FR3133215B1 - Turbomachine intermediate casing comprising an open fire-tight ring, corresponding turbomachine and assembly method - Google Patents

Turbomachine intermediate casing comprising an open fire-tight ring, corresponding turbomachine and assembly method Download PDF

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Publication number
FR3133215B1
FR3133215B1 FR2201887A FR2201887A FR3133215B1 FR 3133215 B1 FR3133215 B1 FR 3133215B1 FR 2201887 A FR2201887 A FR 2201887A FR 2201887 A FR2201887 A FR 2201887A FR 3133215 B1 FR3133215 B1 FR 3133215B1
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FR
France
Prior art keywords
turbomachine
intermediate casing
structural
ring
shell
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
FR2201887A
Other languages
French (fr)
Other versions
FR3133215A1 (en
Inventor
Bruno Marie-Joseph Anne Padoue Haentjens
Sébastien Nicolas Juigne
Erwan Pierre Antoine Perse
Régis Eugène Henri Servant
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 FR2201887A priority Critical patent/FR3133215B1/en
Publication of FR3133215A1 publication Critical patent/FR3133215A1/en
Application granted granted Critical
Publication of FR3133215B1 publication Critical patent/FR3133215B1/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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • F02C7/25—Fire protection or prevention
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Carter intermédiaire de turbomachine comprenant un moyeu et une virole disposés concentriquement et reliés entre eux par des bras structuraux s'étendant radialement, une boite de transfert étant mécaniquement reliée à un arbre primaire de la turbomachine par l’intermédiaire d’un axe d’entrainement radial disposé dans un des bras structuraux, la virole de carter intermédiaire (1) comprenant un ajourage disposé sur sa partie extérieure en regard du bras structural (2) abritant l’axe d’entrainement radial, l’ajourage coïncidant avec un bol (2a) ménagé dans ledit bras structural communiquant avec un percement d’axe d’entrainement radial destiné à recevoir ledit axe, la virole de carter intermédiaire (1) comprenant en outre : - un anneau d’étanchéité (3) au feu disposé à la jonction entre l’ajourage de la virole de carter intermédiaire et le bol (2a) d’axe structural, - au moins trois dispositifs de maintien (4) de l’anneau d’étanchéité (3), - l’anneau (3) étant un anneau ouvert. Figure pour l’abrégé : Fig 3Intermediate turbomachine casing comprising a hub and a shell arranged concentrically and connected together by structural arms extending radially, a transfer case being mechanically connected to a primary shaft of the turbomachine via a drive axis radial arranged in one of the structural arms, the intermediate casing shell (1) comprising an aperture arranged on its outer part facing the structural arm (2) housing the radial drive axis, the aperture coinciding with a bowl (2a ) provided in said structural arm communicating with a radial drive shaft bore intended to receive said shaft, the intermediate casing shell (1) further comprising: - a fire sealing ring (3) arranged at the junction between the opening of the intermediate casing shell and the bowl (2a) of structural axis, - at least three holding devices (4) of the sealing ring (3), - the ring (3) being an open ring. Figure for abstract: Fig 3

FR2201887A 2022-03-04 2022-03-04 Turbomachine intermediate casing comprising an open fire-tight ring, corresponding turbomachine and assembly method Active FR3133215B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2201887A FR3133215B1 (en) 2022-03-04 2022-03-04 Turbomachine intermediate casing comprising an open fire-tight ring, corresponding turbomachine and assembly method

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2201887 2022-03-04
FR2201887A FR3133215B1 (en) 2022-03-04 2022-03-04 Turbomachine intermediate casing comprising an open fire-tight ring, corresponding turbomachine and assembly method

Publications (2)

Publication Number Publication Date
FR3133215A1 FR3133215A1 (en) 2023-09-08
FR3133215B1 true FR3133215B1 (en) 2024-02-02

Family

ID=81749370

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2201887A Active FR3133215B1 (en) 2022-03-04 2022-03-04 Turbomachine intermediate casing comprising an open fire-tight ring, corresponding turbomachine and assembly method

Country Status (1)

Country Link
FR (1) FR3133215B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2977635B1 (en) * 2011-07-04 2017-03-24 Snecma DRIVE SHAFT DEVICE OF A TURBOMACHINE
US9951639B2 (en) * 2012-02-10 2018-04-24 Pratt & Whitney Canada Corp. Vane assemblies for gas turbine engines
EP2900956B1 (en) * 2012-09-26 2019-11-20 United Technologies Corporation Gas turbine engine comprising a seal assembly for a static structure thereof
FR3010154B1 (en) * 2013-09-05 2015-10-02 Snecma INTERMEDIATE CASTER SEAL PANEL FOR A DOUBLE FLOW AIRCRAFT TURBOMACHINE
FR3083213B1 (en) * 2018-06-29 2020-10-02 Safran Aircraft Engines IMPROVED FIRE RESISTANCE DEVICE INTENDED TO BE INTERPOSED BETWEEN AN AIRCRAFT TURBOMACHINE HANGING MAST END, AND A TURBOMACHINE COVER DELIMING AN INTER-VEIN COMPARTMENT

Also Published As

Publication number Publication date
FR3133215A1 (en) 2023-09-08

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