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FR3109962B1 - Aube directrice de sortie pour turbomachine d’aeronef, comprenant un passage de refroidissement de lubrifiant equipe de parois ondulees - Google Patents

Aube directrice de sortie pour turbomachine d’aeronef, comprenant un passage de refroidissement de lubrifiant equipe de parois ondulees Download PDF

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Publication number
FR3109962B1
FR3109962B1 FR2004498A FR2004498A FR3109962B1 FR 3109962 B1 FR3109962 B1 FR 3109962B1 FR 2004498 A FR2004498 A FR 2004498A FR 2004498 A FR2004498 A FR 2004498A FR 3109962 B1 FR3109962 B1 FR 3109962B1
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FR
France
Prior art keywords
guide vane
lubricant
flow
cooling passage
exit guide
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
FR2004498A
Other languages
English (en)
Other versions
FR3109962A1 (fr
Inventor
Christophe Marcel Lucien Perdrigeon
Cédric Zaccardi
Dimitri Daniel Gabriel Marquie
Mohammed-Lamine Boutaleb
Tinguy Tiphaine De
Sébastien Vincent François Dreano
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 FR2004498A priority Critical patent/FR3109962B1/fr
Publication of FR3109962A1 publication Critical patent/FR3109962A1/fr
Application granted granted Critical
Publication of FR3109962B1 publication Critical patent/FR3109962B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F01D25/125—Cooling of bearings
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L’invention concerne une aube directrice pour turbomachine d’aéronef à double flux, l’aube directrice comprenant un pied (34), une tête (36), ainsi qu’une partie aérodynamique (32) de redressement de flux comportant au moins un passage intérieur (50a, 50b) de refroidissement de lubrifiant, l’aube comprenant dans le passage intérieur une matrice de conduction thermique (80), et le passage intérieur (50a, 50b) s’étendant selon une direction principale (52a, 52b) d’écoulement du lubrifiant, parallèle ou sensiblement parallèle à une direction d’envergure (25) de l’aube. Selon l’invention, dans le passage intérieur (50a, 50b), la matrice (80) comporte au moins une paroi ondulée (82) s’étendant selon la direction principale (52a, 52b) d’écoulement du lubrifiant, de manière à délimiter de part et d’autre de celle-ci deux canaux ondulés (86) de circulation de fluide de refroidissement s’étendant également chacun selon la direction principale (52a, 52b). Figure pour l’abrégé : Figure 4a.
FR2004498A 2020-05-06 2020-05-06 Aube directrice de sortie pour turbomachine d’aeronef, comprenant un passage de refroidissement de lubrifiant equipe de parois ondulees Active FR3109962B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2004498A FR3109962B1 (fr) 2020-05-06 2020-05-06 Aube directrice de sortie pour turbomachine d’aeronef, comprenant un passage de refroidissement de lubrifiant equipe de parois ondulees

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2004498 2020-05-06
FR2004498A FR3109962B1 (fr) 2020-05-06 2020-05-06 Aube directrice de sortie pour turbomachine d’aeronef, comprenant un passage de refroidissement de lubrifiant equipe de parois ondulees

Publications (2)

Publication Number Publication Date
FR3109962A1 FR3109962A1 (fr) 2021-11-12
FR3109962B1 true FR3109962B1 (fr) 2022-04-29

Family

ID=71894953

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2004498A Active FR3109962B1 (fr) 2020-05-06 2020-05-06 Aube directrice de sortie pour turbomachine d’aeronef, comprenant un passage de refroidissement de lubrifiant equipe de parois ondulees

Country Status (1)

Country Link
FR (1) FR3109962B1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20240247593A1 (en) * 2023-01-25 2024-07-25 Raytheon Technologies Corporation Two piece hollow-vane assembly joined via brazing
US12110807B1 (en) 2023-03-14 2024-10-08 Rtx Corporation Altering structural response of two-piece hollow-vane assembly by changing the cover composition

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8616834B2 (en) 2010-04-30 2013-12-31 General Electric Company Gas turbine engine airfoil integrated heat exchanger
FR2978196B1 (fr) * 2011-07-20 2016-12-09 Snecma Aubes de turbomachine comprenant une plaque rapportee sur une partie principale
FR2989110B1 (fr) 2012-04-05 2016-09-09 Snecma Aube de stator formee par un ensemble de parties d'aube
US10465525B2 (en) * 2016-07-22 2019-11-05 General Electric Company Blade with internal rib having corrugated surface(s)
FR3066532B1 (fr) * 2017-05-22 2019-07-12 Safran Aircraft Engines Aube directrice de sortie pour turbomachine d'aeronef, comprenant un passage de refroidissement de lubrifiant equipe de plots perturbateurs de flux a fabrication simplifiee

Also Published As

Publication number Publication date
FR3109962A1 (fr) 2021-11-12

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