GB2420602A - A non-contacting sealing device for a rotor shaft bearing - Google Patents

A non-contacting sealing device for a rotor shaft bearing Download PDF

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Publication number
GB2420602A
GB2420602A GB0523192A GB0523192A GB2420602A GB 2420602 A GB2420602 A GB 2420602A GB 0523192 A GB0523192 A GB 0523192A GB 0523192 A GB0523192 A GB 0523192A GB 2420602 A GB2420602 A GB 2420602A
Authority
GB
United Kingdom
Prior art keywords
housing
oil
rotor shaft
sealing device
seal
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.)
Granted
Application number
GB0523192A
Other versions
GB2420602B (en
GB0523192D0 (en
Inventor
Klaus Naegler
Ferdinand Werdecker
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.)
MAN B&W Diesel GmbH
Original Assignee
MAN B&W Diesel GmbH
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 MAN B&W Diesel GmbH filed Critical MAN B&W Diesel GmbH
Publication of GB0523192D0 publication Critical patent/GB0523192D0/en
Publication of GB2420602A publication Critical patent/GB2420602A/en
Application granted granted Critical
Publication of GB2420602B publication Critical patent/GB2420602B/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • 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
    • F01D25/186—Sealing means for sliding contact bearing
    • 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
    • F16C33/72—Sealings
    • F16C33/76—Sealings of ball or roller bearings
    • F16C33/80—Labyrinth sealings
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/10—Shaft sealings
    • 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
    • F16C33/72—Sealings
    • F16C33/74—Sealings of sliding-contact bearings
    • 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
    • F16J15/164—Sealings between relatively-moving surfaces the sealing action depending on movements; pressure difference, temperature or presence of leaking fluid
    • 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
    • F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
    • 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
    • F16J15/44—Free-space packings
    • 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
    • F16J15/44—Free-space packings
    • F16J15/447—Labyrinth packings
    • F16J15/4472—Labyrinth packings with axial path
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • F16C2360/24—Turbochargers

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Sealing Of Bearings (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Sealing Devices (AREA)

Abstract

It is desirable to improve the tightness of a sealing device for a bearing of a rotor shaft 1 that is lubricated in particular when at a standstill, the sealing device sealing a bearing housing 2, in particular of an exhaust gas turbocharger, in the axial direction with respect to lubricant. On the rotor shaft 1 a first seal 11 in the form of a gap, a labyrinth or a piston ring 11 and a second seal 12 in the form of a narrow gap 33or a labyrinth between them enclose an oil-drain passage 13, 14 that extends annularly around the circumference of the rotor shaft 1. The sealing device includes a first oil-drain groove 13 on the housing side and a second oil-drain groove 14 arranged in the same axial position on the shaft side, and provided in the oil-drain passage 13, 14 there is an annular sealing web 15 that projects with one end in a radial direction of the rotor shaft 1 into the annular oil-drain passage 13, 14 and creates a barrier acting in the axial direction for lubricant penetrating into the oil-drain passage.

Description

Sealing device for a rotor shaft bearing The invention relates to a
sealing device for a rotor- shaft bearing, in particular one that is lubricated when at a standstill. The sealing device seals a bearing housing in the axial direction with respect to a lubricant that is supplied and is relevant to the case of an exhaust gas turbocharger with a rotor shaft, which is guided at one end in a turbine housing in a housing bore and bears a turbine wheel, and is guided at the other end in a compressor housing in a housing bore and bears a compressor wheel. The device can be applied within a bearing arrangement of the rotor shaft that is on the turbine-housing side and/or a bearing arrangement that is on the compressor-housing side and seals the turbine housing and/or the compressor housing with respect to a lubricant that issues from a central bearing housing between the turbine housing and the compressor housing and is supplied to the bearing arrangement on the turbine-housing side and/or the compressor-housing side.
Such sealing devices, that is, shaft seals of the kind mentioned, have been known for a long time and inter alia are used to prevent exhaust gas, for example, from flowing out of the turbine housing by way of unavoidable leakage points or instances of bearing clearance, that is, minimum gaps between the bearing housing or bearing body and the shaft, into the bearing housing, and/or to prevent air that is taken in by suction in the case of comparatively high speeds and high boost pressure, or the gas-air-mixture in the case of a gas engine, from flowing out of the compressor housing by way of the sealing device on the compressor side into the bearing housing.
Moreover, as is known a situation is also to be prevented where at low boost pressures and high speeds oil- containing air/exhaust gas mixture flows out of the respective bearing housing in the direction of the turbine housing and/or compressor housing and is supplied to the internal combustion engine.
The sealing device can be a labyrinth seal or a piston ring that is used in this way. DE 25 13 582 02 for example describes a shaft seal in the shaft-sealing housing of an exhaust gas turbocharger, which is arranged between a turbine-housing portion for higher pressure and a turbinehousing portion for lower pressure and through which a working means leakage flow (fluid) flows axially.
This shaft seal forms a labyrinth with constrictions arranged one after the other in the direction of flow of the fluid and enforcing repeat deflection of the fluid.
The labyrinth can, as is known, also be realized by means of a piston ring that is provided in the bearing housing or bearing body and dips, for example, into a groove of the rotor shaft.
Such sealing devices have had the disadvantage hitherto that lubricating oil is sucked out of the central bearing housing during the re- or prelubricating process in particular in connection with a suction draught (low pressure) in the turbine- and compressor-flow chamber.
This can result in considerable damage to the point of total damage of the exhaust gas Lurbocharger.
The object of the present invention is therefore to improve the tightness of a sealing device of the kind described by way of introduction that can be applied in particular in the case of an exhaust gas turbocharger with a rotor shaft, as likewise described by way of introduction, in particular when the rotor shaft is at a standstill.
In embodiments of the invention, which is defined in claim 1, in order to form the sealing device on the rotor shaft a first seal in the form of a gap, a labyrinth or a piston ring and a second seal in the form of a narrow gap or a labyrinth between them enclose an oil-drain passage that extends annularly around the circumference of the rotor shaft and is made up of an oil-drain groove on the housing side and an oil-drain groove arranged in the same axial position on the shaft side. In the oil-drain passage there is an annular sealing web that projects with one end in the radial direction freely into the annular oil-drain passage and represents a barrier acting in an axial direction for lubricant penetrating into the oil-drain passage.
In this way, during the re- or pre-lubricating operation in particular in connection with suction draught (low pressure), lubricating oil coming out of the bearing housing through the second seal is prevented from reaching the first seal by way of the oil-drain passage.
An improvement in the oil-tightness is thus achieved at standstill so that no leakage can occur under the operating conditions that are to be expected.
In a particularly advantageous way the sealing web in the oil-drain groove on the shaft side is pre-formed on the rotor shaft and its height up to the radially outward end is at the most in alignment with the housing bore or shorter. The sealing web can, however, also be pre- formed in the oil-drain groove on the housing side, in which case then its height as far as the radially inward end extends at the most up to alignment with the housing bore or just shorter.
Furthermore, the second seal is advantageously realized in the form of a wall that delimits the oil-drain groove on the shaft side and is shortened in the radially outward direction with respect to the housing bore, and of a wall that is located in the same axial position in relation thereto, delimits the oil-drain groove on the housing side arid is lengthened in a corresponding manner radially inwardly with respect to the housing bore, with both walls enclosing a gap so that the free end of the sealing web covers this gap in the radial direction.
This means that the housing bore at the axial position of the second seal has a smaller diameter than the diameter that the rotor shaft with the pre-formed sealing web achieves.
It is not important whether the sealing web and the walls are separate components or whether they are formed as parts of the housing or rotor shaft that are turned or milled thereon.
So that advantageously in the case of the application of the exhaust gas turbocharger it is guaranteed that the lubricant, that is, oil, can run around the circumference of the annular oil-drain groove and can run off by way of a lower tap, the second seal is arranged in the axial direction between the central bearing housing and the first seal of the bearing arrangement on the turbine- housing side and/or between the central bearing housing and the first seal of the bearing arrangement on the compressor side.
An embodiment of the invention as applied to an exhaust gas turbocharger will now be explained with reference to the attached drawings, in which: Figure 1 shows an axial section through the important portions of an exhaust gas turbocharger; and Figure 2 shows a detail representation X in accordance with Figure 1 of a sealing device in accordance with the invention of the rotor shaft within a bearing arrangement on the turbinehousing side.
As Figure 1 shows, an exhaust gas turbocharger has in the usual way a turbine housing 2 and a compressor housing 5 connected to it, into which housings a rotor shaft 1 is introduced. The turbine housing 2 has a substantially annular supply passage 28 for exhaust gas in order to supply exhaust gas from an internal combustion engine to the turbine wheel 4. A compressor wheel 7 that sits on the rotor shaft 1 at the other end is driven by way of the rotor shaft 1 in this way. This compressor wheel 7 takes in air by suction by way of a supply passage 29 surrounding it, compresses the air and blows it out again.
The rotor shaft 1 is guided through a housing bore 3 in the turbine housing 2, where the turbine wheel 4 is secured at its end. The bearings 19, 20 of the rotor shaft 1, to which lubricant is fed with excess pressure by way of a vertical oil-infeed connection piece 26 and oilinfeed bores 27 originating therefrom, are as a rule located in a central bearing housing 10 between the turbine housing 2 and the compressor housing 5.
In order to prevent a situation from occurring where this lubricant from the central bearing housing 10 reaches the turbine housing 2, for example by way of the bearing clearance between a bearing body 19, a bearing bush 20 and the rotor shaft 1, the sealing device that is described in the following with reference to Figure 2 is provided.
A sealing device, for example within a bearing arrangement on the turbinehousing side (a sealing device of a bearing arrangement on the compressorhousing side would be configured in a similar way), comprises a first seal 11 and a second seal 12 arranged between a housing wall of the turbine housing 2 and a radial bearing 19, 20 of the rotor shaft. The radial bearing comprises, as is known, a bearing body 19 of the central bearing housing 10 that is connected to the rotor shaft 1 by means of a bearing bush 20. Provided in the axial direction of the rotor shaft 1 between the bearing body 19 and the turbine housing 2 there is an interior space 21, following on from which in the direction of the turbine housing 2 there is the second seal 12, followed by an oil-drain groove 13 on the housing side which together with an oil-drain groove 14 on the shaft side forms an oil-drain passage that extends annularly over the circumference of the rotor shaft 1. Arranged in the oil-drain passage there is an annular sealing web 15 that projects with one end or edge in the radial direction of the rotor shaft 1 from the base of the shaft-side groove 14 freely into the housing side annular oil-drain passage 13, and following on from this in the axial direction is the first seal in the form of a piston ring 11 that is applied to the inner wall of the turbine-housing bore 3.
The piston ring 11 is inserted into a groove 18 of the rotor shaft 1 or of a turned portion connected thereto to effect sealing with respect to a fluid which might possibly penetrate. The sealing web 15 is pre-formed on the rotor shaft 1 in the oil-drain groove 14 on the shaft side. Its height in the radially outward direction is realized so that the outer edge is at the most in alignment with the housing bore 3 of the turbine housing 2 or, as it is here, somewhat shorter.
Of course, the sealing web 15 could also be arranged in the oil-drain groove 13 on the housing side and its height as far as the end or edge that is directed radially inwards could be realized so as to be at the most in alignment with the housing bore 3 of the turbine housing 2 or so as to be just shorter. In this connection, respective sealing webs in the oil-drain groove on the housing side and in the oil-drain groove on the shaft side cooperating together whilst overlapping in the radial direction would also be conceivable.
In order to form the second seal 12, the oil-drain groove 14 on the shaft side is realized with a wall 31 adjacent to the interior space 21 and remote from the turbine wheel 4 and is shorter in the radially outward direction than the continuation of the turbine-housing bore 3, and the oil-drain groove 13 on the housing side is realized with a wall 32 that is remote from the turbine wheel 4 and is lengthened in a corresponding manner radially inwards with respect to the alignment of the turbinehousing bore 3. The two walls 31, 32 enclose a gap 33 so that the free end of the sealing web 15 overlaps this gap in the radial direction in order to prevent as far as possible further conveyance of the lubricant through the gap 33 by way of the oil-drain passage 13, 14 to the first seal 11.
In a preferred manner, the free end of the sealing web 15 is realized so as to be bevelled by, for example, 450 with respect to the line of the respective housing bore 3 or 6 facing the turbine wheel, in order to prevent a drop of a lubricant coming through the gap 33 of the second seal 12, left suspended, for example, at the sealing web 15, from nevertheless still being able to reach the piston ring of the first seal 11 by means of suction draught.
The previously described embodiment is brought into line with the intended manner of assembly, namely in order to introduce the rotor shaft 1 first through the turbine housing 2 and then into the central bearing housing 10 and to mount the compressor wheel 7 in the compressor housing 5 on the rotor-shaft stub. This is the reason why in the exemplary embodiment the height of the sealing web 15 (arrow a) may not project beyond the line of the housing bore (arrow b), why the shortened wall 31 (arrow c) and the lengthened wall 32 (arrow d) delimit a gap 33, and the diameter of the rotor shaft 1 in the turbine housing 2 is larger than the diameter of the rotor shaft 1 in the region of the second seal 12 and this in turn is larger than the diameter of the rotor shaft in the central bearing housing 10 in this embodiment. The sealing web 15 should therefore as far as possible be formed with a substantial height in the radial direction of the rotor shaft 1 in order to cover the gap 33, through which lubricating oil penetrates into the oil-drain passage 13, 14, in the axial direction; however, it may not overlap the line of the housing bore 3 on the turbine side, so that the rotor shaft 1 remains capable of being mounted.

Claims (10)

  1. Claims 1. A sealing device for a rotor-shaft bearing to be lubricated when
    at a standstill, the sealing device sealing a bearing housing in the axial direction with respect to the lubricant, characterised in that on the rotor shaft a first seal (11) in the form of a gap, a labyrinth or a piston ring and a second seal (12) in the form of a narrow gap or a labyrinth between them enclose an oil-drain passage (13, 14) that extends annularly around the circumference of the rotor shaft (1) and is constituted by an oil-drain groove (13) on the housing side and an oildrain groove (14) arranged in the same axial position on the shaft side, and in that provided in the oil-drain passage (13, 14) there is an annular sealing web (15) that projects with one end in a radial direction of the rotor shaft (1) freely into the annular oil-drain passage (13, 14) and represents a barrier acting in the axial direction for lubricant penetrating into the oil-drain passage.
  2. 2. A sealing device according to claim 1, in which the second seal (12) is realized in the form of a wall (31) that delimits the oil-drain groove (14) on the shaft side and is shortened radially outwards with respect to the housing bore (3 and/or 6), and of a wall (32) that is located in the same axial position in relation thereto, delimits the oil-drain groove (13) on the housing side and is lengthened in a corresponding manner radially inwards with respect to the housing bore (3 and/or 6), with both walls (31, 32) enclosing a gap (33) so that the free end of the sealing web (15) covers this gap (33) in the radial direction.
  3. 3. A sealing device according to claim 1 or 2, in which the first seal (11) is a labyrinth seal.
  4. 4. A sealing device according to claim 1 or 2, in which the first seal (11) is in the form of a piston ring (11) that is applied to the inner wall of the housing bore (3 and/or 6)
  5. 5. A sealing device according to claim 4, in which the piston ring (11) is inserted into a groove (18) of the rotor shaft (1) or of a turned portion connected therewith.
  6. 6. A sealing device according to any preceding claim, in which the free end of the sealing web (15) is bevelled in relation to the line of the respective housing bore (3, 6).
  7. 7. An exhaust gas turbocharger including a sealing device according to any preceding claim, in which the rotor shaft (1) guided at one end in a turbine housing (2) in a housing bore (3) bears a turbine wheel (4) and guided at the other end in a compressor housing (5) in a housing bore bears a compressor wheel (7), the sealing device being provided within a bearing arrangement of the rotor shaft (1) that is on the turbine-housing side and/or within a bearing arrangement of the rotor shaft (1) that is on the compressor-housing side in order to seal the turbine housing (2) and/or the compressor housing (5) with respect to a lubricant that issues from a central bearing housing (10) between the turbine housing (2) and the compressor housing (5) and is supplied to the bearing arrangement on the turbine- housing side and/or the compressor-housing side.
  8. 8. A turbocharger according to claim 7, in which the sealing web (15) is pre-formed in the oil-drain groove (14) on the shaft side on the rotor shaft (1) and its height as far as the free end directed radially outwards is realized so as to be at the most in alignment with the housing bore (3, 6), in particular of the turbine housing (2) and/or compressor housing (5), or so as to be shorter.
  9. 9. A turbocharger according to claim 7, in which the sealing web (15) is pre-formed on the housing side of the oil-drain groove (13) and its extent in the radially inward direction is realized so as to be at the most in alignment with the housing bore (3, 6) of the turbine housing (2) and/or compressor housing (5) or so as to be shorter.
  10. 10. A sealing arrangement substantially as described herewith with reference to the accompanying drawings.
GB0523192A 2004-11-17 2005-11-14 Sealing device for a rotor shaft bearing Expired - Fee Related GB2420602B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102004055429A DE102004055429B3 (en) 2004-11-17 2004-11-17 Sealing device for a particularly lubricated at standstill bearing a rotor shaft

Publications (3)

Publication Number Publication Date
GB0523192D0 GB0523192D0 (en) 2005-12-21
GB2420602A true GB2420602A (en) 2006-05-31
GB2420602B GB2420602B (en) 2009-03-18

Family

ID=35516901

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0523192A Expired - Fee Related GB2420602B (en) 2004-11-17 2005-11-14 Sealing device for a rotor shaft bearing

Country Status (7)

Country Link
JP (1) JP2006145034A (en)
KR (1) KR20060055404A (en)
CN (1) CN1776264B (en)
CH (1) CH698162B1 (en)
DE (1) DE102004055429B3 (en)
FR (1) FR2878007B1 (en)
GB (1) GB2420602B (en)

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US20100192571A1 (en) * 2007-06-18 2010-08-05 Continental Automotive Gmbh Turbocharger Having a Turbocharger Housing
US8075251B2 (en) 2006-11-28 2011-12-13 Cummins Turbo Technologies Limited Hydraulic seal for a turbocharger
EP3594552A1 (en) * 2014-05-24 2020-01-15 Garrett Transportation I Inc. Turbocharger

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JP2009167803A (en) * 2008-01-10 2009-07-30 Jtekt Corp Supercharger
DE102010003796A1 (en) * 2010-04-09 2011-10-13 Abb Turbo Systems Ag shaft seal
US20130106061A1 (en) * 2011-10-28 2013-05-02 General Electric Company High temperature seal system
CN102996650B (en) * 2012-11-26 2015-01-07 北京七星华创电子股份有限公司 Gas sealing device for low-speed rotation of main shaft
EP2743460B1 (en) 2012-12-14 2017-04-05 ABB Turbo Systems AG Shaft seal
GB2530699B (en) * 2013-06-28 2016-09-21 Borgwarner Inc Turbocharger compressor-end carbon face seal
JP6097188B2 (en) * 2013-09-25 2017-03-15 三菱重工業株式会社 Turbocharger
FR3020658B1 (en) * 2014-04-30 2020-05-15 Safran Aircraft Engines LUBRICATION OIL RECOVERY HOOD FOR TURBOMACHINE EQUIPMENT
FR3022587B1 (en) * 2014-06-23 2019-03-22 Safran Aircraft Engines DEVICE AND METHOD FOR LUBRICATING A TURBOMACHINE BEARING BEARING
DE102014011849A1 (en) 2014-08-08 2016-02-11 Man Diesel & Turbo Se Shaft seal system and turbocharger
US10196986B2 (en) * 2015-09-04 2019-02-05 General Electric Company Hydrodynamic seals in bearing compartments of gas turbine engines
DE102018106900A1 (en) * 2018-03-22 2019-09-26 Man Energy Solutions Se Turbo compressor
TWI735960B (en) * 2018-09-28 2021-08-11 美商英普羅密封有限責任公司 Shaft seal assembly
DE102019101258A1 (en) 2019-01-18 2020-07-23 Bayerische Motoren Werke Aktiengesellschaft Exhaust gas turbocharger

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CH698162B1 (en) 2009-06-15
KR20060055404A (en) 2006-05-23
CN1776264B (en) 2010-06-16
GB2420602B (en) 2009-03-18
FR2878007B1 (en) 2014-09-12
GB0523192D0 (en) 2005-12-21
FR2878007A1 (en) 2006-05-19
CN1776264A (en) 2006-05-24
JP2006145034A (en) 2006-06-08
DE102004055429B3 (en) 2006-08-10

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