US20040179935A1 - Seal - Google Patents

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Publication number
US20040179935A1
US20040179935A1 US10/793,853 US79385304A US2004179935A1 US 20040179935 A1 US20040179935 A1 US 20040179935A1 US 79385304 A US79385304 A US 79385304A US 2004179935 A1 US2004179935 A1 US 2004179935A1
Authority
US
United States
Prior art keywords
seal
lubricant
weir
shafts
passage
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.)
Abandoned
Application number
US10/793,853
Other languages
English (en)
Inventor
Alan Maguire
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of US20040179935A1 publication Critical patent/US20040179935A1/en
Priority to US11/113,036 priority Critical patent/US20050230922A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/40—Sealings between relatively-moving surfaces by means of fluid
    • F16J15/42—Sealings between relatively-moving surfaces by means of fluid kept in sealing position by centrifugal force
    • 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
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/30—Parts of ball or roller bearings
    • F16C33/66—Special parts or details in view of lubrication
    • F16C33/6637—Special parts or details in view of lubrication with liquid lubricant
    • F16C33/6659—Details of supply of the liquid to the bearing, e.g. passages or nozzles
    • F16C33/6677—Details of supply of the liquid to the bearing, e.g. passages or nozzles from radial inside, e.g. via a passage through the shaft and/or inner ring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/30—Parts of ball or roller bearings
    • F16C33/66—Special parts or details in view of lubrication
    • F16C33/6637—Special parts or details in view of lubrication with liquid lubricant
    • F16C33/6685—Details of collecting or draining, e.g. returning the liquid to a sump
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/162—Special parts or details relating to lubrication or cooling of the sealing itself
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/22—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings
    • F16C19/24—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for radial load mainly
    • F16C19/26—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for radial load mainly with a single row of rollers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2360/00—Engines or pumps
    • F16C2360/23—Gas turbine engines

Definitions

  • the present invention relates to seals and more particularly to seals used between rotating shafts.
  • a seal for rotating shafts the seal being formed between inter-engaging shafts appropriately lubricated by a lubricant source, this seal characterized in that a weir is formed by overlapping flanges with a weir pool therebetween, one flange including a passage for controlled release of lubricant from the weir pool for a desired purpose.
  • the overlapping flanges of the shafts are arranged whereby weir pool formation is facilitated in use by co-rotation of the shafts.
  • the desired purpose is as a coolant in use for a seal element and/or as a lubricant for specific parts of the seal as required.
  • the seal element is a carbon seal extending from one shaft to the other.
  • the other lubricant lubricates and/or cools a bearing.
  • that bearing is a roller bearing assembly between the shafts.
  • the lubricant source is an oil jet generally propelling oil towards the seal.
  • oil jet generally propelling oil towards the seal.
  • the weir edge forms a lip for cascade of other lubricant and flow along a surface to a sump hole.
  • the seal is located between a high pressure shaft and a low pressure shaft of a turbine engine.
  • FIG. 1 is a schematic half cross-section of a turbine engine
  • FIG. 2 is a schematic cross-section of a seal in accordance with the present invention.
  • a gas turbine engine is generally indicated at 10 and comprises, in axial flow series, an air intake 11 , a propulsive fan 12 , an intermediate pressure compressor 13 , a high pressure compressor 14 , combustion equipment 15 , a high pressure turbine 16 , an intermediate pressure turbine 17 , a low pressure turbine 18 and an exhaust nozzle 19 .
  • the gas turbine engine 10 works in a conventional manner so that air entering the intake 11 is accelerated by the fan 12 which produce two air flows: a first air flow into the intermediate pressure compressor 13 and a second air flow which provides propulsive thrust.
  • the intermediate pressure compressor compresses the air flow directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
  • the compressed air exhausted from the high pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive, the high, intermediate and low pressure turbines 16 , 17 and 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust.
  • the high, intermediate and low pressure turbine 16 , 17 and 18 respectively drive the high and intermediate pressure compressors 14 and 13 , and the fan 12 by suitable interconnecting shafts.
  • the present invention relates to a seal between a higher pressure and a lower pressure shaft typically in an engine 10 as described above with regard to FIG. 1.
  • FIG. 2 is a schematic illustration of a seal 21 in accordance with the present invention.
  • a high pressure shaft 22 is arranged such that it is concentric about a low pressure shaft 23 with the seal 21 between them. It will be understood that the shafts 22 , 23 are generally cylindrical and rotate about a central axis.
  • a knife edge seal 24 in cooperation with a circlip retainer 25 act in association with other bearings to appropriately present the shafts 22 , 23 relative to each other.
  • the high pressure shaft 22 itself is secured within a housing 26 with a bearing 27 to allow rotation.
  • the seal 21 in accordance with the present invention provides a barrier between a high pressure side 28 and a low pressure side 29 .
  • a barrier should preferably be created without requiring related recesses in a shaft and into which oil and a knife edge seal element are located to create the desired seal barrier.
  • recesses create problems with regard to assembly.
  • a carbon seal 30 is provided in order to establish the desired seal barrier between the high pressure side 28 and a low pressure side 29 .
  • this carbon seal 30 requires cooling in order to prevent degradation and over heating of a portion 31 of the shaft 22 .
  • a weir is provided by overlapping flanges 20 , 32 .
  • the weir creates a weir pool 33 formed from lubricating oil projected by a jet 34 .
  • the shafts 22 , 23 are normally co-rotating rapidly such that by centrifugal forces the lubricating oil congregates within a weir well 35 as shown in FIG. 2. Due to the pressure differential and the relative inefficiency of the knife edge seal 24 there is a slight bias pressure presented to one side of the weir pool 33 . This bias pressure is in a cavity 36 .
  • a passage 37 is provided whereby a proportion of the lubricant oil in the weir pool 33 is allowed to leak through the passage 37 into a gallery 38 .
  • the leakage of lubricant is controlled.
  • the jet 34 presents lubricant (shown by arrowhead 39 ) to the seal 21 and in particular the weir pool 33 .
  • other lubricant oil passes over a weir edge 40 .
  • approximately 10% of the lubricant oil passes through the passage 37 whilst the remainder or other lubricant passes over the weir edge 40 .
  • alternative proportions may be used where necessary for operational requirements.
  • Lubricant passing through the passage 37 enters the gallery 38 and again through centrifugal force migrates along a surface 41 until it is collected within a gutter 42 .
  • a radial conduit 43 At the base of this gutter 42 is a radial conduit 43 such that the lubricant oil is ejected in the direction of arrowhead 44 within a cavity 45 at the rear of the carbon seal 30 .
  • the lubricant oil passing through the passage 37 in addition to being a lubricant acts as a coolant for the seal 30 by extracting heat energy from the portion 31 of the shaft 32 below the seal 30 as well as through contact in the conduit 43 and at the rear of the seal within the cavity 45 of the housing 26 . In such circumstances, overheating of the carbon seal 30 is inhibited by heat exchange with this oil.
  • the other lubricant oil which passes over the weir edge 40 migrates again under the influence of centrifugal forces along a surface 46 until it passes through a sump slot 47 into the gallery 38 .
  • the lubricant oil which passes through the sump slot 47 is collected within a reservoir 48 and thereafter distributed through radial conduits 49 to lubricate the bearing 27 .
  • this bearing 27 is a caged roller assembly.
  • the lubricating oil which passes through the conduits 43 , 49 is collected, filtered and normally cooled before being returned through the jet 34 as projected lubricant 39 directed towards the seal 21 and weir pool 33 .
  • the jet 34 will provide an indirect supply of lubricant oil to the weir pool 33 . Rotation of the shaft 32 will effectively scatter and disperse the lubricant oil and subsequent centrifugal force will collect that lubricant oil within the weir pool 33 and drive movement along the surfaces 41 , 46 .
  • a flange 32 forms the weir and weir pool 33 by re-entrant overlap with another flange in the form of the weir edge 40 .
  • this weir edge 40 will be formed as a collet member appropriately secured by the circlip retainer 25 .
  • the low pressure shaft 23 will be located within the high pressure shaft 22 with engagement between the knife edge seal 24 and an anvil seal foot 50 .
  • the collet will then be located and retained by the circlip retainer 25 in order to create the gallery 38 . It will be understood that normally a number of passages 37 will be created between the weir pool 33 and the gallery 38 .
  • passages 37 may be made by grooves or castellations in the end of the collet adjacent to the weir edge 40 .
  • the passages 37 will be formed by the grooves or the gaps between the raised portions of the castellations in engagement with an inner surface of the shaft 22 .
  • weir lip 40 as well as the inner surface of the shaft 22 immediately after the passage 37 are shaped for rapid cascade flow away typically under the action of centrifugal forces in order to promote flow respectively along the surfaces 41 and 46 .
  • the lubricant oil which passes through the passage 37 will act to suspend the collet retained by the retainer 25 .
  • the lubricant which passes through the passage 37 is pressurised by the action of centrifugal forces as well as the overpressure within the cavity 36 as a result of the relative inefficiency of the knife seal 24 .
  • the flange 32 will extend sufficiently within the overlap with the weir edge 40 in order to ensure an adequate depth of lubricant oil in the weir pool 33 to provide a hydraulic seal preventing escape of the overpressure within the cavity 36 as well as determining the overflow rate of lubricant oil over the weir edge 40 .
  • the high pressure shaft 22 will generally be an integral part of a disc/shaft combination 51 .
  • Such arrangement as described required bolting of two components together in order to define the recess with the blade seal element in between.
  • the present invention provides a seal which does not require such combination for a hydraulic seal.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing With Elastic Sealing Lips (AREA)
US10/793,853 2003-03-15 2004-03-08 Seal Abandoned US20040179935A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US11/113,036 US20050230922A1 (en) 2003-03-15 2005-04-25 Seal

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB0305974.8A GB0305974D0 (en) 2003-03-15 2003-03-15 A seal
GB0305974.8 2003-03-15

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US11/113,036 Continuation-In-Part US20050230922A1 (en) 2003-03-15 2005-04-25 Seal

Publications (1)

Publication Number Publication Date
US20040179935A1 true US20040179935A1 (en) 2004-09-16

Family

ID=9954854

Family Applications (2)

Application Number Title Priority Date Filing Date
US10/793,853 Abandoned US20040179935A1 (en) 2003-03-15 2004-03-08 Seal
US11/113,036 Abandoned US20050230922A1 (en) 2003-03-15 2005-04-25 Seal

Family Applications After (1)

Application Number Title Priority Date Filing Date
US11/113,036 Abandoned US20050230922A1 (en) 2003-03-15 2005-04-25 Seal

Country Status (4)

Country Link
US (2) US20040179935A1 (fr)
EP (1) EP1460319B1 (fr)
DE (1) DE602004000658T2 (fr)
GB (1) GB0305974D0 (fr)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050230922A1 (en) * 2003-03-15 2005-10-20 Maguire Alan R Seal
US20070025835A1 (en) * 2005-06-22 2007-02-01 Honeywell International, Inc. Internally-cooled seal housing for turbine engine
US20090238691A1 (en) * 2006-11-28 2009-09-24 Purdey Matthew J Hydraulic Seal for a turbocharger
US20130078091A1 (en) * 2011-09-28 2013-03-28 Rolls-Royce Plc Sealing arrangement
WO2015094539A1 (fr) 2013-12-16 2015-06-25 United Technologies Corporation Palier de transfert pour réacteur à double flux à réducteur
JP2015190376A (ja) * 2014-03-28 2015-11-02 本田技研工業株式会社 ガスタービンエンジンのベアリング潤滑構造
JP2016521823A (ja) * 2013-06-12 2016-07-25 スネクマ 高圧タービンのためのトラニオン、およびこのようなトラニオンを含むターボジェットエンジン
US9453535B2 (en) * 2014-01-06 2016-09-27 Hamilton Sundstrand Corporation Oil retention and delivery system for a bearing
US20160348792A1 (en) * 2015-05-26 2016-12-01 Pratt & Whitney Canada Corp. Internally cooled seal runner and method of cooling seal runner of a gas turbine engine
US9631508B2 (en) 2013-06-13 2017-04-25 Pratt & Whitney Canada Corp. Internally cooled seal runner
JP2017526847A (ja) * 2014-09-05 2017-09-14 サフラン・エアクラフト・エンジンズ ターボマシンシャフト
US20170370288A1 (en) * 2016-06-28 2017-12-28 Rolls-Royce Deutschland Ltd & Co Kg Oil distribution system and turbomachine with an oil distribution system
US10400787B2 (en) * 2014-05-30 2019-09-03 Nuovo Pignone Srl Sealing device for turbomachines
US11203948B2 (en) * 2019-09-06 2021-12-21 Pratt & Whitney Canada Corp. Seal runner and method
US12000299B1 (en) * 2023-08-25 2024-06-04 Rolls-Royce Corporation Centrifugally operated oil shield for lubrication flow control

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0615144D0 (en) 2006-07-29 2006-09-06 Rolls Royce Plc Turbomachine blade
US8678741B2 (en) * 2008-11-28 2014-03-25 Pratt & Whitney Canada Corp. Oil cooled runner
DE102012011144A1 (de) * 2012-06-05 2013-12-05 Rolls-Royce Deutschland Ltd & Co Kg Hydraulische Dichtungsanordnung
WO2014138617A1 (fr) 2013-03-08 2014-09-12 United Technologies Corporation Agencement de joint refroidi par fluide pour un moteur à turbine à gaz
US9896969B2 (en) * 2015-03-19 2018-02-20 United Technologies Corporation Zero or low leakage oil transfer bearing
US10371263B2 (en) 2017-06-23 2019-08-06 United Technologies Corporation Hydraulic seal for non-mainshaft, rotating to static
CN109373171B (zh) * 2018-12-19 2020-12-01 中国航发沈阳发动机研究所 一种轴间轴承收油结构及收油效率试验方法
CN112797078A (zh) * 2021-02-05 2021-05-14 中国航发沈阳发动机研究所 一种轴承密封支撑结构
US20230399978A1 (en) * 2022-06-10 2023-12-14 Raytheon Technologies Corporation Turbine Engine Shaft Plug
US12044172B2 (en) * 2022-11-02 2024-07-23 General Electric Company Air guide for a gas turbine engine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3765688A (en) * 1971-07-19 1973-10-16 Avco Corp High speed shaft centrifuge fluid seal
US5593165A (en) * 1994-09-20 1997-01-14 Allison Engine Company, Inc. Circumferential flow channel for carbon seal runner cooling
US5984630A (en) * 1997-12-24 1999-11-16 General Electric Company Reduced windage high pressure turbine forward outer seal
US6170832B1 (en) * 1998-03-26 2001-01-09 Hermann H. F. Ernst Fluid ring seal system and method
US6568688B1 (en) * 1999-04-14 2003-05-27 Rolls-Royce Deutschland Ltd & Co Kg Hydraulic seal arrangement, more particularly on a gas turbine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2284465A (en) * 1940-11-25 1942-05-26 Gen Electric Shaft packing
US2891808A (en) * 1957-06-20 1959-06-23 Falk Corp Oil-and-vapor shaft-seal
GB984497A (en) * 1963-10-15 1965-02-24 Rolls Royce Bearing assembly
GB961522A (en) * 1963-01-09 1964-06-24 Rolls Royce Bearing assembly
GB1219171A (en) * 1968-03-29 1971-01-13 Rolls Royce Improvements in or relating to gas turbine engine accessory drive systems
GB2125118A (en) * 1982-08-03 1984-02-29 Rolls Royce Hydraulic seal
US4453784A (en) * 1983-05-02 1984-06-12 United Technologies Corporation Means for feeding oil between counterrotating shafts
GB8318582D0 (en) * 1983-07-08 1983-08-10 Rolls Royce Air separation and lubricant scavenge apparatus
FR2621970A1 (fr) * 1987-10-20 1989-04-21 Hebert Michel Dispositif d'etancheite dynamique par corps centrifuge
GB9801561D0 (en) * 1998-01-27 1998-03-25 Rolls Royce Plc Hydraulic seal
DE10201055A1 (de) * 2002-01-14 2003-07-24 Rolls Royce Deutschland Hydraulische Dichtungsanordnung
GB0305974D0 (en) * 2003-03-15 2003-04-23 Rolls Royce Plc A seal

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3765688A (en) * 1971-07-19 1973-10-16 Avco Corp High speed shaft centrifuge fluid seal
US5593165A (en) * 1994-09-20 1997-01-14 Allison Engine Company, Inc. Circumferential flow channel for carbon seal runner cooling
US5984630A (en) * 1997-12-24 1999-11-16 General Electric Company Reduced windage high pressure turbine forward outer seal
US6170832B1 (en) * 1998-03-26 2001-01-09 Hermann H. F. Ernst Fluid ring seal system and method
US6568688B1 (en) * 1999-04-14 2003-05-27 Rolls-Royce Deutschland Ltd & Co Kg Hydraulic seal arrangement, more particularly on a gas turbine

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050230922A1 (en) * 2003-03-15 2005-10-20 Maguire Alan R Seal
US20070025835A1 (en) * 2005-06-22 2007-02-01 Honeywell International, Inc. Internally-cooled seal housing for turbine engine
US7410341B2 (en) 2005-06-22 2008-08-12 Honeywell International, Inc. Internally-cooled seal housing for turbine engine
US20090238691A1 (en) * 2006-11-28 2009-09-24 Purdey Matthew J Hydraulic Seal for a turbocharger
US8075251B2 (en) * 2006-11-28 2011-12-13 Cummins Turbo Technologies Limited Hydraulic seal for a turbocharger
US20130078091A1 (en) * 2011-09-28 2013-03-28 Rolls-Royce Plc Sealing arrangement
JP2016521823A (ja) * 2013-06-12 2016-07-25 スネクマ 高圧タービンのためのトラニオン、およびこのようなトラニオンを含むターボジェットエンジン
US10526907B2 (en) 2013-06-13 2020-01-07 Pratt & Whitney Canada Corp. Internally cooled seal runner
US9631508B2 (en) 2013-06-13 2017-04-25 Pratt & Whitney Canada Corp. Internally cooled seal runner
WO2015094539A1 (fr) 2013-12-16 2015-06-25 United Technologies Corporation Palier de transfert pour réacteur à double flux à réducteur
EP3084180A4 (fr) * 2013-12-16 2017-01-11 United Technologies Corporation Palier de transfert pour réacteur à double flux à réducteur
US10605352B2 (en) 2013-12-16 2020-03-31 United Technologies Corporation Transfer bearing for geared turbofan
US10077830B2 (en) 2013-12-16 2018-09-18 United Technologies Corporation Transfer bearing for geared turbofan
US9453535B2 (en) * 2014-01-06 2016-09-27 Hamilton Sundstrand Corporation Oil retention and delivery system for a bearing
US9932899B2 (en) 2014-03-28 2018-04-03 Honda Motor Co., Ltd. Bearing lubricating structure for gas turbine engine
JP2015190376A (ja) * 2014-03-28 2015-11-02 本田技研工業株式会社 ガスタービンエンジンのベアリング潤滑構造
US10400787B2 (en) * 2014-05-30 2019-09-03 Nuovo Pignone Srl Sealing device for turbomachines
JP2017526847A (ja) * 2014-09-05 2017-09-14 サフラン・エアクラフト・エンジンズ ターボマシンシャフト
US20160348792A1 (en) * 2015-05-26 2016-12-01 Pratt & Whitney Canada Corp. Internally cooled seal runner and method of cooling seal runner of a gas turbine engine
US10753219B2 (en) * 2015-05-26 2020-08-25 Pratt & Whitney Canada Corp. Internally cooled seal runner and method of cooling seal runner of a gas turbine engine
US20170370288A1 (en) * 2016-06-28 2017-12-28 Rolls-Royce Deutschland Ltd & Co Kg Oil distribution system and turbomachine with an oil distribution system
US11203948B2 (en) * 2019-09-06 2021-12-21 Pratt & Whitney Canada Corp. Seal runner and method
US12000299B1 (en) * 2023-08-25 2024-06-04 Rolls-Royce Corporation Centrifugally operated oil shield for lubrication flow control

Also Published As

Publication number Publication date
GB0305974D0 (en) 2003-04-23
EP1460319B1 (fr) 2006-04-19
US20050230922A1 (en) 2005-10-20
EP1460319A1 (fr) 2004-09-22
DE602004000658D1 (de) 2006-05-24
DE602004000658T2 (de) 2006-09-14

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STCB Information on status: application discontinuation

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