FR3127524B1 - Stator part of turbomachine with tangentially retained retaining ring - Google Patents

Stator part of turbomachine with tangentially retained retaining ring Download PDF

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Publication number
FR3127524B1
FR3127524B1 FR2110356A FR2110356A FR3127524B1 FR 3127524 B1 FR3127524 B1 FR 3127524B1 FR 2110356 A FR2110356 A FR 2110356A FR 2110356 A FR2110356 A FR 2110356A FR 3127524 B1 FR3127524 B1 FR 3127524B1
Authority
FR
France
Prior art keywords
turbomachine
casing
ring
retaining ring
stator part
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
FR2110356A
Other languages
French (fr)
Other versions
FR3127524A1 (en
Inventor
Antoine Giguet
Nicolas Daniel Delaporte
Pierre Marie Mulheim
Arnaud Martine
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 FR2110356A priority Critical patent/FR3127524B1/en
Publication of FR3127524A1 publication Critical patent/FR3127524A1/en
Application granted granted Critical
Publication of FR3127524B1 publication Critical patent/FR3127524B1/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
    • 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
    • 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
    • F05D2220/3215—Application in turbines in gas turbines for a special turbine stage the last stage of the turbine

Landscapes

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

Abstract

Partie statorique de turbomachine comprenant un carter (22), au moins un aubage fixe statorique (24) et un anneau (26) de maintien dudit aubage (24) monté dans une gorge annulaire (22a) du carter (22), ledit anneau (26) de maintien présentant une forme annulaire comprenant deux extrémités libres (26a, 26b) espacées circonférentiellement l’une de l’autre. Le carter (22) comprend, sur sa surface intérieure une encoche (23) pratiquée localement dans le fond de la gorge annulaire (22a), et l’anneau (26) de maintien comprend un tenon (28a, 28b) de retenue circonférentielle s’étendant respectivement depuis chacune des extrémités libres (26a, 26b) dudit anneau (26) dans l’encoche (23) du carter (22). Figure pour l’abrégé : Fig 3Stator part of a turbomachine comprising a casing (22), at least one fixed stator vane (24) and a ring (26) for holding said vane (24) mounted in an annular groove (22a) of the casing (22), said ring ( 26) holding device having an annular shape comprising two free ends (26a, 26b) spaced circumferentially from one another. The casing (22) comprises, on its interior surface, a notch (23) made locally in the bottom of the annular groove (22a), and the retaining ring (26) comprises a circumferential retaining pin (28a, 28b). extending respectively from each of the free ends (26a, 26b) of said ring (26) in the notch (23) of the casing (22). Figure for abstract: Fig 3

FR2110356A 2021-09-30 2021-09-30 Stator part of turbomachine with tangentially retained retaining ring Active FR3127524B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2110356A FR3127524B1 (en) 2021-09-30 2021-09-30 Stator part of turbomachine with tangentially retained retaining ring

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2110356A FR3127524B1 (en) 2021-09-30 2021-09-30 Stator part of turbomachine with tangentially retained retaining ring
FR2110356 2021-09-30

Publications (2)

Publication Number Publication Date
FR3127524A1 FR3127524A1 (en) 2023-03-31
FR3127524B1 true FR3127524B1 (en) 2023-08-25

Family

ID=78770773

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2110356A Active FR3127524B1 (en) 2021-09-30 2021-09-30 Stator part of turbomachine with tangentially retained retaining ring

Country Status (1)

Country Link
FR (1) FR3127524B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0844369B1 (en) * 1996-11-23 2002-01-30 ROLLS-ROYCE plc A bladed rotor and surround assembly
FR2989724B1 (en) * 2012-04-20 2015-12-25 Snecma TURBINE STAGE FOR A TURBOMACHINE
FR2989725B1 (en) * 2012-04-23 2014-04-11 Snecma TURBINE FLOOR
FR3061741B1 (en) 2017-01-09 2021-04-02 Safran Aircraft Engines TURBINE FOR TURBOMACHINE
FR3079871B1 (en) * 2018-04-10 2020-05-08 Safran Aircraft Engines TURBINE DISTRIBUTOR EQUIPPED WITH A HOLDING JUNK

Also Published As

Publication number Publication date
FR3127524A1 (en) 2023-03-31

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