition the expansion of the shim in the peripheral direction helps to maintain the blades 1, firmly in place and to dampen vibrations.

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)
EP82402165A 1981-12-03 1982-11-29 Dispositif d'amortissement des aubes d'une soufflante de turbomachine Withdrawn EP0081416A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8122622A FR2517779B1 (fr) 1981-12-03 1981-12-03 Dispositif d'amortissement des aubes d'une soufflante de turbomachine
FR8122622 1981-12-03

Publications (1)

Publication Number Publication Date
EP0081416A1 true EP0081416A1 (fr) 1983-06-15

Family

ID=9264621

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82402165A Withdrawn EP0081416A1 (fr) 1981-12-03 1982-11-29 Dispositif d'amortissement des aubes d'une soufflante de turbomachine

Country Status (4)

Country Link
US (1) US4494909A (enrdf_load_stackoverflow)
EP (1) EP0081416A1 (enrdf_load_stackoverflow)
JP (1) JPS58150100A (enrdf_load_stackoverflow)
FR (1) FR2517779B1 (enrdf_load_stackoverflow)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0280246A1 (en) * 1987-02-24 1988-08-31 Westinghouse Electric Corporation Method of assembly of a blade arrangement for a steam turbine
FR2716502A1 (fr) * 1994-02-23 1995-08-25 Snecma Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires.
WO2011018425A1 (fr) * 2009-08-11 2011-02-17 Snecma Cale amortisseuse de vibrations pour aube de soufflante
WO2014140449A1 (fr) 2013-03-15 2014-09-18 Snecma Soufflante de turbomoteur a flux multiple, et turbomoteur equipe d'une telle soufflante

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
JPS6217306A (ja) * 1985-07-12 1987-01-26 Mitsubishi Heavy Ind Ltd 回転機械翼
FR2585069B1 (fr) * 1985-07-16 1989-06-09 Snecma Dispositif de limitation du debattement angulaire d'aubes montees sur un disque de rotor de turbomachine
US4743164A (en) * 1986-12-29 1988-05-10 United Technologies Corporation Interblade seal for turbomachine rotor
US4936749A (en) * 1988-12-21 1990-06-26 General Electric Company Blade-to-blade vibration damper
US5205713A (en) * 1991-04-29 1993-04-27 General Electric Company Fan blade damper
US5302085A (en) * 1992-02-03 1994-04-12 General Electric Company Turbine blade damper
US5261790A (en) * 1992-02-03 1993-11-16 General Electric Company Retention device for turbine blade damper
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal
KR20020005747A (ko) * 1999-05-14 2002-01-17 칼 하인쯔 호르닝어 터보 엔진의 회전자용 밀봉 시스템
US6575704B1 (en) * 1999-06-07 2003-06-10 Siemens Aktiengesellschaft Turbomachine and sealing element for a rotor thereof
GB9915637D0 (en) 1999-07-06 1999-09-01 Rolls Royce Plc A rotor seal
FR2915510B1 (fr) * 2007-04-27 2009-11-06 Snecma Sa Amortisseur pour aubes de turbomachines
US8210823B2 (en) * 2008-07-08 2012-07-03 General Electric Company Method and apparatus for creating seal slots for turbine components
US8210821B2 (en) * 2008-07-08 2012-07-03 General Electric Company Labyrinth seal for turbine dovetail
US8210820B2 (en) * 2008-07-08 2012-07-03 General Electric Company Gas assisted turbine seal
US8011894B2 (en) * 2008-07-08 2011-09-06 General Electric Company Sealing mechanism with pivot plate and rope seal
US8038405B2 (en) * 2008-07-08 2011-10-18 General Electric Company Spring seal for turbine dovetail
US8215914B2 (en) * 2008-07-08 2012-07-10 General Electric Company Compliant seal for rotor slot
US8419370B2 (en) * 2009-06-25 2013-04-16 Rolls-Royce Corporation Retaining and sealing ring assembly
US8469670B2 (en) * 2009-08-27 2013-06-25 Rolls-Royce Corporation Fan assembly
US8435006B2 (en) * 2009-09-30 2013-05-07 Rolls-Royce Corporation Fan
FR2962481B1 (fr) * 2010-07-12 2012-08-31 Snecma Propulsion Solide Amortisseur de vibrations a bras de levier pour aube d'un rotor de moteur a turbine a gaz
EP2647847B1 (en) 2011-03-09 2017-01-11 IHI Corporation Guide vane assembly and fan
US9920627B2 (en) * 2014-05-22 2018-03-20 United Technologies Corporation Rotor heat shield
EP3073052B1 (en) * 2015-02-17 2018-01-24 Rolls-Royce Corporation Fan assembly
RU2602643C1 (ru) * 2015-06-18 2016-11-20 федеральное государственное бюджетное образовательное учреждение высшего образования "Пермский национальный исследовательский политехнический университет" Рабочее колесо турбомашины с демпфером для лопаток
US10612405B2 (en) 2017-01-13 2020-04-07 United Technologies Corporation Stator outer platform sealing and retainer
FR3096731B1 (fr) * 2019-05-29 2021-05-07 Safran Aircraft Engines Ensemble pour turbomachine
WO2020239803A1 (fr) * 2019-05-29 2020-12-03 Safran Aircraft Engines Ensemble pour turbomachine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3119595A (en) * 1961-02-23 1964-01-28 Gen Electric Bladed rotor and baffle assembly
FR1417600A (fr) * 1963-12-16 1965-11-12 Rolls Royce Perfectionnements aux turbines et aux compresseurs
FR2026212A1 (enrdf_load_stackoverflow) * 1968-12-16 1970-09-18 Rolls Royce
GB1457417A (en) * 1973-06-30 1976-12-01 Dunlop Ltd Vibration damping means
FR2376958A1 (fr) * 1977-01-11 1978-08-04 Rolls Royce Etage mobile de compresseur

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB667979A (en) * 1949-07-28 1952-03-12 Rolls Royce Improvements in or relating to axial flow compressors and turbines
GB750397A (en) * 1951-12-10 1956-06-13 Power Jets Res & Dev Ltd Damped turbine and dynamic compressor blades
GB700898A (en) * 1952-04-30 1953-12-09 George Allen Dean Improvements relating to fans, compressors and the like
US2877980A (en) * 1954-09-28 1959-03-17 Stalker Dev Company Vibration dampers for gas turbine wheels and the like
GB1428365A (en) * 1972-03-15 1976-03-17 Rolls Royce Fluid flow machines
GB1549422A (en) * 1976-10-19 1979-08-08 Rolls Royce Axial flow gas turbine engine compressor
DE2658345A1 (de) * 1976-12-23 1978-06-29 Motoren Turbinen Union Rezirkulationsdichtung fuer stroemungsmaschinen, insbesondere gasturbinenstrahltriebwerke

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3119595A (en) * 1961-02-23 1964-01-28 Gen Electric Bladed rotor and baffle assembly
FR1417600A (fr) * 1963-12-16 1965-11-12 Rolls Royce Perfectionnements aux turbines et aux compresseurs
FR2026212A1 (enrdf_load_stackoverflow) * 1968-12-16 1970-09-18 Rolls Royce
GB1457417A (en) * 1973-06-30 1976-12-01 Dunlop Ltd Vibration damping means
FR2376958A1 (fr) * 1977-01-11 1978-08-04 Rolls Royce Etage mobile de compresseur

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0280246A1 (en) * 1987-02-24 1988-08-31 Westinghouse Electric Corporation Method of assembly of a blade arrangement for a steam turbine
FR2716502A1 (fr) * 1994-02-23 1995-08-25 Snecma Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires.
EP0669451A1 (fr) * 1994-02-23 1995-08-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires
US5520514A (en) * 1994-02-23 1996-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Sealing lining between vanes and intermediate platforms
WO2011018425A1 (fr) * 2009-08-11 2011-02-17 Snecma Cale amortisseuse de vibrations pour aube de soufflante
FR2949142A1 (fr) * 2009-08-11 2011-02-18 Snecma Cale amortisseuse de vibrations pour aube de soufflante
US8911210B2 (en) 2009-08-11 2014-12-16 Snecma Vibration-damping shim for fan blade
WO2014140449A1 (fr) 2013-03-15 2014-09-18 Snecma Soufflante de turbomoteur a flux multiple, et turbomoteur equipe d'une telle soufflante
FR3003294A1 (fr) * 2013-03-15 2014-09-19 Snecma Soufflante de turbomoteur a flux multiple, et turbomoteur equipe d'une telle soufflante
GB2526475A (en) * 2013-03-15 2015-11-25 Snecma Multiflow turbojet engine fan and turbojet engine fitted with such a fan
GB2526475B (en) * 2013-03-15 2018-05-16 Snecma Fan for a multi-flow turboshaft engine, and turboshaft engine equipped with such a fan

Also Published As

Publication number Publication date
JPS58150100A (ja) 1983-09-06
FR2517779B1 (fr) 1986-06-13
FR2517779A1 (fr) 1983-06-10
JPS641680B2 (enrdf_load_stackoverflow) 1989-01-12
US4494909A (en) 1985-01-22

Similar Documents

Publication Publication Date Title
EP0081416A1 (fr) Dispositif d'amortissement des aubes d'une soufflante de turbomachine
EP0132182B1 (fr) Dispositif d'étanchéité d'aubages mobiles de turbomachine
CA2646970C (fr) Panneau de support d'abradable dans une turbomachine
EP2268926B1 (fr) Carter pour roue a aubes mobiles de turbomachine
EP0488874B1 (fr) Rotor de soufflante avec aubes sans plates-formes et sabots reconstituant le profil de veine
EP1950381A1 (fr) Disque de rotor de soufflante de turbomachine
EP1698761A2 (fr) Carter interne de turbomachine équipé d'un bouclier thermique
FR2568308A1 (fr) Aube de rotor
FR2585069A1 (fr) Dispositif de limitation du debattement angulaire d'aubes montees sur un disque de rotor de turbomachine
FR2955608A1 (fr) Amortisseur de vibrations a lamelle et chemises entre talons d'aubes adjacentes en materiau composite d'une roue mobile de turbomachine.
EP1640564A1 (fr) Dispositif de limitation de survitesse de turbine
EP1262633A1 (fr) Aube de turbine avec léchette d'étanchéité
EP0069620A1 (fr) Dispositif d'amortissement d'aubes de turbomachines, notamment de soufflantes
EP0797005A1 (fr) Dispositif de retenue du pied des aubes d'une soufflante
CA2952752A1 (fr) Ensemble rotatif pour turbomachine
CA2994912C (fr) Aube de rotor de turbomachine
FR2927357A1 (fr) Dispositif d'amortissement des vibrations entre deux aubes de roue aubagee de turbomachine
EP3201438B1 (fr) Aube mobile de turbomachine, comprenant un ergot engageant une entaille de blocage d'un disque de rotor
FR2697051A1 (fr) Rotor de turbomachine comprenant un disque dont le pourtour est occupé par des alvéoles obliques qui alternent avec des dents de section transversale variable.
FR2561307A1 (fr) Dispositif de verrouillage d'aubes de soufflantes
FR2874402A1 (fr) Aube de rotor d'un compresseur ou d'une turbine a gaz
FR2507696A1 (fr) Perfectionnements aux moteurs a fluide
EP4396445B1 (fr) Dispositif d'amortissement pour roue mobile de turbomachine d'aéronef, roue mobile pour turbomachine d'aéronef, turbomachine pour aéronef et procédé de fabrication d'un dispositif d'amortissement
WO2021074508A1 (fr) Virole amelioree de roue mobile de turbine contrarotative
EP1707864A1 (fr) Dispositif de contrôle d'écoulement insérable dans une canalisation, à ancrage assisté

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19821208

AK Designated contracting states

Designated state(s): DE FR GB SE

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 19850607

RIN1 Information on inventor provided before grant (corrected)

Inventor name: FORESTIER, ALEXANDRE