EP2452050B2 - Ölabscheideranordnung - Google Patents

Ölabscheideranordnung Download PDF

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Publication number
EP2452050B2
EP2452050B2 EP10729924.0A EP10729924A EP2452050B2 EP 2452050 B2 EP2452050 B2 EP 2452050B2 EP 10729924 A EP10729924 A EP 10729924A EP 2452050 B2 EP2452050 B2 EP 2452050B2
Authority
EP
European Patent Office
Prior art keywords
sleeve
hub
cover
shaft
oil separator
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
EP10729924.0A
Other languages
English (en)
French (fr)
Other versions
EP2452050B1 (de
EP2452050A1 (de
Inventor
Olivier Belmonte
Muriel Jane Sylvie Borzakian
Lionel René Henri WELLER
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
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Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP2452050A1 publication Critical patent/EP2452050A1/de
Publication of EP2452050B1 publication Critical patent/EP2452050B1/de
Application granted granted Critical
Publication of EP2452050B2 publication Critical patent/EP2452050B2/de
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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
    • F01D25/18—Lubricating arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
    • F01M13/00—Crankcase ventilating or breathing
    • F01M13/04—Crankcase ventilating or breathing having means for purifying air before leaving crankcase, e.g. removing oil
    • F01M2013/0422—Separating oil and gas with a centrifuge device
    • 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
    • F05D2260/602—Drainage

Definitions

  • the subject of the invention is an oil separator arrangement, located at the end of the turbine shaft of a turbomachine.
  • Such an oil separator (a description of a model can be found in the document EP 0 780 546 A ) is placed at the outlet of an air flow maintained in the machine to transport the oil which lubricates bearings or other parts, in order to separate the air from the oil which is dispersed therein in mist before rejecting the air to the outside, and to return the oil to the inlet of the lubrication device.
  • the recovery of the oil prevents pollution from the outside, drying out of the lubrication circuit or even fires by deposit on hot external parts.
  • the model considered here of the oil separator comprises three main parts: a hub used for mounting and positioning the oil separator on a vent shaft, concentric with the turbine shaft and projecting from the rear of the machine, and extending in front of the end of the turbine shaft; a cover delimiting a housing with the hub; and a filter, which may be a honeycomb network, contained in the housing, retained by the cover and responsible for the separation of air and oil, which is deposited on the walls of the honeycomb when the vent shaft rotates the oil separator.
  • a hub used for mounting and positioning the oil separator on a vent shaft, concentric with the turbine shaft and projecting from the rear of the machine, and extending in front of the end of the turbine shaft
  • a cover delimiting a housing with the hub
  • a filter which may be a honeycomb network, contained in the housing, retained by the cover and responsible for the separation of air and oil, which is deposited on the walls of the honeycomb when the vent shaft rotates the oil separator.
  • the cover and a closing flange of the housing are provided with circular hubs allowing them to be successively threaded onto the vent shaft.
  • the cover is held axially both by pins passing through its hub and the vent shaft, and by stop faces belonging to the turbine shaft and the closing flange.
  • the closing flange appears to be held axially by a nut screwed onto the vent shaft. The arrangement is complicated.
  • the hub and the cover are axially retained on the vent shaft between abutment faces belonging to a bearing and a nut.
  • the cover abuts against a conical shoulder of the shaft.
  • the vent shaft having to ensure the separate abutment of the two elements of the oil separator and being shaped accordingly.
  • the subject of the invention is an improved oil separator arrangement, also lighter than the bolted oil separator, more easily dismantled than the welded oil separator, and also which offers very good cohesion between the hub and the cover, while allowing simple mounting on the vent shaft.
  • the invention relates to an oil separator arrangement according to claim 1.
  • the cover is held by the abutment faces, excluding any means of fixing. This achieves significant weight reduction.
  • the cover is no longer mounted on the vent shaft after the hub, but on the hub: the vent shaft carries the means for abutting only one of the two elements of the oil separator and is therefore simplified; by being held on the hub by its two opposite ends, the cover is assembled with much better cohesion to the hub; finally, it is easy to arrange the sleeve of the hub to make it carry one of the abutment faces of the cover flange, or both.
  • the first thrust face may be a cleat on the sleeve; the second thrust face may be one end of the turbine shaft, or perhaps better, a ring engaged on the sleeve.
  • the arrangement comprises an oil separator 4, a vent shaft 1, a turbine shaft 2 concentric with the previous one and surrounding it; the shafts 1 and 2 extend in a longitudinal direction of the machine to which they belong, the vent shaft 1 projecting beyond one end 3 of the turbine shaft 2 towards the rear of the machine.
  • the oil separator 4 comprises a hub 5 essentially composed of a cylindrical sleeve 16, mounted on the vent shaft 1 and abutting on a shoulder 15 of the turbine shaft 2, and a flange of hub 6, flat, perpendicular to the shafts 1 and 2 and extending outside the sleeve 16 while being integral with it.
  • a tightening nut 7 screwed onto the vent shaft 1 holds the hub 5 in abutment against the shoulder 15.
  • the oil separator 4 also comprises a cover 8, delimiting with the hub 5 a housing 9 in which a filter 10 is contained.
  • the housing 9 is delimited by the sleeve 16, the hub flange 6, a cover flange 11 parallel to the previous one, and a spacer 12 belonging to the cover 8, cylindrical and surrounding the sleeve 16 in a concentric state with it and with the vent shaft 1.
  • the spacer 12 is in one piece with the cover flange 11. One end of the spacer 12 opposite the cover flange 11 extends under a rim 13 of the hub flange 6.
  • the cover 8 is retained axially by a double stop of the cover flange 11: against a cleat 14 standing on the hub 5 by its face inside the housing 9 and towards the rear of the machine, and against the end 3 of the turbine shaft 2 by its external face and towards the front.
  • Longitudinal play is however provided, mainly in order not to compress the thin, perforated spacer 12 subjected to significant centrifugal forces in service.
  • This double stop arrangement makes it possible to retain the cover 8 without any means of fixing other than the interlocking of parts. It is obtained by placing the hub flange 6 at the rear of the sleeve 16, unlike the part designs.
  • the vent shaft 1, the hub 5 and the spacer 12 are perforated to allow a centripetal flow of air through the oil separator 4.
  • the filter 10 is a honeycomb network whose channels are oriented radially; its function is to collect the oil suspended in the flow by deposition on the walls of the honeycomb and to force it outwards thanks to the centrifugal forces caused by the rotation of the oil separator 4, and therefore to allow only perfectly dry air, having completed its centripetal movement, to pass into the vent shaft 1.
  • Other details of the environment of the oil separator, which are however not part of the invention, can be found in the document EP 0 780 546 A .
  • Other fillings, such as marbles, have been used and may still be suitable.
  • the hub flange, now referenced by 6', and the cover, now referenced by 8' are however interchanged along the oil separator 4 while retaining the same shape: the hub flange 6' is now adjacent to the end 3, and the cover flange, now 11', is at the front of the oil separator.
  • the spacer 12 is not only thin but perforated to allow the flow of oil by centrifugation and therefore consists of a group of straps 19 along its circumference between the hub flange 6 or 6' and the cover flange 11 or 11'. These straps 19 are subject to significant bending due to centrifugal forces, which is likely to create stress concentrations at the point where they connect to the cover flange 11 or 11'. To overcome this drawback, it is advantageous to provide the cover flange 11 or 11' with a border 20 at its outer circumference, where the cover flange 11 or 11' connects to the spacer 12, which projects on the side opposite the spacer 12, i.e.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
  • Supercharger (AREA)
  • Centrifugal Separators (AREA)
  • Sliding-Contact Bearings (AREA)

Claims (4)

  1. Ölabscheideranordnung (4, 4') für eine Turbine, umfassend:
    eine Turbinenwelle (2),
    eine Lüftungswelle (1), die von der Turbinenwelle umgeben ist,
    wobei der Ölabscheider eine Nabe (5) mit Stutzen (16) in zylindrischer Form umfasst, die auf der Lüftungswelle montiert ist, und mit Nabenflansch (6), der sich nach außerhalb des Stutzens (16) erstreckt, und
    eine Abdeckung (8, 8') mit Abdeckungsflansch (11, 11') und mit Querband (12) in zylindrischer Form, das den Stutzen (16) umgibt,
    wobei der Nabenflansch einen Rand (13) umfasst, in den das Querband von einem Ende eingeführt wird,
    dadurch gekennzeichnet, dass der Abdeckungsflansch (11, 11') um den Stutzen herum montiert ist, und mit dem Stutzen in Eingriff steht,
    wobei der Stutzen in einer Längsrichtung der Wellen durch ein Element (7) der Lüftungswelle und ein Element (15) der Turbinenwelle festgehalten wird, und
    der Abdeckungsflansch (11, 11') in der Längsrichtung der Wellen zwischen einer ersten Anschlagfläche, die zu dem Stutzen gehört, und einer zweiten Anschlagfläche, die entweder zu dem Stutzen fest gekoppelt ist, oder zu der Turbinenwelle gehört, ohne Befestigungselement der Abdeckung an der Nabe festgehalten wird,
    wobei die zweite Anschlagfläche zu einem Ring (17) gehört, der sich auf dem Stutzen (16) in Eingriff befindet, wenn die zweite Anschlagfläche zu dem Stutzen fest gekoppelt.
  2. Ölabscheideranordnung nach Anspruch 1, dadurch gekennzeichnet, dass die erste Anschlagfläche von einem Ansatz (14, 14') des Stutzens (16) gebildet wird.
  3. Ölabscheideranordnung nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die zweite Anschlagfläche ein Ende (3) der Turbinenwelle (2) ist.
  4. Ölabscheideranordnung nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass der Abdeckungsflansch (11, 11') einen vorstehenden Rand (20) entgegengesetzt zum Querband (12) und dieses verlängernd beinhaltet.
EP10729924.0A 2009-07-10 2010-07-09 Ölabscheideranordnung Active EP2452050B2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0903427A FR2947857B1 (fr) 2009-07-10 2009-07-10 Agencement de deshuileur
PCT/EP2010/059935 WO2011004023A1 (fr) 2009-07-10 2010-07-09 Agencement de deshuileur

Publications (3)

Publication Number Publication Date
EP2452050A1 EP2452050A1 (de) 2012-05-16
EP2452050B1 EP2452050B1 (de) 2018-09-12
EP2452050B2 true EP2452050B2 (de) 2025-04-23

Family

ID=42026251

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10729924.0A Active EP2452050B2 (de) 2009-07-10 2010-07-09 Ölabscheideranordnung

Country Status (9)

Country Link
US (1) US8696779B2 (de)
EP (1) EP2452050B2 (de)
JP (1) JP5580413B2 (de)
CN (1) CN102472113B (de)
BR (1) BR112012000529B1 (de)
CA (1) CA2767265C (de)
FR (1) FR2947857B1 (de)
RU (1) RU2531485C2 (de)
WO (1) WO2011004023A1 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3007463B1 (fr) * 2013-06-21 2017-10-20 Hispano-Suiza Boitier d'accessoires de turbomachine equipe d'un separateur air/huile
DE102015118996A1 (de) * 2015-11-05 2017-05-11 Abb Turbo Systems Ag Wellendichtung
FR3071418B1 (fr) 2017-09-26 2019-09-13 Safran Helicopter Engines Piece pour degazeur centrifuge de turbomachine et procede de fabrication de ladite piece
US10870079B2 (en) * 2018-04-10 2020-12-22 Pratt & Whitney Canada Corp. Air-oil separator with first separator radially outward of matrix separator
US10918989B2 (en) * 2018-04-10 2021-02-16 Pratt & Whitney Canada Corp. Air-oil separator with two flow paths
FR3096402B1 (fr) 2019-05-24 2022-03-04 Safran Pièce pour dégazeur centrifuge de turbomachine avec treillis de filtrage
US11965440B2 (en) 2018-07-05 2024-04-23 Safran Part for a turbomachine centrifugal breather having a filtering mesh
FR3096275B1 (fr) * 2019-05-24 2021-06-18 Safran Helicopter Engines Pièce pour dégazeur centrifuge de turbomachine avec parois longitudinales adaptées
FR3120091B1 (fr) 2021-02-19 2023-06-02 Safran Helicopter Engines Rotor pour un degazeur centrifuge de turbomachine
CN114233474A (zh) * 2021-11-29 2022-03-25 中国航发沈阳发动机研究所 一种一体化结构的油气分离装置

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU322209A1 (ru) * 1969-03-17 1971-11-30 Ю. Д. Блохин , В. П. Сорогин Центробежный суфлер
DE2510225C2 (de) * 1974-03-11 1986-09-11 Pall Corp., Glen Cove, N.Y. Vorrichtung zum Abscheiden von in Gasen schwebenden Flüssigkeiten
GB1508212A (en) * 1975-02-10 1978-04-19 Rolls Royce Apparatus for separating suspension of liquids in gas
FR2696655B1 (fr) * 1992-10-14 1994-11-10 Snecma Appareil pour séparer une suspension de liquide dans un gaz.
FR2742804B1 (fr) * 1995-12-20 1998-01-16 Snecma Rotor deshuileur pour enceinte de lubrification
US5716423A (en) * 1995-12-21 1998-02-10 United Technologies Corporation Multi-stage deoiler with porous media
US6398833B1 (en) * 2000-11-06 2002-06-04 Pratt & Whitney Canada Corp. Air/oil separator
US7377110B2 (en) * 2004-03-31 2008-05-27 United Technologies Corporation Deoiler for a lubrication system
RU52578U1 (ru) * 2005-10-19 2006-04-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Центробежный суфлер
FR2913061B1 (fr) * 2007-02-27 2009-05-22 Snecma Sa Systeme de deshuilage pour moteur d'aeronef.
FR2926738B1 (fr) * 2008-01-29 2010-04-02 Snecma Dispositif de deshuilage et turbomachine comportant ce dispositif
FR2937680B1 (fr) * 2008-10-24 2013-11-08 Snecma Rotor deshuileur pour turbomachine

Also Published As

Publication number Publication date
RU2012104645A (ru) 2013-08-20
CN102472113A (zh) 2012-05-23
BR112012000529A2 (pt) 2019-12-10
CA2767265A1 (fr) 2011-01-13
JP2012533013A (ja) 2012-12-20
JP5580413B2 (ja) 2014-08-27
EP2452050B1 (de) 2018-09-12
RU2531485C2 (ru) 2014-10-20
BR112012000529B1 (pt) 2021-01-12
FR2947857A1 (fr) 2011-01-14
EP2452050A1 (de) 2012-05-16
US8696779B2 (en) 2014-04-15
FR2947857B1 (fr) 2012-03-30
US20120102900A1 (en) 2012-05-03
CN102472113B (zh) 2014-11-19
WO2011004023A1 (fr) 2011-01-13
CA2767265C (fr) 2017-08-08

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