FR3104206B1 - LUBRICATION ENCLOSURE FOR AN AIRCRAFT TURBOMACHINE - Google Patents

LUBRICATION ENCLOSURE FOR AN AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3104206B1
FR3104206B1 FR1914011A FR1914011A FR3104206B1 FR 3104206 B1 FR3104206 B1 FR 3104206B1 FR 1914011 A FR1914011 A FR 1914011A FR 1914011 A FR1914011 A FR 1914011A FR 3104206 B1 FR3104206 B1 FR 3104206B1
Authority
FR
France
Prior art keywords
shaft
annular
support
enclosure
bearing
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
FR1914011A
Other languages
French (fr)
Other versions
FR3104206A1 (en
Inventor
Paul Ghislain Albert Levisse
Olivier Belmonte
Fabien Roger Gaston Caty
Amélie Argie Antoinette Chassagne
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 FR1914011A priority Critical patent/FR3104206B1/en
Publication of FR3104206A1 publication Critical patent/FR3104206A1/en
Application granted granted Critical
Publication of FR3104206B1 publication Critical patent/FR3104206B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • 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
    • F02C7/06—Arrangements of bearings; Lubricating
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/608—Aeration, ventilation, dehumidification or moisture removal of closed spaces
    • 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
    • F05D2260/98—Lubrication

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Enceinte de lubrification (84) pour une turbomachine (10) d’aéronef, comportant un arbre de rotor (90), au moins un palier (56, 58) de guidage en rotation de l’arbre autour d’un axe (A), un support annulaire (57) dudit au moins un palier, ce support comportant une première bride annulaire de fixation (57a), une pièce annulaire (50) comportant une seconde bride annulaire (46a) fixée à ladite première bride, ledit arbre et ledit support définissant entre eux volume annulaire de ladite enceinte dans lequel est situé ledit au moins un palier, des joints d’étanchéité dynamique (84a, 84b) étant situés entre ledit support et ledit arbre, et/ou entre ladite pièce et ledit arbre, caractérisée en ce que lesdites première et seconde brides sont traversées par au moins une canalisation (100) de passage d’un flux d’air destiné à contourner l’enceinte. Figure pour l'abrégé : Figure 4Lubrication chamber (84) for an aircraft turbomachine (10), comprising a rotor shaft (90), at least one bearing (56, 58) for guiding the shaft in rotation about an axis (A) , an annular support (57) of said at least one bearing, this support comprising a first annular fixing flange (57a), an annular part (50) comprising a second annular flange (46a) fixed to said first flange, said shaft and said support defining between them the annular volume of said enclosure in which said at least one bearing is located, dynamic seals (84a, 84b) being located between said support and said shaft, and / or between said part and said shaft, characterized in that said first and second flanges are crossed by at least one duct (100) for the passage of an air flow intended to bypass the enclosure. Figure for abstract: Figure 4

FR1914011A 2019-12-10 2019-12-10 LUBRICATION ENCLOSURE FOR AN AIRCRAFT TURBOMACHINE Active FR3104206B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1914011A FR3104206B1 (en) 2019-12-10 2019-12-10 LUBRICATION ENCLOSURE FOR AN AIRCRAFT TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1914011 2019-12-10
FR1914011A FR3104206B1 (en) 2019-12-10 2019-12-10 LUBRICATION ENCLOSURE FOR AN AIRCRAFT TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3104206A1 FR3104206A1 (en) 2021-06-11
FR3104206B1 true FR3104206B1 (en) 2021-11-26

Family

ID=69572253

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1914011A Active FR3104206B1 (en) 2019-12-10 2019-12-10 LUBRICATION ENCLOSURE FOR AN AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3104206B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3132732A1 (en) * 2022-02-17 2023-08-18 Safran Aircraft Engines TURBOMACHINE FOR AN AIRCRAFT

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7296398B2 (en) * 2004-10-29 2007-11-20 General Electric Company Counter-rotating turbine engine and method of assembling same
US7458202B2 (en) * 2004-10-29 2008-12-02 General Electric Company Lubrication system for a counter-rotating turbine engine and method of assembling same
US8292034B2 (en) * 2007-11-28 2012-10-23 General Electric Company Air-oil separator
FR2925131B1 (en) 2007-12-14 2010-01-22 Snecma MOUNTING PRESSURIZING TUBES OF AN INTERNAL ENCLOSURE IN A TURBOMACHINE
FR2944558B1 (en) * 2009-04-17 2014-05-02 Snecma DOUBLE BODY GAS TURBINE ENGINE PROVIDED WITH SUPPLEMENTARY BP TURBINE BEARING.
FR3013325B1 (en) 2013-11-20 2015-11-27 Snecma PRESSURE OIL SUPPLY DEVICE OF A TURBOMACHINE LINEAR ACTUATOR
FR3027060B1 (en) 2014-10-14 2016-12-30 Snecma TURBOMACHINE ASSEMBLY COMPRISING A DRAINING DEVICE MOUNTED ON A SEALING DEVICE

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3132732A1 (en) * 2022-02-17 2023-08-18 Safran Aircraft Engines TURBOMACHINE FOR AN AIRCRAFT
WO2023156733A1 (en) * 2022-02-17 2023-08-24 Safran Aircraft Engines Turbomachine for an aircraft

Also Published As

Publication number Publication date
FR3104206A1 (en) 2021-06-11

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