FR3104644B1 - Système propulsif aéronautique à rendement propulsif amélioré - Google Patents

Système propulsif aéronautique à rendement propulsif amélioré Download PDF

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Publication number
FR3104644B1
FR3104644B1 FR1914192A FR1914192A FR3104644B1 FR 3104644 B1 FR3104644 B1 FR 3104644B1 FR 1914192 A FR1914192 A FR 1914192A FR 1914192 A FR1914192 A FR 1914192A FR 3104644 B1 FR3104644 B1 FR 3104644B1
Authority
FR
France
Prior art keywords
propulsion system
fan
low pressure
propulsive efficiency
aeronautical propulsion
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
FR1914192A
Other languages
English (en)
Other versions
FR3104644A1 (fr
Inventor
Maeva Daphné Gros-Borot
Gilles Alain Marie Charier
Matthieu Bruno François Foglia
Caroline Marie Frantz
Adrien Louis Simon
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
Safran Transmission Systems SAS
Original Assignee
Safran Aircraft Engines SAS
Safran Transmission Systems 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, Safran Transmission Systems SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1914192A priority Critical patent/FR3104644B1/fr
Priority to US17/783,721 priority patent/US20230013650A1/en
Priority to EP20845180.7A priority patent/EP4073369A1/fr
Priority to CN202080092718.1A priority patent/CN114945739A/zh
Priority to PCT/FR2020/052391 priority patent/WO2021116621A1/fr
Publication of FR3104644A1 publication Critical patent/FR3104644A1/fr
Application granted granted Critical
Publication of FR3104644B1 publication Critical patent/FR3104644B1/fr
Priority to US18/133,280 priority patent/US20230265813A1/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
    • F02K3/02—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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/028—Units comprising pumps and their driving means the driving means being a planetary gear
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/545—Ducts
    • F04D29/547—Ducts having a special shape in order to influence fluid flow
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/30—Flow characteristics
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/30—Flow characteristics
    • F05D2210/34—Laminar flow
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

La présente invention concerne un système propulsif (1) aéronautique comprenant :- un arbre d’entrainement (10),- un compresseur basse pression (4), - un arbre de soufflante (13) entrainant une soufflante (2), - un mécanisme de réduction (12) couplant l’arbre d’entrainement (10) et l’arbre de soufflante (13), et - un canal d’entrée (3) qui s’étend entre la soufflante (2) et le compresseur basse pression (4), l’entrée (18) présentant un rayon moyen (R3) prédéterminé,un rapport entre un rayon moyen (R3) du canal d’entrée (3) et le rayon moyen (R2) du compresseur basse pression (4) d’une part, et le rapport de réduction du mécanisme de réduction (12) d’autre part, est strictement inférieur à 0.35. Figure pour l’abrégé : Fig. 3
FR1914192A 2019-12-11 2019-12-11 Système propulsif aéronautique à rendement propulsif amélioré Active FR3104644B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
FR1914192A FR3104644B1 (fr) 2019-12-11 2019-12-11 Système propulsif aéronautique à rendement propulsif amélioré
US17/783,721 US20230013650A1 (en) 2019-12-11 2020-12-11 Aeronautic propulsion system with improved propulsion efficiency
EP20845180.7A EP4073369A1 (fr) 2019-12-11 2020-12-11 Système propulsif aéronautique à rendement propulsif amélioré
CN202080092718.1A CN114945739A (zh) 2019-12-11 2020-12-11 具有改进的推进效率的航空推进***
PCT/FR2020/052391 WO2021116621A1 (fr) 2019-12-11 2020-12-11 Système propulsif aéronautique à rendement propulsif amélioré
US18/133,280 US20230265813A1 (en) 2019-12-11 2023-04-11 Aeronautic propulsion system with improved propulsion efficiency

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1914192A FR3104644B1 (fr) 2019-12-11 2019-12-11 Système propulsif aéronautique à rendement propulsif amélioré
FR1914192 2019-12-11

Publications (2)

Publication Number Publication Date
FR3104644A1 FR3104644A1 (fr) 2021-06-18
FR3104644B1 true FR3104644B1 (fr) 2021-11-19

Family

ID=69811205

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1914192A Active FR3104644B1 (fr) 2019-12-11 2019-12-11 Système propulsif aéronautique à rendement propulsif amélioré

Country Status (1)

Country Link
FR (1) FR3104644B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3134867B1 (fr) * 2022-04-22 2024-05-17 Safran Trans Systems Reducteur mecanique de turbomachine d’aeronef

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5010729A (en) * 1989-01-03 1991-04-30 General Electric Company Geared counterrotating turbine/fan propulsion system
US8863491B2 (en) * 2012-01-31 2014-10-21 United Technologies Corporation Gas turbine engine shaft bearing configuration
GB201712993D0 (en) * 2017-08-14 2017-09-27 Rolls Royce Plc Gas turbine engine

Also Published As

Publication number Publication date
FR3104644A1 (fr) 2021-06-18

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