FR3122668B1 - Procédé de montage d’un élément abradable comprenant une structure alvéolaire dans une gorge annulaire d’un organe de turbomachine - Google Patents

Procédé de montage d’un élément abradable comprenant une structure alvéolaire dans une gorge annulaire d’un organe de turbomachine Download PDF

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Publication number
FR3122668B1
FR3122668B1 FR2104675A FR2104675A FR3122668B1 FR 3122668 B1 FR3122668 B1 FR 3122668B1 FR 2104675 A FR2104675 A FR 2104675A FR 2104675 A FR2104675 A FR 2104675A FR 3122668 B1 FR3122668 B1 FR 3122668B1
Authority
FR
France
Prior art keywords
abradable element
annular
mounting
annular groove
honeycomb structure
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
FR2104675A
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English (en)
Other versions
FR3122668A1 (fr
Inventor
Silva Quentin Alexandre Da
Bastien Gilbert Assouly
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 FR2104675A priority Critical patent/FR3122668B1/fr
Priority to EP22722316.1A priority patent/EP4334572B1/fr
Priority to US18/558,840 priority patent/US12168935B2/en
Priority to CN202280034682.0A priority patent/CN117295877A/zh
Priority to PCT/FR2022/050710 priority patent/WO2022234205A1/fr
Publication of FR3122668A1 publication Critical patent/FR3122668A1/fr
Application granted granted Critical
Publication of FR3122668B1 publication Critical patent/FR3122668B1/fr
Active 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
    • 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
    • F05D2230/80—Repairing, retrofitting or upgrading 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Procédé de montage (100) d’un élément abradable (16) annulaire dans une gorge annulaire d’un organe (21) d’une turbomachine (1), l’élément abradable (16) annulaire s’étendant selon un axe (A3) et comprenant une structure alvéolaire, la gorge débouchant en périphérie radialement interne dudit organe (21), le procédé (100) comportant les étapes consistant à contraindre l’élément abradable (16) de façon à le déformer dans un plan perpendiculaire à l’axe (A3) de l’élément abradable (16) annulaire non déformé, à l’aide d’un dispositif (20) ; positionner axialement l’élément abradable (16) déformé en regard de la gorge annulaire, à l’intérieur de l’organe (21) ; libérer l’élément abradable (16) de façon à ce qu’il s’insère dans la gorge et y retrouve sa forme annulaire. Figure de l’abrégé : Figure 10
FR2104675A 2021-05-04 2021-05-04 Procédé de montage d’un élément abradable comprenant une structure alvéolaire dans une gorge annulaire d’un organe de turbomachine Active FR3122668B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR2104675A FR3122668B1 (fr) 2021-05-04 2021-05-04 Procédé de montage d’un élément abradable comprenant une structure alvéolaire dans une gorge annulaire d’un organe de turbomachine
EP22722316.1A EP4334572B1 (fr) 2021-05-04 2022-04-14 Procédé de montage d'un élément abradable comprenant une structure alvéolaire dans une gorge annulaire d'un organe de turbomachine
US18/558,840 US12168935B2 (en) 2021-05-04 2022-04-14 Method for mounting an abradable element comprising a cellular structure in an annular groove of a turbomachine member
CN202280034682.0A CN117295877A (zh) 2021-05-04 2022-04-14 用于在涡轮机部件的环形凹槽中安装包括蜂窝式结构的可磨耗元件的方法
PCT/FR2022/050710 WO2022234205A1 (fr) 2021-05-04 2022-04-14 Procédé de montage d'un élément abradable comprenant une structure alvéolaire dans une gorge annulaire d'un organe de turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2104675 2021-05-04
FR2104675A FR3122668B1 (fr) 2021-05-04 2021-05-04 Procédé de montage d’un élément abradable comprenant une structure alvéolaire dans une gorge annulaire d’un organe de turbomachine

Publications (2)

Publication Number Publication Date
FR3122668A1 FR3122668A1 (fr) 2022-11-11
FR3122668B1 true FR3122668B1 (fr) 2023-05-26

Family

ID=76601383

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2104675A Active FR3122668B1 (fr) 2021-05-04 2021-05-04 Procédé de montage d’un élément abradable comprenant une structure alvéolaire dans une gorge annulaire d’un organe de turbomachine

Country Status (5)

Country Link
US (1) US12168935B2 (fr)
EP (1) EP4334572B1 (fr)
CN (1) CN117295877A (fr)
FR (1) FR3122668B1 (fr)
WO (1) WO2022234205A1 (fr)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0216952D0 (en) * 2002-07-20 2002-08-28 Rolls Royce Plc Gas turbine engine casing and rotor blade arrangement
DE102009004934B4 (de) * 2009-01-16 2021-08-26 MTU Aero Engines AG Verfahren zur Montage eines integralen Innenrings eines Turboverdichterstators
JP6184173B2 (ja) * 2013-05-29 2017-08-23 三菱日立パワーシステムズ株式会社 ガスタービン
US9273611B2 (en) * 2014-07-22 2016-03-01 Siemens Energy, Inc. Method and apparatus for improved turbine bellyband rotor seal machining, installation and life
US10113447B2 (en) * 2014-12-12 2018-10-30 Rolls-Royce Plc Fan casing arrangement for a gas turbine engine
DE102015202070A1 (de) * 2015-02-05 2016-08-25 MTU Aero Engines AG Gasturbinenbauteil
US11215070B2 (en) * 2019-12-13 2022-01-04 Pratt & Whitney Canada Corp. Dual density abradable panels
FR3116860B1 (fr) * 2020-11-27 2026-01-30 Safran Aircraft Engines Installation et procede pour l’assemblage des distributeurs d’une turbine

Also Published As

Publication number Publication date
CN117295877A (zh) 2023-12-26
FR3122668A1 (fr) 2022-11-11
US12168935B2 (en) 2024-12-17
WO2022234205A1 (fr) 2022-11-10
EP4334572B1 (fr) 2026-03-04
EP4334572A1 (fr) 2024-03-13
US20240240567A1 (en) 2024-07-18

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