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FR3121951B1 - Systeme de renforcement pour un carter de soufflante en materiau composite, carter de soufflante et turbomachine correspondants - Google Patents

Systeme de renforcement pour un carter de soufflante en materiau composite, carter de soufflante et turbomachine correspondants Download PDF

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Publication number
FR3121951B1
FR3121951B1 FR2103894A FR2103894A FR3121951B1 FR 3121951 B1 FR3121951 B1 FR 3121951B1 FR 2103894 A FR2103894 A FR 2103894A FR 2103894 A FR2103894 A FR 2103894A FR 3121951 B1 FR3121951 B1 FR 3121951B1
Authority
FR
France
Prior art keywords
fan casing
reinforcement system
turbomachine
longitudinal axis
extending
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
FR2103894A
Other languages
English (en)
Other versions
FR3121951A1 (fr
Inventor
Vincent Pascal Fiore
Clémentine Arnold
Clément Bourolleau
Serge Domingues
Thomas Dupays
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 FR2103894A priority Critical patent/FR3121951B1/fr
Publication of FR3121951A1 publication Critical patent/FR3121951A1/fr
Application granted granted Critical
Publication of FR3121951B1 publication Critical patent/FR3121951B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/12—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to temperature
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6034—Orientation of fibres, weaving, ply angle

Landscapes

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

Abstract

L’invention concerne un système de renforcement (22) destiné à équiper un carter de soufflante (8) pour une turbomachine, le carter de soufflante (8), réalisé dans un matériau composite avec un renfort fibreux et une matrice, comprenant une paroi (20) généralement cylindrique d’axe longitudinal X et au moins une bride de fixation (21a, 21b), annulaire, s’étendant radialement en formant une zone de jonction (17). Selon l’invention, le système de renforcement comprend au moins une embase (23) s’étendant au moins en partie suivant une direction circonférentielle autour de l’axe longitudinal X, l’embase présentant une première surface de contact (24a) de forme complémentaire avec une surface radiale (25) de la bride de fixation (21a, 21b) et un côté (26a) destiné à épouser la zone de jonction (17), et au moins un organe de renfort (30) qui comporte une semelle (31) s’étendant depuis l’embase suivant l’axe longitudinal, la semelle présentant une deuxième surface de contact (32) de forme complémentaire avec une surface radialement externe (27) de la paroi cylindrique. Figure pour l’abrégé : Figure  4
FR2103894A 2021-04-15 2021-04-15 Systeme de renforcement pour un carter de soufflante en materiau composite, carter de soufflante et turbomachine correspondants Active FR3121951B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2103894A FR3121951B1 (fr) 2021-04-15 2021-04-15 Systeme de renforcement pour un carter de soufflante en materiau composite, carter de soufflante et turbomachine correspondants

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2103894 2021-04-15
FR2103894A FR3121951B1 (fr) 2021-04-15 2021-04-15 Systeme de renforcement pour un carter de soufflante en materiau composite, carter de soufflante et turbomachine correspondants

Publications (2)

Publication Number Publication Date
FR3121951A1 FR3121951A1 (fr) 2022-10-21
FR3121951B1 true FR3121951B1 (fr) 2023-09-29

Family

ID=76283955

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2103894A Active FR3121951B1 (fr) 2021-04-15 2021-04-15 Systeme de renforcement pour un carter de soufflante en materiau composite, carter de soufflante et turbomachine correspondants

Country Status (1)

Country Link
FR (1) FR3121951B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3149041B1 (fr) * 2023-05-26 2025-09-05 Safran Carter intermediaire pour une turbomachine d’aeronef et procede de farication associe

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2936223B1 (fr) * 2008-09-23 2010-09-17 Airbus France Dispositif de liaison entre une entree d'air et une motorisation d'une nacelle d'aeronef
US9140135B2 (en) * 2010-09-28 2015-09-22 United Technologies Corporation Metallic radius block for composite flange
FR2978734B1 (fr) * 2011-08-05 2015-01-02 Airbus Operations Sas Dispositif de liaison plus particulierement adapte pour assurer la liaison entre une entree d'air et une motorisation d'une nacelle d'aeronef
CN104105868B (zh) * 2012-02-16 2017-05-03 联合工艺公司 复合风扇容纳箱组件
US10221718B2 (en) * 2013-09-09 2019-03-05 United Technologies Corporation Fan cases and manufacture methods

Also Published As

Publication number Publication date
FR3121951A1 (fr) 2022-10-21

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