FR3114840B1 - Annular assembly for turbomachine turbine - Google Patents

Annular assembly for turbomachine turbine Download PDF

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Publication number
FR3114840B1
FR3114840B1 FR2010150A FR2010150A FR3114840B1 FR 3114840 B1 FR3114840 B1 FR 3114840B1 FR 2010150 A FR2010150 A FR 2010150A FR 2010150 A FR2010150 A FR 2010150A FR 3114840 B1 FR3114840 B1 FR 3114840B1
Authority
FR
France
Prior art keywords
sector
deflector
crown
annular assembly
ring
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
FR2010150A
Other languages
French (fr)
Other versions
FR3114840A1 (en
Inventor
Vassili Pascal Davesne
Etienne Gérard Joseph Canelle
Garrai Younes El
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 FR2010150A priority Critical patent/FR3114840B1/en
Publication of FR3114840A1 publication Critical patent/FR3114840A1/en
Application granted granted Critical
Publication of FR3114840B1 publication Critical patent/FR3114840B1/en
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
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals
    • 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
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Le présent docuement concerne un ensemble annulaire pour turbine de turbomachine, en particulier d’aéronef, ledit ensemble annulaire s’étendant autour d’un axe longitudinal X et comprenant :- un distributeur (20);- une roue à aubes (4) agencée en aval du distributeur (20) ;- ladite roue à aubes (4) étant entourée par un anneau sectorisé circonférentiellement et porté par le carter (16) externe et formé d’une couronne (18) et d’un déflecteur (20);caractérisé en ce que chaque secteur de déflecteur d’au moins un secteur d’anneau est engagé pour partie dans un logement du secteur de couronne dudit secteur d’anneau et en ce que le secteur de déflecteur et le secteur de couronne coopère par liaison de forme pour le maintien statique du secteur de déflecteur avec le secteur de couronne. Figure à publier avec l’abrégé : Figure 7This document relates to an annular assembly for a turbomachine turbine, in particular an aircraft turbine, said annular assembly extending around a longitudinal axis X and comprising:- a distributor (20);- a blade wheel (4) arranged downstream of the distributor (20); - said blade wheel (4) being surrounded by a circumferentially sectorized ring and carried by the outer casing (16) and formed of a crown (18) and a deflector (20); characterized in that each deflector sector of at least one ring sector is partly engaged in a housing of the crown sector of said ring sector and in that the deflector sector and the crown sector cooperate by linking form for the static maintenance of the deflector sector with the crown sector. Figure to be published with abstract: Figure 7

FR2010150A 2020-10-05 2020-10-05 Annular assembly for turbomachine turbine Active FR3114840B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2010150A FR3114840B1 (en) 2020-10-05 2020-10-05 Annular assembly for turbomachine turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2010150A FR3114840B1 (en) 2020-10-05 2020-10-05 Annular assembly for turbomachine turbine
FR2010150 2020-10-05

Publications (2)

Publication Number Publication Date
FR3114840A1 FR3114840A1 (en) 2022-04-08
FR3114840B1 true FR3114840B1 (en) 2022-11-11

Family

ID=74871448

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2010150A Active FR3114840B1 (en) 2020-10-05 2020-10-05 Annular assembly for turbomachine turbine

Country Status (1)

Country Link
FR (1) FR3114840B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3145182A1 (en) * 2023-01-23 2024-07-26 Safran Aircraft Engines Turbomachine turbine annular assembly particularly for turbine sealing

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3016391B1 (en) * 2014-01-10 2017-12-29 Snecma DEVICE FOR SEALING AND THERMALLY PROTECTING A TURBOMACHINE
FR3058458B1 (en) * 2016-11-09 2020-11-20 Safran Aircraft Engines TURBOMACHINE TURBINE STAGE PROVIDED WITH SEALING MEANS
US10428689B2 (en) * 2017-05-17 2019-10-01 Rolls-Royce Deutschland Ltd & Co Kg Heat shield for a gas turbine engine
FR3083563B1 (en) * 2018-07-03 2020-07-24 Safran Aircraft Engines AIRCRAFT TURBOMACHINE SEALING MODULE

Also Published As

Publication number Publication date
FR3114840A1 (en) 2022-04-08

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