FR3090033B1 - TURBOMACHINE OUTLET AND BIFURCATION DIRECTOR VANE ASSEMBLY - Google Patents

TURBOMACHINE OUTLET AND BIFURCATION DIRECTOR VANE ASSEMBLY Download PDF

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Publication number
FR3090033B1
FR3090033B1 FR1873247A FR1873247A FR3090033B1 FR 3090033 B1 FR3090033 B1 FR 3090033B1 FR 1873247 A FR1873247 A FR 1873247A FR 1873247 A FR1873247 A FR 1873247A FR 3090033 B1 FR3090033 B1 FR 3090033B1
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FR
France
Prior art keywords
bifurcation
turbomachine
vane assembly
height
guide vane
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
FR1873247A
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French (fr)
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FR3090033A1 (en
Inventor
Laurent Soulat
Eva Julie Lebeault
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 FR1873247A priority Critical patent/FR3090033B1/en
Publication of FR3090033A1 publication Critical patent/FR3090033A1/en
Application granted granted Critical
Publication of FR3090033B1 publication Critical patent/FR3090033B1/en
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Classifications

    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention décrit un ensemble pour une turbomachine comprenant : - une aube directrice de sortie (10), - une bifurcation (20) présentant une hauteur (25) suivant un axe radial (Y1) entre une face interne (6) d’un carter interne (5) et une face externe (8) d’un carter externe (7), - une paroi aérodynamique (30) raccordant un bord de fuite (12) de l’aube directrice de sortie (10) et un bord d’attaque (21) de la bifurcation (20),tel que la paroi aérodynamique (30) présente une hauteur (35) suivant l’axe radial (Y1) entre son bord radial interne (33) et une face externe (8) d’un carter externe (7) strictement inférieure à la hauteur (25) de la bifurcation (20). L’invention porte également sur une turbomachine comprenant une telle aube directrice de sortie (10), bifurcation (20) et/ou paroi aérodynamique (30). Figure pour l’abrégé : Fig. 6The present invention describes an assembly for a turbomachine comprising: - an outlet guide vane (10), - a bifurcation (20) having a height (25) along a radial axis (Y1) between an internal face (6) of a inner casing (5) and an outer face (8) of an outer casing (7), - an aerodynamic wall (30) connecting a trailing edge (12) of the outlet guide vane (10) and an edge of 'attack (21) of the bifurcation (20), such that the aerodynamic wall (30) has a height (35) along the radial axis (Y1) between its inner radial edge (33) and an outer face (8) d 'an outer casing (7) strictly less than the height (25) of the bifurcation (20). The invention also relates to a turbomachine comprising such an outlet guide vane (10), bifurcation (20) and / or aerodynamic wall (30). Figure for the abstract: Fig. 6

FR1873247A 2018-12-18 2018-12-18 TURBOMACHINE OUTLET AND BIFURCATION DIRECTOR VANE ASSEMBLY Active FR3090033B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1873247A FR3090033B1 (en) 2018-12-18 2018-12-18 TURBOMACHINE OUTLET AND BIFURCATION DIRECTOR VANE ASSEMBLY

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1873247A FR3090033B1 (en) 2018-12-18 2018-12-18 TURBOMACHINE OUTLET AND BIFURCATION DIRECTOR VANE ASSEMBLY

Publications (2)

Publication Number Publication Date
FR3090033A1 FR3090033A1 (en) 2020-06-19
FR3090033B1 true FR3090033B1 (en) 2020-11-27

Family

ID=68072454

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1873247A Active FR3090033B1 (en) 2018-12-18 2018-12-18 TURBOMACHINE OUTLET AND BIFURCATION DIRECTOR VANE ASSEMBLY

Country Status (1)

Country Link
FR (1) FR3090033B1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3118786B1 (en) 2021-01-11 2023-10-20 Safran Straightening set
FR3118787B1 (en) * 2021-01-12 2023-06-09 Safran Aircraft Engines PROPULSION ASSEMBLY FOR AIRCRAFT COMPRISING A RECTIFIER VANE INTEGRATED IN AN UPSTREAM PART OF A REDUCED HEIGHT ATTACHMENT MAST

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8221071B2 (en) 2008-09-30 2012-07-17 General Electric Company Integrated guide vane assembly
DE102010014900A1 (en) * 2010-04-14 2011-10-20 Rolls-Royce Deutschland Ltd & Co Kg Secondary flow channel of a turbofan engine
EP2841712A2 (en) * 2012-04-25 2015-03-04 General Electric Company Aircraft engine driveshaft vessel assembly and method of assembling the same
FR3032495B1 (en) * 2015-02-09 2017-01-13 Snecma RECOVERY ASSEMBLY WITH OPTIMIZED AERODYNAMIC PERFORMANCE
FR3039598B1 (en) * 2015-07-29 2019-12-27 Safran Aircraft Engines AIR FLOW RECTIFICATION ASSEMBLY WITH IMPROVED AERODYNAMIC PERFORMANCE
FR3052823B1 (en) * 2016-06-20 2018-05-25 Safran Aircraft Engines AERODYNAMIC BOND IN A TURBOMACHINE PART

Also Published As

Publication number Publication date
FR3090033A1 (en) 2020-06-19

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