FR3061512B1 - Element radial de stator de turbomachine comportant un raidisseur - Google Patents

Element radial de stator de turbomachine comportant un raidisseur Download PDF

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Publication number
FR3061512B1
FR3061512B1 FR1750112A FR1750112A FR3061512B1 FR 3061512 B1 FR3061512 B1 FR 3061512B1 FR 1750112 A FR1750112 A FR 1750112A FR 1750112 A FR1750112 A FR 1750112A FR 3061512 B1 FR3061512 B1 FR 3061512B1
Authority
FR
France
Prior art keywords
radial element
stator
straightener
internal cavity
turbomachine
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
FR1750112A
Other languages
English (en)
Other versions
FR3061512A1 (fr
Inventor
Patrick Sultana
Sebastien Jean Laurent Prestel
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 FR1750112A priority Critical patent/FR3061512B1/fr
Publication of FR3061512A1 publication Critical patent/FR3061512A1/fr
Application granted granted Critical
Publication of FR3061512B1 publication Critical patent/FR3061512B1/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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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

L'invention concerne un élément radial (54), notamment un bras structurel et/ou au moins une aube formant redresseur, d'un secteur de stator (66) de turbomachine (10) comportant au moins un tronçon angulaire de virole extérieure axiale (68) et un tronçon angulaire de moyeu intérieur axial (70) entre lesquels sont interposés ledit au moins un élément radial (54), ledit élément radial (54) comportant une enveloppe (74) délimitant une cavité interne (76), et étant susceptible d'être soumis à au moins un effort traversant ledit secteur de stator selon un chemin déterminé, caractérisé en ce que ladite cavité interne (54) dudit élément radial (54) comporte au moins un raidisseur (86) qui est formé d'une seule pièce avec l'enveloppe (74) et qui est configuré pour être disposé sur ledit chemin d'effort.
FR1750112A 2017-01-05 2017-01-05 Element radial de stator de turbomachine comportant un raidisseur Active FR3061512B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1750112A FR3061512B1 (fr) 2017-01-05 2017-01-05 Element radial de stator de turbomachine comportant un raidisseur

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1750112A FR3061512B1 (fr) 2017-01-05 2017-01-05 Element radial de stator de turbomachine comportant un raidisseur
FR1750112 2017-01-05

Publications (2)

Publication Number Publication Date
FR3061512A1 FR3061512A1 (fr) 2018-07-06
FR3061512B1 true FR3061512B1 (fr) 2020-10-23

Family

ID=58707700

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1750112A Active FR3061512B1 (fr) 2017-01-05 2017-01-05 Element radial de stator de turbomachine comportant un raidisseur

Country Status (1)

Country Link
FR (1) FR3061512B1 (fr)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2743391B1 (fr) * 1996-01-04 1998-02-06 Snecma Aube refrigeree de distributeur de turbine
US7189064B2 (en) * 2004-05-14 2007-03-13 General Electric Company Friction stir welded hollow airfoils and method therefor
US7980817B2 (en) * 2007-04-16 2011-07-19 United Technologies Corporation Gas turbine engine vane
FR2921973B1 (fr) * 2007-10-04 2011-04-29 Snecma Carter intermediaire de turboreacteur et turboreacteur
US8511968B2 (en) * 2009-08-13 2013-08-20 Siemens Energy, Inc. Turbine vane for a gas turbine engine having serpentine cooling channels with internal flow blockers
US20150096306A1 (en) * 2013-10-08 2015-04-09 General Electric Company Gas turbine airfoil with cooling enhancement

Also Published As

Publication number Publication date
FR3061512A1 (fr) 2018-07-06

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