FR3106610B1 - Carter de turbomachine d’aeronef et son procede de fabrication - Google Patents

Carter de turbomachine d’aeronef et son procede de fabrication Download PDF

Info

Publication number
FR3106610B1
FR3106610B1 FR2000871A FR2000871A FR3106610B1 FR 3106610 B1 FR3106610 B1 FR 3106610B1 FR 2000871 A FR2000871 A FR 2000871A FR 2000871 A FR2000871 A FR 2000871A FR 3106610 B1 FR3106610 B1 FR 3106610B1
Authority
FR
France
Prior art keywords
casing
crankcase
manufacturing
aircraft turbomachine
axis
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
FR2000871A
Other languages
English (en)
Other versions
FR3106610A1 (fr
Inventor
Ambroise Nicolas Marie Malfroy
Nicolas François Paul Broussais-Colella
Matthieu Patrick Jean Roger Perlin
Adrienne Retiveau-Leca
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 FR2000871A priority Critical patent/FR3106610B1/fr
Publication of FR3106610A1 publication Critical patent/FR3106610A1/fr
Application granted granted Critical
Publication of FR3106610B1 publication Critical patent/FR3106610B1/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
    • 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
    • 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
    • F01D11/125—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 with a reinforcing structure
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

Carter (3) de turbomachine d’aéronef, ce carter comportant : - une enveloppe annulaire (9) s’étendant autour d’un axe A et réalisée dans un matériau composite comportant des fibres tissées et noyées dans une résine, - une couche annulaire (4) en matériau abradable s’étendant à l’intérieur de l’enveloppe, autour de l’axe A, et obtenue par étalement et polymérisation d’une pâte, et - des panneaux supports (10) s’étendant autour de l’axe A et intercalés entre l’enveloppe et la couche abradable. Figure pour l'abrégé : Figure 10
FR2000871A 2020-01-29 2020-01-29 Carter de turbomachine d’aeronef et son procede de fabrication Active FR3106610B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2000871A FR3106610B1 (fr) 2020-01-29 2020-01-29 Carter de turbomachine d’aeronef et son procede de fabrication

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2000871A FR3106610B1 (fr) 2020-01-29 2020-01-29 Carter de turbomachine d’aeronef et son procede de fabrication
FR2000871 2020-01-29

Publications (2)

Publication Number Publication Date
FR3106610A1 FR3106610A1 (fr) 2021-07-30
FR3106610B1 true FR3106610B1 (fr) 2023-04-14

Family

ID=70154714

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2000871A Active FR3106610B1 (fr) 2020-01-29 2020-01-29 Carter de turbomachine d’aeronef et son procede de fabrication

Country Status (1)

Country Link
FR (1) FR3106610B1 (fr)

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2418957B (en) * 2003-10-22 2006-07-05 Rolls Royce Plc A liner for a gas turbine engine casing
FR2997726B1 (fr) 2012-11-05 2018-03-02 Safran Aircraft Engines Carter de turbomachine
FR2997725B1 (fr) 2012-11-05 2018-03-02 Safran Aircraft Engines Carter de turbomachine
FR3005100B1 (fr) 2013-04-26 2015-05-01 Snecma Carter de turbomachine
FR3007064B1 (fr) * 2013-06-13 2018-06-29 Composite Industrie Secteur de joint annulaire abradable pour turbomachine et procede de fabrication d'une telle piece
FR3048018B1 (fr) * 2016-02-22 2018-03-02 Safran Aircraft Engines Dispositif d'application de materiau abradable sur une surface d'un carter de turbomachine
FR3051828B1 (fr) * 2016-05-24 2018-05-11 Safran Aircraft Engines Procede de fabrication d'un carter a revetement abradable de turbomachine
FR3060438B1 (fr) 2016-12-15 2021-01-29 Safran Aircraft Engines Procede et outillage de mise en forme d'un carter de soufflante
FR3074218B1 (fr) * 2017-11-29 2021-02-12 Safran Aircraft Engines Procede de fabrication d'un revetement annulaire pour un carter d'aubes tournantes d'une turbomachine

Also Published As

Publication number Publication date
FR3106610A1 (fr) 2021-07-30

Similar Documents

Publication Publication Date Title
FR3079445B1 (fr) Procede de fabrication d'une aube en materiau composite a bord d'attaque metallique rapporte pour turbine a gaz
CA1211360A (fr) Dispositif d'attenuation d'energie acoustique et methode de fabrication
EP1157372B1 (fr) Procede de fabrication d'un panneau d'attenuation acoustique a couche resistive a propriete structurale et panneau ainsi obtenu
EP2246179A2 (fr) Matériau composite, pièce composite et leurs procédés de fabrication
GB2570211A (en) A casing of reinforced composite material, and a method of fabricating it
CA2902849C (fr) Moule d'injection pour la fabrication d'une piece de revolution en materiau composite ayant des brides externes, et notamment d'un carter de turbine a gaz
RU2679517C2 (ru) Лента для истираемого материала в компрессоре турбины
AU2015210376B2 (en) Structure including a light-curable adhesive and associated method for assembling and curing same
FR3037854A1 (fr) Procede de fabrication d'un carter de soufflante en materiau composite a panneau abradable integre pour moteur a turbine a gaz et carter ainsi obtenu
FR3106610B1 (fr) Carter de turbomachine d’aeronef et son procede de fabrication
FR3106612B1 (fr) Carter de turbomachine d’aeronef et son procede de fabrication
FR3106611B1 (fr) Carter de turbomachine d’aeronef et son procede de fabrication
FR3095369B1 (fr) Procédé de fabrication d’une structure d’absorption acoustique utilisant au moins une plaque de conformation, structure d’absorption acoustique obtenue à partir dudit procédé et aéronef comprenant ladite structure d’absorption acoustique
FR3089297B1 (fr) Procédé de fabrication d’un corps d’essai
FR3123826B1 (fr) Revêtement abradable à structure nid d’abeilles en matériau composite à matrice céramique en fibres courtes
FR3085126B1 (fr) Procede de fabrication d'une preforme composite pour la fabrication d'un panneau composite a geometrie a double courbure
FR3121953B1 (fr) Procede de fabrication d’une aube composite de turbomachine
US2322582A (en) Laminated glass
FR3099131B1 (fr) Hublot d’avion allégé à faible traînée
EP4401956A1 (fr) Aube en matériau composite comportant un renfort métallique et procédé de fabrication d'une telle aube
FR3102086B1 (fr) Aube en matériau composite comportant un renfort métallique, et procédés de fabrication et de réparation d’une telle aube
CN107310167A (zh) 一种强化碳纤维布复合层的构造方法以及应用该方法的管道止裂器
FR3068277B1 (fr) Materiau composite constitue de fibres tissees pre-impregnees
US11638972B2 (en) Method for manufacturing a porous layer of an acoustic attenuation structure, porous layer of an acoustic attenuation structure thus obtained and acoustic attenuation structure comprising said porous layer
FR3100152B1 (fr) Procede de fabrication d’un carter annulaire pour une turbomachine d’aeronef

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20210730

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5