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FR3099208B1 - FUEL SYSTEM FOR AN AIRCRAFT TURBOMACHINE - Google Patents

FUEL SYSTEM FOR AN AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3099208B1
FR3099208B1 FR1908560A FR1908560A FR3099208B1 FR 3099208 B1 FR3099208 B1 FR 3099208B1 FR 1908560 A FR1908560 A FR 1908560A FR 1908560 A FR1908560 A FR 1908560A FR 3099208 B1 FR3099208 B1 FR 3099208B1
Authority
FR
France
Prior art keywords
driven
aircraft turbomachine
fuel system
turbomachine
outlet
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
FR1908560A
Other languages
French (fr)
Other versions
FR3099208A1 (en
Inventor
Wergifosse Huguette De
Hervé Eugène Blum
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 FR1908560A priority Critical patent/FR3099208B1/en
Publication of FR3099208A1 publication Critical patent/FR3099208A1/en
Application granted granted Critical
Publication of FR3099208B1 publication Critical patent/FR3099208B1/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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/30—Control of fuel supply characterised by variable fuel pump output
    • 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
    • F02C7/22—Fuel supply systems
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Details Of Reciprocating Pumps (AREA)

Abstract

Circuit (10) de carburant pour une turbomachine d’aéronef, comportant : une pompe centrifuge (24) comportant un rotor configuré pour être entraîné par un arbre de sortie (40) d’une boîte d’engrenages (20), et un module (16) de dosage de carburant comportant une entrée reliée à une sortie de ladite pompe, et une sortie (16b) destinée à être reliée à un équipement de la turbomachine, telle qu’une chambre de combustion (28), caractérisé en ce qu’il comprend en outre : un différentiel mécanique (34) 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 (44), et -- une sortie qui entraîne en rotation ledit rotor. Figure pour l'abrégé : Figure 4Fuel circuit (10) for an aircraft turbomachine, comprising: a centrifugal pump (24) including a rotor configured to be driven by an output shaft (40) of a gearbox (20), and a module (16) for metering fuel comprising an inlet connected to an outlet of said pump, and an outlet (16b) intended to be connected to equipment of the turbomachine, such as a combustion chamber (28), characterized in that 'it further comprises: a mechanical differential (34) with an epicyclic train, 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 (44 ), and - an output which drives said rotor in rotation. Figure for abstract: Figure 4

FR1908560A 2019-07-26 2019-07-26 FUEL SYSTEM FOR AN AIRCRAFT TURBOMACHINE Active FR3099208B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1908560A FR3099208B1 (en) 2019-07-26 2019-07-26 FUEL SYSTEM FOR AN AIRCRAFT TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1908560A FR3099208B1 (en) 2019-07-26 2019-07-26 FUEL SYSTEM FOR AN AIRCRAFT TURBOMACHINE
FR1908560 2019-07-26

Publications (2)

Publication Number Publication Date
FR3099208A1 FR3099208A1 (en) 2021-01-29
FR3099208B1 true FR3099208B1 (en) 2021-07-16

Family

ID=68343102

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1908560A Active FR3099208B1 (en) 2019-07-26 2019-07-26 FUEL SYSTEM FOR AN AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3099208B1 (en)

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2934321B1 (en) * 2008-07-25 2013-09-27 Hispano Suiza Sa CONTROL OF FUEL FLOW DRAINED IN A FUEL SYSTEM OF AN AIRCRAFT PROPELLED BY AN ENGINE.
FR3062421B1 (en) * 2017-01-30 2021-04-16 Safran Aircraft Engines FUEL PUMP DRIVE DEVICE FOR TURBOMACHINE

Also Published As

Publication number Publication date
FR3099208A1 (en) 2021-01-29

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