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FR3099203B1 - AIRCRAFT TURBOMACHINE LUBRICATION CIRCUIT - Google Patents

AIRCRAFT TURBOMACHINE LUBRICATION CIRCUIT Download PDF

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Publication number
FR3099203B1
FR3099203B1 FR1908563A FR1908563A FR3099203B1 FR 3099203 B1 FR3099203 B1 FR 3099203B1 FR 1908563 A FR1908563 A FR 1908563A FR 1908563 A FR1908563 A FR 1908563A FR 3099203 B1 FR3099203 B1 FR 3099203B1
Authority
FR
France
Prior art keywords
lubrication circuit
aircraft turbomachine
driven
rotation
output shaft
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
FR1908563A
Other languages
French (fr)
Other versions
FR3099203A1 (en
Inventor
Wergifosse Huguette De
Wergifosse Eric De
Loïc Pora
Blois Nicolas Bertrand Georges De
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 FR1908563A priority Critical patent/FR3099203B1/en
Publication of FR3099203A1 publication Critical patent/FR3099203A1/en
Application granted granted Critical
Publication of FR3099203B1 publication Critical patent/FR3099203B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • General Details Of Gearings (AREA)

Abstract

Circuit (10) de lubrification d’une turbomachine d’aéronef, comportant : un groupe de lubrification (12) équipé d’au moins une pompe d’alimentation (14) comportant un rotor configuré pour être entraîné par un arbre de sortie (26) d’une boîte d’engrenages (27), au moins un réservoir d’huile (18) comportant une sortie d’huile (18a) reliée à ladite au moins une pompe, caractérisé en ce qu’il comprend en outre : un différentiel mécanique (22) à train épicycloïdal, ce différentiel comportant : -- une première entrée configurée pour être entraînée par ledit arbre de sortie, -- une seconde entrée entraînée en rotation par un premier moteur électrique (30), et -- une sortie qui entraîne en rotation ledit rotor. Figure pour l'abrégé : Figure 2Lubrication circuit (10) of an aircraft turbomachine, comprising: a lubrication unit (12) equipped with at least one feed pump (14) comprising a rotor configured to be driven by an output shaft (26 ) of a gearbox (27), at least one oil reservoir (18) comprising an oil outlet (18a) connected to said at least one pump, characterized in that it further comprises: a mechanical differential (22) with planetary gear, this differential comprising: - a first input configured to be driven by said output shaft, - a second input driven in rotation by a first electric motor (30), and - an output which drives said rotor in rotation. Figure for abstract: Figure 2

FR1908563A 2019-07-26 2019-07-26 AIRCRAFT TURBOMACHINE LUBRICATION CIRCUIT Active FR3099203B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1908563A FR3099203B1 (en) 2019-07-26 2019-07-26 AIRCRAFT TURBOMACHINE LUBRICATION CIRCUIT

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1908563A FR3099203B1 (en) 2019-07-26 2019-07-26 AIRCRAFT TURBOMACHINE LUBRICATION CIRCUIT
FR1908563 2019-07-26

Publications (2)

Publication Number Publication Date
FR3099203A1 FR3099203A1 (en) 2021-01-29
FR3099203B1 true FR3099203B1 (en) 2021-07-16

Family

ID=68581967

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1908563A Active FR3099203B1 (en) 2019-07-26 2019-07-26 AIRCRAFT TURBOMACHINE LUBRICATION CIRCUIT

Country Status (1)

Country Link
FR (1) FR3099203B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113639029B (en) * 2021-08-16 2023-04-25 上海尚实航空发动机股份有限公司 Vortex oar engine reduction gearbox unit body

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2892456B1 (en) * 2005-10-21 2008-01-04 Hispano Suiza Sa DEVICE FOR DRIVING ACCESSORY MACHINES OF A GAS TURBINE ENGINE
GB0805177D0 (en) * 2008-03-20 2008-04-30 Rolls Royce Plc A gas turbine engine arrangement
FR3028887B1 (en) * 2014-11-25 2019-09-27 Safran Aircraft Engines METHOD AND LUBRICATION CIRCUIT FOR TURBOMACHINE USING ELECTRICAL MEANS
FR3062421B1 (en) * 2017-01-30 2021-04-16 Safran Aircraft Engines FUEL PUMP DRIVE DEVICE FOR TURBOMACHINE
US20180283281A1 (en) * 2017-03-31 2018-10-04 Hamilton Sundstrand Corporation Accessory gearboxes

Also Published As

Publication number Publication date
FR3099203A1 (en) 2021-01-29

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