FR3096731B1 - Ensemble pour turbomachine - Google Patents

Ensemble pour turbomachine Download PDF

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Publication number
FR3096731B1
FR3096731B1 FR1905734A FR1905734A FR3096731B1 FR 3096731 B1 FR3096731 B1 FR 3096731B1 FR 1905734 A FR1905734 A FR 1905734A FR 1905734 A FR1905734 A FR 1905734A FR 3096731 B1 FR3096731 B1 FR 3096731B1
Authority
FR
France
Prior art keywords
rotor
radial thickness
turbomachine assembly
turbomachine
assembly
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.)
Active
Application number
FR1905734A
Other languages
English (en)
Other versions
FR3096731A1 (fr
Inventor
Philippe Gérard Edmond Joly
Romain Nicolas Lagarde
Jean-Marc Claude Perrollaz
Laurent Jablonski
François Jean Comin
Jaeghere Edouard Antoine Dominique Marie De
Charles Jean-Pierre Douguet
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1905734A priority Critical patent/FR3096731B1/fr
Priority to US17/614,667 priority patent/US11808169B2/en
Priority to CN202080045179.6A priority patent/CN114026312B/zh
Priority to PCT/EP2020/064650 priority patent/WO2020239808A1/fr
Priority to EP20728038.9A priority patent/EP3976928B1/fr
Publication of FR3096731A1 publication Critical patent/FR3096731A1/fr
Application granted granted Critical
Publication of FR3096731B1 publication Critical patent/FR3096731B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • 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
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F04D29/324—Blades
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

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)

Abstract

La présente invention concerne un ensemble pour turbomachine comprenant :- un premier rotor,- un deuxième rotor, et- un amortisseur (2) configuré pour amortir un déplacement du premier rotor par rapport au deuxième rotor, l’amortisseur comprenant :○ une première partie (21) venant en appui sur le premier rotor, et présentant une première épaisseur radiale,○ une deuxième partie (22) venant en appui sur le deuxième rotor, et présentant une deuxième épaisseur radiale, et○ une troisième partie (23) reliant la première partie (21) à la deuxième partie (22), et présentant une troisième épaisseur radiale,dans lequel la troisième épaisseur radiale est supérieure à au moins une parmi la première épaisseur radiale et à la deuxième épaisseur radiale. Figure pour l’abrégé : Fig. 3
FR1905734A 2019-05-29 2019-05-29 Ensemble pour turbomachine Active FR3096731B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR1905734A FR3096731B1 (fr) 2019-05-29 2019-05-29 Ensemble pour turbomachine
US17/614,667 US11808169B2 (en) 2019-05-29 2020-05-27 Assembly for a turbomachine
CN202080045179.6A CN114026312B (zh) 2019-05-29 2020-05-27 用于涡轮机的组件
PCT/EP2020/064650 WO2020239808A1 (fr) 2019-05-29 2020-05-27 Ensemble pour turbomachine
EP20728038.9A EP3976928B1 (fr) 2019-05-29 2020-05-27 Ensemble pour turbomachine et turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1905734A FR3096731B1 (fr) 2019-05-29 2019-05-29 Ensemble pour turbomachine
FR1905734 2019-05-29

Publications (2)

Publication Number Publication Date
FR3096731A1 FR3096731A1 (fr) 2020-12-04
FR3096731B1 true FR3096731B1 (fr) 2021-05-07

Family

ID=68072683

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1905734A Active FR3096731B1 (fr) 2019-05-29 2019-05-29 Ensemble pour turbomachine

Country Status (5)

Country Link
US (1) US11808169B2 (fr)
EP (1) EP3976928B1 (fr)
CN (1) CN114026312B (fr)
FR (1) FR3096731B1 (fr)
WO (1) WO2020239808A1 (fr)

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2517779B1 (fr) * 1981-12-03 1986-06-13 Snecma Dispositif d'amortissement des aubes d'une soufflante de turbomachine
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
US5205713A (en) * 1991-04-29 1993-04-27 General Electric Company Fan blade damper
US5820346A (en) * 1996-12-17 1998-10-13 General Electric Company Blade damper for a turbine engine
US7121801B2 (en) * 2004-02-13 2006-10-17 United Technologies Corporation Cooled rotor blade with vibration damping device
FR2915510B1 (fr) 2007-04-27 2009-11-06 Snecma Sa Amortisseur pour aubes de turbomachines
FR2923557B1 (fr) 2007-11-12 2010-01-22 Snecma Ensemble d'une aube de soufflante et de son amortisseur, amortisseur d'aube de soufflante et methode de calibrage de l'amortisseur
FR2949142B1 (fr) 2009-08-11 2011-10-14 Snecma Cale amortisseuse de vibrations pour aube de soufflante
FR2961553B1 (fr) * 2010-06-18 2012-08-31 Snecma Secteur angulaire de redresseur pour compresseur de turbomachine, redresseur de turbomachine et turbomachine comprenant un tel secteur
FR2961554B1 (fr) * 2010-06-18 2012-07-20 Snecma Secteur angulaire de redresseur pour compresseur de turbomachine, redresseur de turbomachine et turbomachine comprenant un tel secteur
US9151170B2 (en) * 2011-06-28 2015-10-06 United Technologies Corporation Damper for an integrally bladed rotor
FR3003301B1 (fr) * 2013-03-14 2018-01-05 Safran Helicopter Engines Anneau de turbine pour turbomachine
CA2966126C (fr) * 2014-10-15 2023-02-28 Safran Aircraft Engines Ensemble rotatif pour turbomachine comprenant une virole de rotor auto-portee
GB201506196D0 (en) * 2015-04-13 2015-05-27 Rolls Royce Plc Rotor damper
CN204941612U (zh) * 2015-09-16 2016-01-06 中国航空工业集团公司沈阳发动机设计研究所 一种可压缩阻尼块

Also Published As

Publication number Publication date
US20220228494A1 (en) 2022-07-21
WO2020239808A1 (fr) 2020-12-03
CN114026312B (zh) 2024-03-29
FR3096731A1 (fr) 2020-12-04
US11808169B2 (en) 2023-11-07
CN114026312A (zh) 2022-02-08
EP3976928B1 (fr) 2023-08-23
EP3976928A1 (fr) 2022-04-06

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