FR3116082B1 - Turbofan engine provided with air communication means - Google Patents

Turbofan engine provided with air communication means Download PDF

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Publication number
FR3116082B1
FR3116082B1 FR2011488A FR2011488A FR3116082B1 FR 3116082 B1 FR3116082 B1 FR 3116082B1 FR 2011488 A FR2011488 A FR 2011488A FR 2011488 A FR2011488 A FR 2011488A FR 3116082 B1 FR3116082 B1 FR 3116082B1
Authority
FR
France
Prior art keywords
central part
duct
fan compartment
communication means
air communication
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
FR2011488A
Other languages
French (fr)
Other versions
FR3116082A1 (en
Inventor
Bruno Albert Beutin
Soufien Akachkachy
Joseph Taglialavore
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 FR2011488A priority Critical patent/FR3116082B1/en
Publication of FR3116082A1 publication Critical patent/FR3116082A1/en
Application granted granted Critical
Publication of FR3116082B1 publication Critical patent/FR3116082B1/en
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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/047—Heating to prevent icing
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • 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
    • F02C7/12—Cooling of plants
    • 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
    • F02C7/232—Fuel valves; Draining valves or systems
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/602—Drainage
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/608—Aeration, ventilation, dehumidification or moisture removal of closed spaces
    • 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

Abstract

Le turboréacteur est à double flux et comprend :- une partie centrale (13) comprenant une turbine et définissant une veine principale,- un compartiment de soufflante (16), situé à l’extérieur d’une veine secondaire du turboréacteur,- un conduit (24) s'étendant depuis l'intérieur de la partie centrale (13) jusqu’au compartiment de soufflante (16),- des premiers moyens (30, 32) aptes à mettre le conduit (24) en communication avec la partie centrale (13) et le compartiment de soufflante (16) de sorte que le conduit achemine de l'air passant de l'intérieur de la partie centrale à travers la veine secondaire jusqu'au compartiment de soufflante, et- des deuxièmes moyens (35, 40) aptes à mettre le conduit (24) en communication avec le compartiment de soufflante (16) et la partie centrale de sorte que le conduit achemine de l'air passant du compartiment de soufflante à travers la veine secondaire jusqu'à l'intérieur de la partie centrale. Figure de l’abrégé : Fig. 2The turbojet is dual-flow and comprises:- a central part (13) comprising a turbine and defining a main stream,- a fan compartment (16), located outside a secondary stream of the turbojet,- a duct (24) extending from the inside of the central part (13) as far as the fan compartment (16), - first means (30, 32) able to place the duct (24) in communication with the central part (13) and the fan compartment (16) so that the duct conveys air passing from the interior of the central part through the secondary stream to the fan compartment, and- from the second means (35, 40) capable of placing the duct (24) in communication with the fan compartment (16) and the central part so that the duct conveys air passing from the fan compartment through the secondary stream to the interior of the central part. Abstract Figure: Fig. 2

FR2011488A 2020-11-09 2020-11-09 Turbofan engine provided with air communication means Active FR3116082B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2011488A FR3116082B1 (en) 2020-11-09 2020-11-09 Turbofan engine provided with air communication means

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2011488A FR3116082B1 (en) 2020-11-09 2020-11-09 Turbofan engine provided with air communication means
FR2011488 2020-11-09

Publications (2)

Publication Number Publication Date
FR3116082A1 FR3116082A1 (en) 2022-05-13
FR3116082B1 true FR3116082B1 (en) 2022-09-30

Family

ID=74668956

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2011488A Active FR3116082B1 (en) 2020-11-09 2020-11-09 Turbofan engine provided with air communication means

Country Status (1)

Country Link
FR (1) FR3116082B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5136837A (en) * 1990-03-06 1992-08-11 General Electric Company Aircraft engine starter integrated boundary bleed system
FR2871519B1 (en) 2004-06-10 2006-08-04 Snecma Moteurs Sa METHOD AND SYSTEM FOR PROTECTING GAS TURBINE FUEL INJECTORS
US8387950B2 (en) * 2011-04-06 2013-03-05 General Electric Company Flow device and method and system using the flow device
FR3039208B1 (en) * 2015-07-24 2018-01-19 Safran Aircraft Engines DEFROSTING AN AIR INLET LIP AND COOLING A TURBINE HOUSING OF A PROPELLANT AIRCRAFT ASSEMBLY

Also Published As

Publication number Publication date
FR3116082A1 (en) 2022-05-13

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