FR3091905B1 - turboreacteur double flux comportant un système d’inversion de poussée - Google Patents

turboreacteur double flux comportant un système d’inversion de poussée Download PDF

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Publication number
FR3091905B1
FR3091905B1 FR1900579A FR1900579A FR3091905B1 FR 3091905 B1 FR3091905 B1 FR 3091905B1 FR 1900579 A FR1900579 A FR 1900579A FR 1900579 A FR1900579 A FR 1900579A FR 3091905 B1 FR3091905 B1 FR 3091905B1
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FR
France
Prior art keywords
fan
engine
turbofan engine
nacelle
compressor
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
FR1900579A
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English (en)
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FR3091905A1 (fr
Inventor
Paolo Messina
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.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
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Filing date
Publication date
Application filed by Airbus Operations SAS filed Critical Airbus Operations SAS
Priority to FR1900579A priority Critical patent/FR3091905B1/fr
Publication of FR3091905A1 publication Critical patent/FR3091905A1/fr
Application granted granted Critical
Publication of FR3091905B1 publication Critical patent/FR3091905B1/fr
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
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • 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
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/66—Reversing fan flow using reversing fan blades
    • 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
    • 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)
  • Retarders (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

TURBOREACTEUR DOUBLE FLUX COMPORTANT UN SYSTEME D’INVERSION DE POUSSEE L’invention concerne un turboréacteur double flux (100) comportant : - une soufflante (108), - un moteur (150) avec un compresseur (152) en aval de la soufflante (108), une turbine haute pression (154) en aval du compresseur (152) et présentant un arbre commun (156) avec le compresseur (152), et une turbine basse pression (158) en aval de la turbine haute pression (156) et qui comporte un arbre (160) qui se projette vers l’avant, où le moteur (150) est traversé par une veine primaire (114), - une nacelle (102) fixée autour du moteur (150), - un capot de soufflante (104) fixé autour de la soufflante (108) et de la nacelle (102), où une veine secondaire (112) est délimitée entre la nacelle (102) et le capot de soufflante (104), où le turboréacteur double flux (100) comporte un train épicycloïdal (180) qui est arrangé entre l’arbre (160) et la soufflante (108). Avec un tel mécanisme de train épicycloïdal, le turboréacteur comporte des moyens pour effectuer une inversion de poussée qui sont plus légers et moins encombrants que dans le cas d’état de la technique. Fig. 2
FR1900579A 2019-01-23 2019-01-23 turboreacteur double flux comportant un système d’inversion de poussée Active FR3091905B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1900579A FR3091905B1 (fr) 2019-01-23 2019-01-23 turboreacteur double flux comportant un système d’inversion de poussée

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1900579 2019-01-23
FR1900579A FR3091905B1 (fr) 2019-01-23 2019-01-23 turboreacteur double flux comportant un système d’inversion de poussée

Publications (2)

Publication Number Publication Date
FR3091905A1 FR3091905A1 (fr) 2020-07-24
FR3091905B1 true FR3091905B1 (fr) 2022-08-19

Family

ID=66676823

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1900579A Active FR3091905B1 (fr) 2019-01-23 2019-01-23 turboreacteur double flux comportant un système d’inversion de poussée

Country Status (1)

Country Link
FR (1) FR3091905B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3114622B1 (fr) * 2020-09-29 2023-10-20 Airbus Operations Sas Dispositif d’inversion de poussée par inversion du sens de rotation de la soufflante pour groupe de propulsion d’aéronef

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2775734B1 (fr) * 1998-03-05 2000-04-07 Snecma Procede et dispositif d'inversion de poussee pour moteur a tres grand taux de dilution
US6918244B2 (en) * 2001-08-17 2005-07-19 John Eugene Dickau Vertical takeoff and landing aircraft propulsion systems
US20130255274A1 (en) * 2012-04-02 2013-10-03 Daniel Bernard Kupratis Geared architecture with speed change device for gas turbine engine
US10087886B2 (en) * 2014-05-22 2018-10-02 United Technologies Corporation Turbofan thrust reverser system

Also Published As

Publication number Publication date
FR3091905A1 (fr) 2020-07-24

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