FR3050759B1 - Ensemble de redressement de flux d'air et turbomachine comprenant un tel ensemble - Google Patents

Ensemble de redressement de flux d'air et turbomachine comprenant un tel ensemble Download PDF

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Publication number
FR3050759B1
FR3050759B1 FR1653756A FR1653756A FR3050759B1 FR 3050759 B1 FR3050759 B1 FR 3050759B1 FR 1653756 A FR1653756 A FR 1653756A FR 1653756 A FR1653756 A FR 1653756A FR 3050759 B1 FR3050759 B1 FR 3050759B1
Authority
FR
France
Prior art keywords
assembly
turbomachine
air flow
end portion
useful part
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
FR1653756A
Other languages
English (en)
Other versions
FR3050759A1 (fr
Inventor
Cedric ZACCARDI
Merwen Orieux Kaelig
Henri Joseph Riera William
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
SNECMA 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, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1653756A priority Critical patent/FR3050759B1/fr
Priority to GB1817365.8A priority patent/GB2564366B/en
Priority to PCT/FR2017/051002 priority patent/WO2017187093A1/fr
Priority to US16/096,832 priority patent/US11280204B2/en
Publication of FR3050759A1 publication Critical patent/FR3050759A1/fr
Application granted granted Critical
Publication of FR3050759B1 publication Critical patent/FR3050759B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/15—Two-dimensional spiral
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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

L'invention concerne un ensemble de redressement d'un flux d'air d'une turbomachine, comprenant deux viroles (30) coaxiales radialement interne et externe, respectivement, entre lesquelles s'étendent des aubes (32) en matériau composite fixées à une première portion d'extrémité (42) à la virole radialement interne et à une seconde portion d'extrémité (44) à la virole (30) radialement externe, les aubes (32) comprenant une partie utile s'étendant entre les deux portions d'extrémité (42, 44). Selon l'invention, pour chaque aube (32), dans un plan perpendiculaire à l'axe des viroles (30) radialement interne et externe, une droite passant par une jonction entre lesdites première et seconde portions d'extrémité (42, 44) et la partie utile forme avec un rayon de la virole radialement interne passant par la jonction entre ladite première portion d'extrémité et la partie utile de ladite aube (32) un angle α tel que 0°<α<90°.
FR1653756A 2016-04-27 2016-04-27 Ensemble de redressement de flux d'air et turbomachine comprenant un tel ensemble Active FR3050759B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
FR1653756A FR3050759B1 (fr) 2016-04-27 2016-04-27 Ensemble de redressement de flux d'air et turbomachine comprenant un tel ensemble
GB1817365.8A GB2564366B (en) 2016-04-27 2017-04-27 Air flow straightening assembly and turbomachine including such an assembly
PCT/FR2017/051002 WO2017187093A1 (fr) 2016-04-27 2017-04-27 Ensemble de redressement de flux d'air et turbomachine comprenant un tel ensemble
US16/096,832 US11280204B2 (en) 2016-04-27 2017-04-27 Air flow straightening assembly and turbomachine including such an assembly

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1653756A FR3050759B1 (fr) 2016-04-27 2016-04-27 Ensemble de redressement de flux d'air et turbomachine comprenant un tel ensemble
FR1653756 2016-04-27

Publications (2)

Publication Number Publication Date
FR3050759A1 FR3050759A1 (fr) 2017-11-03
FR3050759B1 true FR3050759B1 (fr) 2020-02-07

Family

ID=56119655

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1653756A Active FR3050759B1 (fr) 2016-04-27 2016-04-27 Ensemble de redressement de flux d'air et turbomachine comprenant un tel ensemble

Country Status (4)

Country Link
US (1) US11280204B2 (fr)
FR (1) FR3050759B1 (fr)
GB (1) GB2564366B (fr)
WO (1) WO2017187093A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3072607B1 (fr) * 2017-10-23 2019-12-20 Safran Aircraft Engines Turbomachine comprenant un ensemble de redressement

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4131387A (en) * 1976-02-27 1978-12-26 General Electric Company Curved blade turbomachinery noise reduction
FR2664647B1 (fr) * 1990-07-12 1994-08-26 Europ Propulsion Distributeur, notamment pour turbine, a aubes fixes en materiau composite thermostructural, et procede de fabrication.
FR2721000B1 (fr) * 1994-06-10 1996-08-23 Eurocopter France Aube de redresseur en composite, redresseur la comportant, pour dispositif anti-couple à rotor et stator redresseur carénés, et leur procédé de fabrication.
US20080159851A1 (en) * 2006-12-29 2008-07-03 Thomas Ory Moniz Guide Vane and Method of Fabricating the Same
US8221071B2 (en) * 2008-09-30 2012-07-17 General Electric Company Integrated guide vane assembly
WO2012121334A1 (fr) * 2011-03-09 2012-09-13 株式会社Ihi Structure de fixation d'aubes directrices et soufflante
WO2014045770A1 (fr) * 2012-09-19 2014-03-27 本田技研工業株式会社 Structure de stator pour un convertisseur de couple
BR112015010844B1 (pt) * 2012-11-13 2021-04-06 Snecma Preforma de fibra para uma pá de turbomáquina, pá para turbomáquina, invólucro intermediário para turbomáquina, ventilador para turbomáquina, e, turbomáquina
FR3016660B1 (fr) * 2014-01-23 2018-10-05 Safran Aircraft Engines Carter de turbomachine a virole sans empochements et a chapes renforcees par des raidisseurs

Also Published As

Publication number Publication date
US11280204B2 (en) 2022-03-22
US20190106998A1 (en) 2019-04-11
FR3050759A1 (fr) 2017-11-03
GB2564366B (en) 2021-08-25
WO2017187093A1 (fr) 2017-11-02
GB2564366A (en) 2019-01-09
GB201817365D0 (en) 2018-12-12

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