FR3107077B1 - Plateforme de turbomachine rigidifiee - Google Patents

Plateforme de turbomachine rigidifiee Download PDF

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Publication number
FR3107077B1
FR3107077B1 FR2001381A FR2001381A FR3107077B1 FR 3107077 B1 FR3107077 B1 FR 3107077B1 FR 2001381 A FR2001381 A FR 2001381A FR 2001381 A FR2001381 A FR 2001381A FR 3107077 B1 FR3107077 B1 FR 3107077B1
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FR
France
Prior art keywords
platform
main wall
turbomachine
stiffener
rigidified
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
FR2001381A
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English (en)
Other versions
FR3107077A1 (fr
Inventor
Jérémy Philippe Pierre Edynak
Claire Marie Figeureu
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 FR2001381A priority Critical patent/FR3107077B1/fr
Publication of FR3107077A1 publication Critical patent/FR3107077A1/fr
Application granted granted Critical
Publication of FR3107077B1 publication Critical patent/FR3107077B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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

L'invention concerne une plateforme (18) de soufflante (12) de turbomachine (10), qui est destinée à être montée sur un moyeu (14) de la soufflante (12) entre deux aubes (16) adjacentes, la plateforme (18) comportant une paroi principale (20) qui est de forme cintrée selon la direction longitudinale en ayant des bords (24, 26) courbés, un raidisseur (34) qui est monté sur une face interne (36) de la paroi principale (20), caractérisée en ce que le raidisseur (34) comporte au moins deux tronçons (38) rectilignes qui sont inclinés l'un par rapport à l'autre et inclinés par rapport à la direction principale longitudinale, les parois d’extrémité transversales (44, 46) de chacun desdits tronçons (38) ayant leurs tranches externes situées à l’opposé de la paroi principale (20) qui sont libres de manière que la section du raidisseur soit ouverte à l’opposé de la paroi principale (20). Figure pour l’abrégé : Figure 3
FR2001381A 2020-02-12 2020-02-12 Plateforme de turbomachine rigidifiee Active FR3107077B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2001381A FR3107077B1 (fr) 2020-02-12 2020-02-12 Plateforme de turbomachine rigidifiee

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2001381 2020-02-12
FR2001381A FR3107077B1 (fr) 2020-02-12 2020-02-12 Plateforme de turbomachine rigidifiee

Publications (2)

Publication Number Publication Date
FR3107077A1 FR3107077A1 (fr) 2021-08-13
FR3107077B1 true FR3107077B1 (fr) 2022-12-23

Family

ID=71111525

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2001381A Active FR3107077B1 (fr) 2020-02-12 2020-02-12 Plateforme de turbomachine rigidifiee

Country Status (1)

Country Link
FR (1) FR3107077B1 (fr)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6447250B1 (en) * 2000-11-27 2002-09-10 General Electric Company Non-integral fan platform
US9657583B2 (en) * 2012-01-09 2017-05-23 Snecma Composite material reinforcing part of pi-shaped section, in particular a platform for a turbine engine fan, and its method of fabrication
FR3084104B1 (fr) * 2018-07-20 2020-10-23 Safran Aircraft Engines Plateforme rigidifiee

Also Published As

Publication number Publication date
FR3107077A1 (fr) 2021-08-13

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