EP2090764B1 - Dispositif de récupération d'huile - Google Patents

Dispositif de récupération d'huile Download PDF

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Publication number
EP2090764B1
EP2090764B1 EP09152349A EP09152349A EP2090764B1 EP 2090764 B1 EP2090764 B1 EP 2090764B1 EP 09152349 A EP09152349 A EP 09152349A EP 09152349 A EP09152349 A EP 09152349A EP 2090764 B1 EP2090764 B1 EP 2090764B1
Authority
EP
European Patent Office
Prior art keywords
oil
recovery device
oil recovery
pressure turbine
ferrule
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
EP09152349A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2090764A1 (fr
Inventor
Jacques René Bart
Serge René Morreale
Jean-Luc Soupizon
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
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2090764A1 publication Critical patent/EP2090764A1/fr
Application granted granted Critical
Publication of EP2090764B1 publication Critical patent/EP2090764B1/fr
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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
    • 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
    • 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 invention relates to an oil recovery device comprising an inter-turbine casing, on which are mounted an upstream bearing support in which is formed a first hole and a downstream bearing support in which is formed a second hole, each equipped with a landing.
  • the low pressure turbine shaft is centered at the rear by an inter-shaft bearing and a bearing mounted on an exhaust casing.
  • the oil passes through several labyrinths. It is recovered by a tube passing through the hub of the exhaust casing. It is then evacuated directly into a room, commonly called "plug". This evacuation device is necessary in order to prevent the oil from spilling onto the hulls of the low pressure turbine discs with the risk of fire that this could cause.
  • this device is not suitable for all types of reactors, particularly in the case of a reactor in which the bearing supports are grouped on an inter-turbine casing, the exhaust casing being no longer structural but making Grid office of rectifier profiles.
  • the evacuated oil must pass through a rotating part, the low pressure turbine spigot.
  • a known type turbojet engine is also described in the document EP-A-1,316,676 .
  • an oil recovery device comprising an inter-turbine casing on which are mounted an upstream bearing support and a downstream bearing support each equipped with a low pressure turbine journal bearing rotatably mounted relative to the inner casing. -turbine. A ferrule and an opening are provided in the low pressure turbine journal. This makes it possible to deliver oil inside the shell.
  • the present invention specifically relates to an oil recovery device that overcomes these disadvantages.
  • the oil recovery device comprises a low-pressure turbine journal rotatably mounted relative to the inter-turbine casing, a downstream bearing support wall located after the second one. hole for guiding the oil, the wall having a seal with a wall coming from the low pressure turbine journal, a fixed ferrule and an oil passage provided in the low pressure turbine journal for delivering the oil to the inside the ferrule.
  • the trunnion of the low-pressure turbine comprises a tongue which extends longitudinally over one end of the ferrule in order to deliver the oil by centrifugation at the said end of the ferrule and the ferrule flares out starting from the end to which the oil is delivered.
  • the oil passage is located at the bottom of a cavity formed by walls of conical shape.
  • the oil recovery device comprises a rotary joint, a first and a second through hole formed in the bearing supports fixed on the inter-turbine casing, a bearing support wall located after the second hole. said wall having sealing means with a wall coming from the low pressure turbine journal, the end of the bearing support wall overhanging the cavity formed by conically shaped walls.
  • the invention relates to a turbomachine which comprises an oil recovery device according to the present invention.
  • FIG. 1 a sectional view of an oil recovery device according to the prior art. It comprises a first bearing 2 and a second bearing 4. These bearings are disposed within an enclosure defined by labyrinth seals. In case of oil flooding of this chamber due to a failure of the oil recovery system, the oil flows through the labyrinths, as shown by the arrows 10 and 12. The oil flows also by the right (according to the figure 1 ) of the bearing 2 as schematized by the arrow 14 and it joins the flow schematized by the arrow 12.
  • the oil passes through another labyrinth seal 16 before being discharged through a discharge pipe 18 into the "plug" (not shown).
  • This evacuation device prevents the oil from spilling onto the flanges of the low pressure turbine discs.
  • this device is not suitable for the case of a reactor in which the bearing supports are grouped on an inter-turbine bearing.
  • FIG. 2 a sectional view of an oil discharge system according to the present invention.
  • the first bearing 2 and the second bearing 4 are mounted on upstream bearing supports 19 and downstream 23 which are mounted on the inter-turbine casing 25.
  • a low-pressure turbine journal 20 is rotatably mounted relative to the inter-turbine casing 25
  • Bearings 2 and 4 are lubricated by nozzles which project a flow of oil.
  • the first tier 2 is lubricated by the nozzle 21, as shown schematically by the arrow 22 and the second bearing 4 is lubricated by the nozzle 24, as shown schematically by the arrow 26.
  • the oil In normal operation, the oil is evacuated as it is introduced through the nozzles 21 and 24.
  • the oil is recovered at the bottom, between the upstream and downstream support supports 19 and 23, and travels in a pipe towards the bottom. outside the engine via an arm, still in the lower part, the interturbine housing 25.
  • it can occur a failure of the oil evacuation system that leads to a flood of the enclosure in which are housed bearings.
  • This enclosure is delimited by a rotating joint 28 located near the bearing 2 and by a rotary joint 30 located near the bearing 4.
  • the oil passes through the rotary joint 28, then through a first hole 32 formed in the upstream bearing support 19, then a second hole 34 made in the support of Downstream bearing 23.
  • the oil is then guided by a wall 36 of the downstream bearing support 23.
  • This wall 36 comprises a sealing by a labyrinth seal 38 with a wall 40 coming from the low-pressure turbine journal 20.
  • the oil crosses the seal 38 and flows into a cavity 42 formed in the low-pressure turbine journal 20.
  • the walls of this cavity are conical so as to promote the flow of oil towards the bottom of the cavity by centrifugation. This bottom is precisely provided with a through hole 44 allowing the oil to pass from one side to the other of the low pressure turbine journal.
  • the low pressure turbine spigot further comprises a tongue 46 which extends longitudinally over a fixed shroud 48.
  • the oil is thus centrifuged on the shell 48.
  • the oil is ejected and trickles on the conical fixed shell 48, via the "drop" rotating 46, to the lower position where there is a hole 50.
  • the oil then passes into the plug (not shown).
  • FIGS. 3 and 4 respectively a perspective view of the front and a rear view of the oil recovery system according to the invention.
  • the rotary joint 28, the first hole 32 and the second hole 34 are recognized, the wall 36 comprising the labyrinth seal 38, the cavity 42 having conical walls, the hole 44 at the bottom of the cavity 42, through which the oil s evacuates and finally the tongue "lance gout" 46 overlying one end of the fixed ferrule 48.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Sliding-Contact Bearings (AREA)
  • Gasket Seals (AREA)
EP09152349A 2008-02-13 2009-02-09 Dispositif de récupération d'huile Active EP2090764B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0850899A FR2927366B1 (fr) 2008-02-13 2008-02-13 Dispositif de recuperation d'huile.

Publications (2)

Publication Number Publication Date
EP2090764A1 EP2090764A1 (fr) 2009-08-19
EP2090764B1 true EP2090764B1 (fr) 2011-04-13

Family

ID=39792770

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09152349A Active EP2090764B1 (fr) 2008-02-13 2009-02-09 Dispositif de récupération d'huile

Country Status (6)

Country Link
US (1) US8312702B2 (ru)
EP (1) EP2090764B1 (ru)
CA (1) CA2652810C (ru)
DE (1) DE602009001007D1 (ru)
FR (1) FR2927366B1 (ru)
RU (1) RU2480599C2 (ru)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2968062B1 (fr) * 2010-11-26 2012-11-16 Snecma Dispositif d'evacuation d'huile et turbomachine comprenant un tel dispositif
FR2985766B1 (fr) * 2012-01-16 2016-07-22 Snecma Agencement pour le guidage de l'ecoulement d'un liquide par rapport au rotor d'une turbomachine
FR2992679A1 (fr) * 2012-06-28 2014-01-03 Snecma Tourillon de turbomachine comportant une couronne de recuperation d'un flux d'huile de lubrification avec une pluralite d'orifices d'evacuation d'huile de lubrification
FR2998611B1 (fr) 2012-11-29 2018-08-10 Safran Aircraft Engines Ensemble formant joint d'etancheite pour une turbomachine comportant un joint a brosse
FR3005487B1 (fr) 2013-05-13 2015-06-05 Snecma Ensemble formant joint d'etancheite pour une turbomachine comportant des moyens de lubrification d'un joint a brosse
FR3007069B1 (fr) * 2013-06-12 2015-07-17 Snecma Tourillon pour turbine haute pression, et turboreacteur incluant un tel tourillon
FR3008738B1 (fr) * 2013-07-16 2015-08-28 Snecma Dispositif de protection contre les fuites d'huile vers les rotors d'une turbine de turbomachine
FR3013387B1 (fr) * 2013-11-20 2015-11-20 Snecma Support de palier presentant une geometrie facilitant l'evacuation des noyaux de fonderie
EP3091177B1 (de) * 2015-05-07 2017-12-20 MTU Aero Engines GmbH Rotor für eine strömungsmaschine und verdichter
US10648365B2 (en) * 2015-12-08 2020-05-12 General Electric Company Gas turbine engine bearing sump and lubricant drain line from cooling passage
FR3053728B1 (fr) * 2016-07-07 2022-01-21 Safran Aircraft Engines Support de palier en deux pieces
CN109707515B (zh) * 2018-12-04 2020-04-21 中国科学院工程热物理研究所 一种用于燃气轮机润滑油路系统的叶轮式轮盘结构
US10954861B2 (en) * 2019-03-14 2021-03-23 Raytheon Technologies Corporation Seal for a gas turbine engine
FR3101662B1 (fr) * 2019-10-03 2023-04-14 Safran Aircraft Engines Agencement de turbine intégrant une rigole circonférentielle de récupération d’huile
FR3137407B1 (fr) 2022-06-30 2024-05-24 Safran Aircraft Engines Turbomachine comportant un dispositif de recuperation d’huile ameliore

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2991005A (en) * 1957-10-14 1961-07-04 Gen Motors Corp Compressor scavenging system
US3528241A (en) * 1969-02-24 1970-09-15 Gen Electric Gas turbine engine lubricant sump vent and circulating system
FR2524064A1 (fr) * 1982-03-26 1983-09-30 Snecma Dispositif de graissage et de refroidissement pour palier inter-arbres d'une turbomachine
US5813214A (en) * 1997-01-03 1998-09-29 General Electric Company Bearing lubrication configuration in a turbine engine
RU2153590C1 (ru) * 1999-04-02 2000-07-27 Открытое Акционерное Общество "А. Люлька-Сатурн" Двухроторный газотурбинный двигатель
US6708482B2 (en) * 2001-11-29 2004-03-23 General Electric Company Aircraft engine with inter-turbine engine frame
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
RU26819U1 (ru) * 2002-05-30 2002-12-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Охлаждаемая турбина двухроторного газотурбинного двигателя
FR2858649B1 (fr) * 2003-08-05 2005-09-23 Snecma Moteurs Turbine basse-pression de turbomachine
US7409819B2 (en) * 2004-10-29 2008-08-12 General Electric Company Gas 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
US7334982B2 (en) * 2005-05-06 2008-02-26 General Electric Company Apparatus for scavenging lubricating oil
FR2889561B1 (fr) * 2005-08-02 2010-10-29 Snecma Systeme d'etancheite de la chambre de lubrification arriere d'un turboreacteur
US7836675B2 (en) * 2006-02-21 2010-11-23 General Electric Company Supercore sump vent pressure control
FR2898939B1 (fr) * 2006-03-22 2008-05-09 Snecma Sa Systeme de degivrage d'un cone d'entree de turbomoteur pour aeronef

Also Published As

Publication number Publication date
FR2927366A1 (fr) 2009-08-14
DE602009001007D1 (de) 2011-05-26
CA2652810C (en) 2016-01-19
CA2652810A1 (en) 2009-08-13
RU2480599C2 (ru) 2013-04-27
FR2927366B1 (fr) 2013-07-05
US20090199534A1 (en) 2009-08-13
EP2090764A1 (fr) 2009-08-19
US8312702B2 (en) 2012-11-20
RU2009104918A (ru) 2010-08-20

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