FR3092869B1 - TURBOMACHINE DISTRIBUTORS INCLUDING A CONTACT INSERT - Google Patents

TURBOMACHINE DISTRIBUTORS INCLUDING A CONTACT INSERT Download PDF

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Publication number
FR3092869B1
FR3092869B1 FR1901611A FR1901611A FR3092869B1 FR 3092869 B1 FR3092869 B1 FR 3092869B1 FR 1901611 A FR1901611 A FR 1901611A FR 1901611 A FR1901611 A FR 1901611A FR 3092869 B1 FR3092869 B1 FR 3092869B1
Authority
FR
France
Prior art keywords
face
radial wall
turbomachine
axial end
platform
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
FR1901611A
Other languages
French (fr)
Other versions
FR3092869A1 (en
Inventor
Vincent Gérard Michel Moreau
Emmanuel Wilfrid Léon Berche
Tangi Rumon Brusq
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 FR1901611A priority Critical patent/FR3092869B1/en
Publication of FR3092869A1 publication Critical patent/FR3092869A1/en
Application granted granted Critical
Publication of FR3092869B1 publication Critical patent/FR3092869B1/en
Active legal-status Critical Current
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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
    • 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
    • F01D9/02—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
    • 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
    • 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
    • F05D2240/55—Seals

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un distributeur (12) d’une turbine de turbomachine disposé autour d’un axe , comprenant une plateforme interne (18) et une plateforme externe (20) entre lesquelles s’étend au moins une pale (22), la plateforme externe (20) comprenant à une extrémité axiale, une paroi radiale (50) pourvue d’une face d'extrémité axiale (52) destinée à être adjacente selon la direction axiale à une face (44) d’une paroi radiale (42) d’un carter (40) de la turbine, caractérisé en ce qu'il comporte un insert (60) recouvrant axialement la face d'extrémité axiale (52) de la paroi radiale (50) de la plateforme externe (20), et qui est destiné à être en regard et à venir en appui axialement avec ladite face (44) de la paroi radiale (42) du carter (40) de sorte que ledit insert (60) constitue le seul moyen d’appui axial de la face d'extrémité axiale (52) de la paroi radiale (50) de la plateforme externe (20) contre la face (44) de la paroi radiale (42) du carter (40). Figure pour l’abrégé : Figure 2The invention relates to a distributor (12) of a turbomachine turbine arranged around an axis, comprising an internal platform (18) and an external platform (20) between which extends at least one blade (22), the external platform (20) comprising, at one axial end, a radial wall (50) provided with an axial end face (52) intended to be adjacent in the axial direction to a face (44) of a radial wall (42 ) a casing (40) of the turbine, characterized in that it comprises an insert (60) axially covering the axial end face (52) of the radial wall (50) of the external platform (20), and which is intended to face and come into axial abutment with said face (44) of the radial wall (42) of the casing (40) so that said insert (60) constitutes the only means of axial abutment of the axial end face (52) of radial wall (50) of outer platform (20) against face (44) of radial wall (42) of housing (40). Figure for abstract: Figure 2

FR1901611A 2019-02-18 2019-02-18 TURBOMACHINE DISTRIBUTORS INCLUDING A CONTACT INSERT Active FR3092869B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1901611A FR3092869B1 (en) 2019-02-18 2019-02-18 TURBOMACHINE DISTRIBUTORS INCLUDING A CONTACT INSERT

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1901611 2019-02-18
FR1901611A FR3092869B1 (en) 2019-02-18 2019-02-18 TURBOMACHINE DISTRIBUTORS INCLUDING A CONTACT INSERT

Publications (2)

Publication Number Publication Date
FR3092869A1 FR3092869A1 (en) 2020-08-21
FR3092869B1 true FR3092869B1 (en) 2023-01-13

Family

ID=67185310

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1901611A Active FR3092869B1 (en) 2019-02-18 2019-02-18 TURBOMACHINE DISTRIBUTORS INCLUDING A CONTACT INSERT

Country Status (1)

Country Link
FR (1) FR3092869B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2923525B1 (en) * 2007-11-13 2009-12-18 Snecma SEALING A ROTOR RING IN A TURBINE FLOOR
US10161414B2 (en) * 2014-12-15 2018-12-25 United Technologies Corporation High compressor exit guide vane assembly to pre-diffuser junction
US10370992B2 (en) * 2016-02-24 2019-08-06 United Technologies Corporation Seal with integral assembly clip and method of sealing
FR3061741B1 (en) * 2017-01-09 2021-04-02 Safran Aircraft Engines TURBINE FOR TURBOMACHINE

Also Published As

Publication number Publication date
FR3092869A1 (en) 2020-08-21

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