FR3043728B1 - PROPELLANT ASSEMBLY COMPRISING A MAIN MOTOR AND AN AUXILIARY MOTOR - Google Patents

PROPELLANT ASSEMBLY COMPRISING A MAIN MOTOR AND AN AUXILIARY MOTOR Download PDF

Info

Publication number
FR3043728B1
FR3043728B1 FR1561011A FR1561011A FR3043728B1 FR 3043728 B1 FR3043728 B1 FR 3043728B1 FR 1561011 A FR1561011 A FR 1561011A FR 1561011 A FR1561011 A FR 1561011A FR 3043728 B1 FR3043728 B1 FR 3043728B1
Authority
FR
France
Prior art keywords
thrust
main
take
motor
auxiliary
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
FR1561011A
Other languages
French (fr)
Other versions
FR3043728A1 (en
Inventor
Pascal Charles Edouard COAT
Jean-Francois Edouard Bersot
Stephane ORCEL
Nicolas Jerome Jean Tantot
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
SNECMA 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, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1561011A priority Critical patent/FR3043728B1/en
Priority to PCT/FR2016/052979 priority patent/WO2017085406A1/en
Priority to US15/776,433 priority patent/US20180327109A1/en
Publication of FR3043728A1 publication Critical patent/FR3043728A1/en
Application granted granted Critical
Publication of FR3043728B1 publication Critical patent/FR3043728B1/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
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/12—Plants including a gas turbine driving a compressor or a ducted fan characterised by having more than one gas turbine
    • 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
    • F01D13/00—Combinations of two or more machines or engines
    • 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
    • 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
    • F05D2260/85—Starting
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un ensemble propulsif (2) configuré pour fournir une poussée de décollage et une poussée de sommet de montée a et comprenant : - un moteur principal (3), configuré pour fournir une poussée principale au cours du régime de décollage et du régime de sommet en montée présentant un rapport (QTCHP) entre une température en sortie du compresseur haute pression (34) en condition de fonctionnement de sommet de montée (TCHP(ToC)) et une température en sortie du compresseur haute pression (34) en condition de fonctionnement de décollage (TCHP(Tkoff)), est compris entre 0.90 et 1.10, par exemple entre 0.95 et 1.05, et - un moteur auxiliaire (4), distinct du moteur principal (3) et configuré pour fournir une poussée auxiliaire afin de compléter la poussée principale du moteur principal (3) pendant au moins le régime de décollage.The invention relates to a propulsion unit (2) configured to provide take-off thrust and summit climb thrust a and comprising: - a main engine (3), configured to provide main thrust during take-off and top-up speed with a ratio (QTCHP) between a temperature at the outlet of the high pressure compressor (34) under the top-up operating condition (TCHP (ToC)) and a temperature at the outlet of the high pressure compressor (34) take-off operating condition (TCHP (Tkoff)), is between 0.90 and 1.10, for example between 0.95 and 1.05, and - an auxiliary engine (4), distinct from the main engine (3) and configured to provide an auxiliary thrust in order to complete the main thrust of the main engine (3) during at least the take-off speed.

FR1561011A 2015-11-16 2015-11-16 PROPELLANT ASSEMBLY COMPRISING A MAIN MOTOR AND AN AUXILIARY MOTOR Active FR3043728B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR1561011A FR3043728B1 (en) 2015-11-16 2015-11-16 PROPELLANT ASSEMBLY COMPRISING A MAIN MOTOR AND AN AUXILIARY MOTOR
PCT/FR2016/052979 WO2017085406A1 (en) 2015-11-16 2016-11-16 Propulsion unit comprising a main engine and an auxiliary engine
US15/776,433 US20180327109A1 (en) 2015-11-16 2016-11-16 Propulsion unit comprising a main engine and an auxiliary engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1561011A FR3043728B1 (en) 2015-11-16 2015-11-16 PROPELLANT ASSEMBLY COMPRISING A MAIN MOTOR AND AN AUXILIARY MOTOR
FR1561011 2015-11-16

Publications (2)

Publication Number Publication Date
FR3043728A1 FR3043728A1 (en) 2017-05-19
FR3043728B1 true FR3043728B1 (en) 2020-05-01

Family

ID=55182377

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1561011A Active FR3043728B1 (en) 2015-11-16 2015-11-16 PROPELLANT ASSEMBLY COMPRISING A MAIN MOTOR AND AN AUXILIARY MOTOR

Country Status (1)

Country Link
FR (1) FR3043728B1 (en)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB924078A (en) * 1961-12-22 1963-04-24 Rolls Royce Aircraft
US6247668B1 (en) * 1999-07-15 2001-06-19 The Boeing Company Auxiliary power and thrust unit
FR2928135B1 (en) * 2008-02-29 2010-09-03 Airbus France BACK PLANE PROPULSION SYSTEM WITH SEVERABLE SIDE AIR INTAKE AND PLANE HAVING SUCH A SYSTEM.

Also Published As

Publication number Publication date
FR3043728A1 (en) 2017-05-19

Similar Documents

Publication Publication Date Title
EP1933077B1 (en) Method and system for lubricating a turbomachine
FR3077804B1 (en) HYBRID PROPULSION FOR AN AIRCRAFT
FR3019224B1 (en) METHOD FOR ASSISTING A MULTI-ENGINE HELICOPTER SLEEPING TURBOMOTEUR AND ARCHITECTURE OF A PROPELLANT HELICOPTER SYSTEM COMPRISING AT LEAST ONE TURBOMOTEUR WHICH CAN BE ON SLEEP
FR3039227B1 (en) AIRCRAFT COMPRISING A CARENE REAR PROPELLER WITH MOBILE SHUTTERS INPUT STATOR
US8002864B2 (en) De-oiler system for an aircraft engine
FR3066552B1 (en) ASSEMBLY ON A TURBOMACHINE SHAFT OF A MONOBLOC BLADE DISC AND A LOW PRESSURE COMPRESSOR ROTOR WITH AT LEAST TWO STAGES OF MOBILE BLADES
WO2016185336A1 (en) Scroll compressor
FR3083570B1 (en) MONOBLOC CENTRIFUGAL DEGAZER
EP2951092B1 (en) Aircraft with a structure for supplying air to an auxiliary power unit
EP0860593A1 (en) Compression system for a turbomachine
FR3062422B1 (en) TURBOMACHINE FUEL SUPPLY SYSTEM
BR112016005119A2 (en) system and emergency start method of an aircraft turbomachine
GB1319348A (en) Dump bleed system in the compressor of a gas turbine engine
FR3082233B1 (en) TURBINE SET
FR3043728B1 (en) PROPELLANT ASSEMBLY COMPRISING A MAIN MOTOR AND AN AUXILIARY MOTOR
US10260615B2 (en) Vented gear spline lubrication
FR3062424B1 (en) DRIVE SYSTEM FOR A FUEL PUMP OF A TURBOMACHINE
EP2458158B1 (en) Lubrication system for a turbomachine
FR3043729B1 (en) PROPELLANT ASSEMBLY COMPRISING A MAIN MOTOR AND AN AUXILIARY MOTOR
FR3048233B1 (en) AIRCRAFT WITH DYNAMIC AIR INTAKE AND STATIC AIR INPUT FOR FEEDING A MOTOR IN AIR
RU2558719C1 (en) Driving centrifugal breather with axial-flow impeller
FR3090035B1 (en) DEVICE FOR DEOILING AND SEALING A TURBOMACHINE LUBRICATION ENCLOSURE
FR3086348B1 (en) REDUCER TURBOREACTOR
FR3021067B1 (en) CIRCUIT FOR CIRCULATING AIR THROUGH A BEARING ENCLOSURE
FR3022951B1 (en) TWO-STAGE PUMP, ESPECIALLY PROVIDED AS A MAIN PUMP FOR SUPPLYING AN AIRCRAFT ENGINE WITH FUEL

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20170519

PLFP Fee payment

Year of fee payment: 3

CD Change of name or company name

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20180809

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6

PLFP Fee payment

Year of fee payment: 7

PLFP Fee payment

Year of fee payment: 8

PLFP Fee payment

Year of fee payment: 9