FR3130891B1 - Turbomachine pour aeronef - Google Patents

Turbomachine pour aeronef Download PDF

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Publication number
FR3130891B1
FR3130891B1 FR2113910A FR2113910A FR3130891B1 FR 3130891 B1 FR3130891 B1 FR 3130891B1 FR 2113910 A FR2113910 A FR 2113910A FR 2113910 A FR2113910 A FR 2113910A FR 3130891 B1 FR3130891 B1 FR 3130891B1
Authority
FR
France
Prior art keywords
internal
auxiliary
pipe
external
turbomachine
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
FR2113910A
Other languages
English (en)
Other versions
FR3130891A1 (fr
Inventor
Eddy Stéphane Joël Fontanel
Sébastien Gameiro
Sébastien Oriol
Nicolas Stoliaroff-Pepin
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 FR2113910A priority Critical patent/FR3130891B1/fr
Publication of FR3130891A1 publication Critical patent/FR3130891A1/fr
Application granted granted Critical
Publication of FR3130891B1 publication Critical patent/FR3130891B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • 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
    • F01D25/18—Lubricating arrangements
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • 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
    • F01D25/34—Turning or inching gear
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • 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
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/53—Kinematic linkage, i.e. transmission of position using gears
    • 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
    • F05D2260/98—Lubrication

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Details Of Gearings (AREA)

Abstract

L’invention concerne une turbomachine (1) comprenant une enceinte de lubrification (17) dans laquelle est agencée un réducteur de vitesse (12), l’enceinte de lubrification (17) étant délimitée radialement par une virole interne (19), une virole externe (18) agencée de manière coaxiale autour de la virole interne (19), un bras (20) tubulaire s’étendant radialement entre les viroles interne (19) et externe (18), le bras (20) étant agencé à 6h, une canalisation (21) s’étendant à l’extérieur de la virole externe (18) et en communication fluidique avec la cavité interne (200), un circuit principal (24) et un circuit auxiliaire (25), la canalisation (21) formant un réservoir auxiliaire d’huile relié au circuit auxiliaire (25), et un conduit de récupération (22) relié au circuit principal (24) et configuré pour récupérer de l’huile du réservoir auxiliaire, le conduit de récupération (22) étant agencé dans le passage interne (212) de la canalisation (21). Figure d’abrégé : Figure 6
FR2113910A 2021-12-17 2021-12-17 Turbomachine pour aeronef Active FR3130891B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2113910A FR3130891B1 (fr) 2021-12-17 2021-12-17 Turbomachine pour aeronef

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2113910 2021-12-17
FR2113910A FR3130891B1 (fr) 2021-12-17 2021-12-17 Turbomachine pour aeronef

Publications (2)

Publication Number Publication Date
FR3130891A1 FR3130891A1 (fr) 2023-06-23
FR3130891B1 true FR3130891B1 (fr) 2023-11-24

Family

ID=80595215

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2113910A Active FR3130891B1 (fr) 2021-12-17 2021-12-17 Turbomachine pour aeronef

Country Status (1)

Country Link
FR (1) FR3130891B1 (fr)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3020658B1 (fr) * 2014-04-30 2020-05-15 Safran Aircraft Engines Capot de recuperation d'huile de lubrification pour un equipement de turbomachine
FR3075875B1 (fr) 2017-12-22 2019-11-15 Safran Aircraft Engines Circuit d'huile pour turbomachine a boucle d'huile auxiliaire
FR3082553B1 (fr) * 2018-06-18 2020-09-25 Safran Aircraft Engines Ensemble pour turbomachine d'aeronef comportant un systeme ameliore de lubrification d'un reducteur d'entrainement de soufflante en cas d'autorotation de la soufflante
FR3108951B1 (fr) 2020-04-03 2022-07-15 Safran Aircraft Engines Lubrification de reducteur par barbotage

Also Published As

Publication number Publication date
FR3130891A1 (fr) 2023-06-23

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