FR3097269B1 - Integration d’un reservoir d’huile a un reducteur mecanique de turbomachine d’aeronef - Google Patents

Integration d’un reservoir d’huile a un reducteur mecanique de turbomachine d’aeronef Download PDF

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Publication number
FR3097269B1
FR3097269B1 FR1906227A FR1906227A FR3097269B1 FR 3097269 B1 FR3097269 B1 FR 3097269B1 FR 1906227 A FR1906227 A FR 1906227A FR 1906227 A FR1906227 A FR 1906227A FR 3097269 B1 FR3097269 B1 FR 3097269B1
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France
Prior art keywords
integration
oil tank
aircraft turbomachine
shaft
turbomachine
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Active
Application number
FR1906227A
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English (en)
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FR3097269A1 (fr
Inventor
Jean-Baptiste Etienne Bernard Lepretre
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Priority to FR1906227A priority Critical patent/FR3097269B1/fr
Publication of FR3097269A1 publication Critical patent/FR3097269A1/fr
Application granted granted Critical
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • 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
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet 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
    • 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
    • F05D2260/98—Lubrication

Abstract

Turbomachine d’aéronef (1), comportant un arbre (3) d’entraînement d’une soufflante (S) par l’intermédiaire d’un réducteur mécanique (6), ce réducteur (6) comportant un solaire (7) entraîné en rotation par l’arbre d’entraînement (3), une couronne (9) d’entraînement d’un arbre (4) de la soufflante (S), et des satellites (8) engrenés respectivement avec le solaire (7) et la couronne (9) et portés par un porte-satellites (10) qui est fixé à un stator (5) par l’intermédiaire d’un dispositif de liaison à soufflet (14) élastiquement déformable, la turbomachine (1) comportant en outre un circuit de lubrification du réducteur comportant un réservoir d’huile (15), caractérisée en ce qu’une paroi dudit réservoir d’huile est au moins en partie définie par une portion de tôle (15a) dudit dispositif de liaison (14). Figure pour l’abrégé : Figure 3
FR1906227A 2019-06-12 2019-06-12 Integration d’un reservoir d’huile a un reducteur mecanique de turbomachine d’aeronef Active FR3097269B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1906227A FR3097269B1 (fr) 2019-06-12 2019-06-12 Integration d’un reservoir d’huile a un reducteur mecanique de turbomachine d’aeronef

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1906227 2019-06-12
FR1906227A FR3097269B1 (fr) 2019-06-12 2019-06-12 Integration d’un reservoir d’huile a un reducteur mecanique de turbomachine d’aeronef

Publications (2)

Publication Number Publication Date
FR3097269A1 FR3097269A1 (fr) 2020-12-18
FR3097269B1 true FR3097269B1 (fr) 2021-05-14

Family

ID=67957097

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1906227A Active FR3097269B1 (fr) 2019-06-12 2019-06-12 Integration d’un reservoir d’huile a un reducteur mecanique de turbomachine d’aeronef

Country Status (1)

Country Link
FR (1) FR3097269B1 (fr)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6223616B1 (en) 1999-12-22 2001-05-01 United Technologies Corporation Star gear system with lubrication circuit and lubrication method therefor
US8402741B1 (en) * 2012-01-31 2013-03-26 United Technologies Corporation Gas turbine engine shaft bearing configuration
FR3036763B1 (fr) 2015-05-27 2017-05-26 Hispano-Suiza Reducteur a train epicycloidal

Also Published As

Publication number Publication date
FR3097269A1 (fr) 2020-12-18

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