FR3072713B1 - TURBINE RING SECTOR FOR AIRCRAFT TURBOMACHINE - Google Patents

TURBINE RING SECTOR FOR AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3072713B1
FR3072713B1 FR1759983A FR1759983A FR3072713B1 FR 3072713 B1 FR3072713 B1 FR 3072713B1 FR 1759983 A FR1759983 A FR 1759983A FR 1759983 A FR1759983 A FR 1759983A FR 3072713 B1 FR3072713 B1 FR 3072713B1
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FR
France
Prior art keywords
ring sector
aircraft turbomachine
turbine ring
circumferential member
upstream
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
FR1759983A
Other languages
French (fr)
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FR3072713A1 (en
Inventor
Olivier Jean-Daniel Baumas
Quentin Bruno Guy Andre Emile Lievoux
Audrey Elise Josette Avisse
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 FR1759983A priority Critical patent/FR3072713B1/en
Publication of FR3072713A1 publication Critical patent/FR3072713A1/en
Application granted granted Critical
Publication of FR3072713B1 publication Critical patent/FR3072713B1/en
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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
    • F01D11/08—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
    • 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

L'invention se rapporte à un secteur d'anneau de turbine (28a) pour turbomachine d'aéronef, comprenant : - une plateforme (50) ; - un élément abradable (48) comportant une portion principale (46) portée par la plateforme ; - un organe circonférentiel amont (52) de montage du secteur sur un distributeur de turbine (22), l'organe circonférentiel amont formant un creux (54) ouvert vers l'amont et défini en partie par une branche axiale intérieure (56). Selon l'invention, l'élément abradable (48) présente une extension d'abradable (62) se situant au moins en partie radialement au droit de la branche axiale intérieure (56) de l'organe circonférentiel amont (52).The invention relates to a turbine ring sector (28a) for an aircraft turbomachine, comprising: - a platform (50); - an abradable element (48) comprising a main portion (46) carried by the platform; - An upstream circumferential member (52) for mounting the sector on a turbine distributor (22), the upstream circumferential member forming a hollow (54) open upstream and defined in part by an internal axial branch (56). According to the invention, the abradable element (48) has an abradable extension (62) located at least partly radially in line with the inner axial branch (56) of the upstream circumferential member (52).

FR1759983A 2017-10-23 2017-10-23 TURBINE RING SECTOR FOR AIRCRAFT TURBOMACHINE Active FR3072713B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1759983A FR3072713B1 (en) 2017-10-23 2017-10-23 TURBINE RING SECTOR FOR AIRCRAFT TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1759983 2017-10-23
FR1759983A FR3072713B1 (en) 2017-10-23 2017-10-23 TURBINE RING SECTOR FOR AIRCRAFT TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3072713A1 FR3072713A1 (en) 2019-04-26
FR3072713B1 true FR3072713B1 (en) 2021-09-10

Family

ID=60955233

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1759983A Active FR3072713B1 (en) 2017-10-23 2017-10-23 TURBINE RING SECTOR FOR AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3072713B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3134410A1 (en) 2022-04-11 2023-10-13 Safran Aircraft Engines Turbine and associated turbomachine assembly

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6120242A (en) * 1998-11-13 2000-09-19 General Electric Company Blade containing turbine shroud
JP4285134B2 (en) * 2003-07-04 2009-06-24 株式会社Ｉｈｉ Shroud segment
FR2899274B1 (en) * 2006-03-30 2012-08-17 Snecma DEVICE FOR FASTENING RING SECTIONS AROUND A TURBINE WHEEL OF A TURBOMACHINE
US20140271142A1 (en) * 2013-03-14 2014-09-18 General Electric Company Turbine Shroud with Spline Seal

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3134410A1 (en) 2022-04-11 2023-10-13 Safran Aircraft Engines Turbine and associated turbomachine assembly

Also Published As

Publication number Publication date
FR3072713A1 (en) 2019-04-26

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