FR3115819B1 - Ensemble de stator de turbomachine d’aéronef, comprenant une structure externe formée de deux tronçons annulaires entourant une couronne aubagée de stator - Google Patents

Ensemble de stator de turbomachine d’aéronef, comprenant une structure externe formée de deux tronçons annulaires entourant une couronne aubagée de stator Download PDF

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Publication number
FR3115819B1
FR3115819B1 FR2011211A FR2011211A FR3115819B1 FR 3115819 B1 FR3115819 B1 FR 3115819B1 FR 2011211 A FR2011211 A FR 2011211A FR 2011211 A FR2011211 A FR 2011211A FR 3115819 B1 FR3115819 B1 FR 3115819B1
Authority
FR
France
Prior art keywords
stator
crown
structure formed
external structure
annular
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
FR2011211A
Other languages
English (en)
Other versions
FR3115819A1 (fr
Inventor
Clément Emile André Cazin
Sébastien Serge Francis Congratel
Pascal Cédric Tabarin
Nicolas Paul Tableau
Matthieu Arnaud Gimat
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
Safran Ceramics SA
Original Assignee
Safran Aircraft Engines SAS
Safran Ceramics SA
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, Safran Ceramics SA filed Critical Safran Aircraft Engines SAS
Priority to FR2011211A priority Critical patent/FR3115819B1/fr
Publication of FR3115819A1 publication Critical patent/FR3115819A1/fr
Application granted granted Critical
Publication of FR3115819B1 publication Critical patent/FR3115819B1/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
    • F01D9/042—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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3212—Application in turbines in gas turbines for a special turbine stage the first stage of a turbine
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • 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
    • F05D2300/6033—Ceramic matrix composites [CMC]
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L’invention se rapporte à un ensemble (20) de stator de turbomachine d’aéronef, l’ensemble s’étendant autour d’un axe central longitudinal (A1) et comprenant une couronne de stator (14) et une structure annulaire (18) qui s’étend autour de la couronne de stator (14), la couronne de stator (14) comportant une pluralité d’aubes de stator (26) qui se succèdent circonférentiellement autour de l’axe central longitudinal (A1), et comprenant une plateforme radialement externe (22a) et une plateforme radialement interne (24a) qui délimitent entre-elles une veine d’écoulement aérodynamique (11A) de turbomachine. Selon l’invention, la structure annulaire (18) comprend un tronçon amont annulaire (18b) et un tronçon aval annulaire (18a) fixés à la couronne de stator (14), et qui sont au contact l’un de l’autre en se succédant le long de l’axe central longitudinal (A1). Figure pour l’abrégé : Fig. 2
FR2011211A 2020-11-02 2020-11-02 Ensemble de stator de turbomachine d’aéronef, comprenant une structure externe formée de deux tronçons annulaires entourant une couronne aubagée de stator Active FR3115819B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2011211A FR3115819B1 (fr) 2020-11-02 2020-11-02 Ensemble de stator de turbomachine d’aéronef, comprenant une structure externe formée de deux tronçons annulaires entourant une couronne aubagée de stator

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2011211 2020-11-02
FR2011211A FR3115819B1 (fr) 2020-11-02 2020-11-02 Ensemble de stator de turbomachine d’aéronef, comprenant une structure externe formée de deux tronçons annulaires entourant une couronne aubagée de stator

Publications (2)

Publication Number Publication Date
FR3115819A1 FR3115819A1 (fr) 2022-05-06
FR3115819B1 true FR3115819B1 (fr) 2023-04-14

Family

ID=74347263

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2011211A Active FR3115819B1 (fr) 2020-11-02 2020-11-02 Ensemble de stator de turbomachine d’aéronef, comprenant une structure externe formée de deux tronçons annulaires entourant une couronne aubagée de stator

Country Status (1)

Country Link
FR (1) FR3115819B1 (fr)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE420632B (sv) * 1980-03-11 1981-10-19 Stal Laval Turbin Ab Turbin med en eller flera ledskovelkransar
FR2724973B1 (fr) * 1982-12-31 1996-12-13 Snecma Dispositif d'etancheite d'aubages mobiles de turbomachine avec controle actif des jeux en temps reel et methode de determination dudit dispositif
SE459683B (sv) * 1987-11-19 1989-07-24 Abb Stal Ab Gasturbin med laenkinfaestning av en taetningsring i en ledskovelkrans
FR2948736B1 (fr) * 2009-07-31 2011-09-23 Snecma Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations
FR3000521B1 (fr) 2012-12-27 2014-12-19 Snecma Tube de liaison a recouvrement
WO2015047478A2 (fr) * 2013-07-23 2015-04-02 United Technologies Corporation Commande de position radiale de structure de support de carter à raccord cannelé
US9915159B2 (en) * 2014-12-18 2018-03-13 General Electric Company Ceramic matrix composite nozzle mounted with a strut and concepts thereof
WO2019240754A2 (fr) * 2018-06-11 2019-12-19 Siemens Aktiengesellschaft Aube céramique et métallique composite pour turbine à combustion

Also Published As

Publication number Publication date
FR3115819A1 (fr) 2022-05-06

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