FR3100287B1 - Improved turbofan engine - Google Patents

Improved turbofan engine Download PDF

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Publication number
FR3100287B1
FR3100287B1 FR1909401A FR1909401A FR3100287B1 FR 3100287 B1 FR3100287 B1 FR 3100287B1 FR 1909401 A FR1909401 A FR 1909401A FR 1909401 A FR1909401 A FR 1909401A FR 3100287 B1 FR3100287 B1 FR 3100287B1
Authority
FR
France
Prior art keywords
blades
turbine
downstream
flow
sets
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
FR1909401A
Other languages
French (fr)
Other versions
FR3100287A1 (en
Inventor
Laurent Louis Robert Baudoin
Norman Bruno André Jodet
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 FR1909401A priority Critical patent/FR3100287B1/en
Publication of FR3100287A1 publication Critical patent/FR3100287A1/en
Application granted granted Critical
Publication of FR3100287B1 publication Critical patent/FR3100287B1/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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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)

Abstract

Turboréacteur à double flux amélioré Turboréacteur (1)comprenant un flux primaire (F1) et un flux secondaire (F2), le turboréacteur (1) présentant un axe principal (Z-Z) et comprenant successivement un compresseur (12), une chambre de combustion (14) et une turbine (16) définissant le flux primaire, et une pluralité d’ensembles d’aubes (18) positionnés successivement dans le flux primaire (F1), en aval de la turbine (16), chaque ensemble d’aube (18) comprenant une pluralité d’aubes s’étendant radialement autour de l’axe principal (Z-Z), entre un diamètre interne et un diamètre externe caractérisé en ce que tout ou partie des ensembles d’aubes (18) présente un segment interne (18i) et un segment externe (18x) configurés de manière à définir respectivement un écoulement aval ayant un angle de giration inférieur à 5° et un écoulement aval ayant un angle de giration supérieur à 5°. Figure pour l’abrégé : Fig. 4.Improved bypass turbojet Turbine engine (1) comprising a primary stream (F1) and a secondary stream (F2), the turbojet (1) having a main axis (ZZ) and successively comprising a compressor (12), a combustion chamber ( 14) and a turbine (16) defining the primary flow, and a plurality of sets of blades (18) positioned successively in the primary flow (F1), downstream of the turbine (16), each set of blades ( 18) comprising a plurality of blades extending radially around the main axis (ZZ), between an internal diameter and an external diameter characterized in that all or part of the sets of blades (18) has an internal segment ( 18i) and an outer segment (18x) configured to respectively define a downstream flow having an angle of gyration less than 5 ° and a downstream flow having an angle of gyration greater than 5 °. Figure for the abstract: Fig. 4.

FR1909401A 2019-08-26 2019-08-26 Improved turbofan engine Active FR3100287B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1909401A FR3100287B1 (en) 2019-08-26 2019-08-26 Improved turbofan engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1909401A FR3100287B1 (en) 2019-08-26 2019-08-26 Improved turbofan engine
FR1909401 2019-08-26

Publications (2)

Publication Number Publication Date
FR3100287A1 FR3100287A1 (en) 2021-03-05
FR3100287B1 true FR3100287B1 (en) 2021-08-06

Family

ID=69172889

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1909401A Active FR3100287B1 (en) 2019-08-26 2019-08-26 Improved turbofan engine

Country Status (1)

Country Link
FR (1) FR3100287B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5233827A (en) * 1970-06-08 1993-08-10 General Motors Corporation Radiation supression
US5184459A (en) * 1990-05-29 1993-02-09 The United States Of America As Represented By The Secretary Of The Air Force Variable vane valve in a gas turbine
US7758303B1 (en) * 2006-07-31 2010-07-20 General Electric Company FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween
WO2008143556A1 (en) * 2007-05-22 2008-11-27 Volvo Aero Corporation A masking arrangement for a gas turbine engine
GB2544735B (en) * 2015-11-23 2018-02-07 Rolls Royce Plc Vanes of a gas turbine engine

Also Published As

Publication number Publication date
FR3100287A1 (en) 2021-03-05

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