FR3106152B1 - Impeller ring assembly with indexed flanges - Google Patents

Impeller ring assembly with indexed flanges Download PDF

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Publication number
FR3106152B1
FR3106152B1 FR2000164A FR2000164A FR3106152B1 FR 3106152 B1 FR3106152 B1 FR 3106152B1 FR 2000164 A FR2000164 A FR 2000164A FR 2000164 A FR2000164 A FR 2000164A FR 3106152 B1 FR3106152 B1 FR 3106152B1
Authority
FR
France
Prior art keywords
flanges
flange
ring
indexed
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
FR2000164A
Other languages
French (fr)
Other versions
FR3106152A1 (en
Inventor
Clément Jarrossay
Clément Emile André Cazin
Antoine Claude Michel Etienne Danis
Lucien Henri Jacques Quennehen
Nicolas Paul Tableau
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 FR2000164A priority Critical patent/FR3106152B1/en
Publication of FR3106152A1 publication Critical patent/FR3106152A1/en
Application granted granted Critical
Publication of FR3106152B1 publication Critical patent/FR3106152B1/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
    • 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
    • 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
    • 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
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Ensemble d’anneau de turbine avec flasques indexés . Un ensemble d’anneau de turbine comprenant des secteurs d’anneau (10) formant un anneau de turbine (1) et une structure de support d’anneau (3), chaque secteur (10) ayant une partie formant base annulaire (12) avec, dans la direction radiale (DR), une face interne (12a) et une face externe (12b) à partir de laquelle s’étendent en saillie une première et une seconde pattes (14, 16), la structure (3) comportant une virole (31) à partir de laquelle s’étendent en saillie une première et une seconde brides radiales (32, 36) entre lesquelles sont maintenues les première et seconde pattes (14, 16), un premier flasque (33) annulaire en une pièce et un second flasque (34) annulaire disposés en amont de l’anneau (1). L’ensemble comprend en outre une tôle d’étanchéité annulaire (35) disposée de manière étanche entre la première extrémité (341) du second flasque (34) et la première extrémité (331) du premier flasque (33). Figure pour l’abrégé : Fig. 4.Turbine ring assembly with indexed flanges. A turbine ring assembly comprising ring sectors (10) forming a turbine ring (1) and a ring support structure (3), each sector (10) having an annular base portion (12) with, in the radial direction (DR), an internal face (12a) and an external face (12b) from which project a first and a second lug (14, 16), the structure (3) comprising a ferrule (31) from which project first and second radial flanges (32, 36) between which the first and second lugs (14, 16) are held, a first flange (33) annular in one piece and a second flange (34) annular arranged upstream of the ring (1). The assembly further comprises an annular sealing plate (35) sealingly disposed between the first end (341) of the second flange (34) and the first end (331) of the first flange (33). Figure for abstract: Fig. 4.

FR2000164A 2020-01-09 2020-01-09 Impeller ring assembly with indexed flanges Active FR3106152B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2000164A FR3106152B1 (en) 2020-01-09 2020-01-09 Impeller ring assembly with indexed flanges

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2000164A FR3106152B1 (en) 2020-01-09 2020-01-09 Impeller ring assembly with indexed flanges
FR2000164 2020-01-09

Publications (2)

Publication Number Publication Date
FR3106152A1 FR3106152A1 (en) 2021-07-16
FR3106152B1 true FR3106152B1 (en) 2022-01-21

Family

ID=70918529

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2000164A Active FR3106152B1 (en) 2020-01-09 2020-01-09 Impeller ring assembly with indexed flanges

Country Status (1)

Country Link
FR (1) FR3106152B1 (en)

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2540939A1 (en) 1983-02-10 1984-08-17 Snecma SEALING RING FOR A TURBINE ROTOR OF A TURBOMACHINE AND TURBOMACHINE INSTALLATION PROVIDED WITH SUCH RINGS
US6733235B2 (en) 2002-03-28 2004-05-11 General Electric Company Shroud segment and assembly for a turbine engine
FR2887601B1 (en) 2005-06-24 2007-10-05 Snecma Moteurs Sa MECHANICAL PIECE AND METHOD FOR MANUFACTURING SUCH A PART
CN102272419A (en) 2009-03-09 2011-12-07 斯奈克玛 Turbine ring assembly
FR2955898B1 (en) 2010-02-02 2012-10-26 Snecma UPPER SEALING OF A CMC RING IN A TURBOMACHINE TURBINE
US8740552B2 (en) 2010-05-28 2014-06-03 General Electric Company Low-ductility turbine shroud and mounting apparatus
US8905709B2 (en) 2010-09-30 2014-12-09 General Electric Company Low-ductility open channel turbine shroud
US9759082B2 (en) 2013-03-12 2017-09-12 Rolls-Royce Corporation Turbine blade track assembly
FR3036436B1 (en) * 2015-05-22 2020-01-24 Safran Ceramics TURBINE RING ASSEMBLY WITH HOLDING BY FLANGES
FR3055147B1 (en) * 2016-08-19 2020-05-29 Safran Aircraft Engines TURBINE RING ASSEMBLY
FR3064023B1 (en) * 2017-03-16 2019-09-13 Safran Aircraft Engines TURBINE RING ASSEMBLY
FR3076578B1 (en) * 2018-01-09 2020-01-31 Safran Aircraft Engines TURBINE RING ASSEMBLY

Also Published As

Publication number Publication date
FR3106152A1 (en) 2021-07-16

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