FR3135749B1 - Ensemble propulsif pour un aeronef - Google Patents

Ensemble propulsif pour un aeronef Download PDF

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Publication number
FR3135749B1
FR3135749B1 FR2204886A FR2204886A FR3135749B1 FR 3135749 B1 FR3135749 B1 FR 3135749B1 FR 2204886 A FR2204886 A FR 2204886A FR 2204886 A FR2204886 A FR 2204886A FR 3135749 B1 FR3135749 B1 FR 3135749B1
Authority
FR
France
Prior art keywords
fan
aircraft
gas generator
propulsion assembly
fan casing
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
FR2204886A
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English (en)
Other versions
FR3135749A1 (fr
Inventor
Vincent François Georges Millier
Olivier Belmonte
Yves Roland Crochemore
Didier René André Escure
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 FR2204886A priority Critical patent/FR3135749B1/fr
Publication of FR3135749A1 publication Critical patent/FR3135749A1/fr
Application granted granted Critical
Publication of FR3135749B1 publication Critical patent/FR3135749B1/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
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods

Landscapes

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

Abstract

Ensemble propulsif (54) pour un aéronef, cet ensemble propulsif (54) comportant : - un générateur de gaz, - une soufflante (24) située en amont du générateur de gaz, - un carter de soufflante (26) s’étendant autour de la soufflante (24), - une nacelle (58) s’étendant autour du carter de soufflante (26) et d’au moins une partie du générateur de gaz, caractérisé en ce que le carter de soufflante (26) comprend, à une position circonférentielle prédéterminée autour de l’axe (A), une ouverture radiale (46) qui est fermée par un panneau (48) amovible, le panneau (46) un revêtement abradable (30), et l’ouverture (46) étant située au droit de la soufflante (24) et étant configurée pour permettre l’extraction radiale d’une des aubes (32) de la soufflante. Figure pour l'abrégé : Figure 4
FR2204886A 2022-05-20 2022-05-20 Ensemble propulsif pour un aeronef Active FR3135749B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2204886A FR3135749B1 (fr) 2022-05-20 2022-05-20 Ensemble propulsif pour un aeronef

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2204886 2022-05-20
FR2204886A FR3135749B1 (fr) 2022-05-20 2022-05-20 Ensemble propulsif pour un aeronef

Publications (2)

Publication Number Publication Date
FR3135749A1 FR3135749A1 (fr) 2023-11-24
FR3135749B1 true FR3135749B1 (fr) 2024-05-03

Family

ID=83690202

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2204886A Active FR3135749B1 (fr) 2022-05-20 2022-05-20 Ensemble propulsif pour un aeronef

Country Status (1)

Country Link
FR (1) FR3135749B1 (fr)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3008912B1 (fr) * 2013-07-29 2017-12-15 Snecma Carter de turbomachine et procede de fabrication
FR3021295B1 (fr) 2014-05-21 2016-05-13 Snecma Moyeu raidi pour helice non carenee a pales a calage variable de turbomachine.
FR3046409B1 (fr) 2016-01-05 2018-02-09 Safran Aircraft Engines Systeme de commande de l'orientation des pales de soufflante d'une turbomachine a pion de blocage de mise en drapeau
US10934866B2 (en) * 2017-06-20 2021-03-02 Rolls-Royce North American Technologies Inc. Variable pitch change control method
GB201817934D0 (en) * 2018-11-02 2018-12-19 Rolls Royce Plc Fan case
FR3112819B1 (fr) 2020-07-24 2024-02-16 Safran Aircraft Engines Turbomachine d’aeronef comportant des aubes d’helice a calage variable
CN116056976A (zh) 2020-07-24 2023-05-02 赛峰飞机发动机公司 包括可变螺距螺旋桨桨叶的飞行器涡轮发动机
US11873076B2 (en) 2020-07-24 2024-01-16 Safran Aircraft Engines Aircraft turbine engine comprising variable pitch propeller blades

Also Published As

Publication number Publication date
FR3135749A1 (fr) 2023-11-24

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