FR3053728B1 - TWO-PIECE BEARING SUPPORT - Google Patents

TWO-PIECE BEARING SUPPORT Download PDF

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Publication number
FR3053728B1
FR3053728B1 FR1656534A FR1656534A FR3053728B1 FR 3053728 B1 FR3053728 B1 FR 3053728B1 FR 1656534 A FR1656534 A FR 1656534A FR 1656534 A FR1656534 A FR 1656534A FR 3053728 B1 FR3053728 B1 FR 3053728B1
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France
Prior art keywords
bearing support
inner ring
defining
shroud
bearing
Prior art date
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Active
Application number
FR1656534A
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French (fr)
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FR3053728A1 (en
Inventor
Dimitri Marquie
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
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Safran Aircraft Engines SAS
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1656534A priority Critical patent/FR3053728B1/en
Publication of FR3053728A1 publication Critical patent/FR3053728A1/en
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Publication of FR3053728B1 publication Critical patent/FR3053728B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports

Abstract

La présente invention concerne un support de palier (1) de turbomachine comportant : - une partie tronconique (10) ayant une extrémité amont configurée pour être fixée au carter inter-turbine (60) et une extrémité aval portant une bague intérieure (15) ; - une partie aval (20) comportant une virole extérieure (31) et une virole intérieure (21) la bague intérieure (15), la virole extérieure (31) et la virole intérieure (21) définissant ensemble trois peaux concentriques ; le support de palier (1) de turbomachine étant constitué par au moins deux pièces de fonderie fixées l'une sur l'autre au montage, la première (100) de ces pièces définissant la partie tronconique (10) et la bague intérieure (15) et étant adapté pour supporter le palier (5), la seconde pièce (200) définissant la partie aval (20) et étant adaptée pour assurer l'étanchéité de la chambre de lubrification (27).The present invention relates to a turbomachine bearing support (1) comprising: - a tapered part (10) having an upstream end configured to be fixed to the inter-turbine casing (60) and a downstream end bearing an inner ring (15); - a downstream part (20) comprising an outer shroud (31) and an inner shroud (21) the inner ring (15), the outer shroud (31) and the inner shroud (21) together defining three concentric skins; the turbomachine bearing support (1) being constituted by at least two casting parts fixed to one another during assembly, the first (100) of these parts defining the frustoconical part (10) and the inner ring (15 ) and being adapted to support the bearing (5), the second part (200) defining the downstream part (20) and being adapted to seal the lubrication chamber (27).

FR1656534A 2016-07-07 2016-07-07 TWO-PIECE BEARING SUPPORT Active FR3053728B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1656534A FR3053728B1 (en) 2016-07-07 2016-07-07 TWO-PIECE BEARING SUPPORT

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1656534A FR3053728B1 (en) 2016-07-07 2016-07-07 TWO-PIECE BEARING SUPPORT
FR1656534 2016-07-07

Publications (2)

Publication Number Publication Date
FR3053728A1 FR3053728A1 (en) 2018-01-12
FR3053728B1 true FR3053728B1 (en) 2022-01-21

Family

ID=56920794

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1656534A Active FR3053728B1 (en) 2016-07-07 2016-07-07 TWO-PIECE BEARING SUPPORT

Country Status (1)

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FR (1) FR3053728B1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3079265B1 (en) * 2018-03-23 2020-04-17 Safran Aircraft Engines TURBO-BEARING BEARING SUPPORT OBTAINED BY ADDITIVE MANUFACTURING
FR3089547B1 (en) * 2018-12-06 2021-04-02 Safran Aircraft Engines Improved bearing support
FR3107550B1 (en) * 2020-02-24 2022-01-28 Safran Aircraft Engines METHOD FOR ASSEMBLING AN AIRCRAFT TURBOMACHINE MODULE
FR3118989B1 (en) * 2021-01-21 2023-03-03 Safran Aircraft Engines Ventilation crown of the rear bearing support of an aircraft turbomachine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6619030B1 (en) * 2002-03-01 2003-09-16 General Electric Company Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors
US6935837B2 (en) * 2003-02-27 2005-08-30 General Electric Company Methods and apparatus for assembling gas turbine engines
FR2927366B1 (en) * 2008-02-13 2013-07-05 Snecma OIL RECOVERY DEVICE.
US8061969B2 (en) * 2008-11-28 2011-11-22 Pratt & Whitney Canada Corp. Mid turbine frame system for gas turbine engine
EP2906798A4 (en) * 2012-10-09 2016-08-03 United Technologies Corp Bearing support stiffness control

Also Published As

Publication number Publication date
FR3053728A1 (en) 2018-01-12

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