EP1224382A1 - Bearing housing for a turbomachine - Google Patents

Bearing housing for a turbomachine

Info

Publication number
EP1224382A1
EP1224382A1 EP00971984A EP00971984A EP1224382A1 EP 1224382 A1 EP1224382 A1 EP 1224382A1 EP 00971984 A EP00971984 A EP 00971984A EP 00971984 A EP00971984 A EP 00971984A EP 1224382 A1 EP1224382 A1 EP 1224382A1
Authority
EP
European Patent Office
Prior art keywords
space
lubrication
lubricant
buffer
turbomachine
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.)
Withdrawn
Application number
EP00971984A
Other languages
German (de)
French (fr)
Inventor
Anatoly Rakhmailov
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.)
ALM Development Inc
Original Assignee
ALM Development Inc
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 ALM Development Inc filed Critical ALM Development Inc
Publication of EP1224382A1 publication Critical patent/EP1224382A1/en
Withdrawn legal-status Critical Current

Links

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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/02—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows
    • F16C19/14—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load
    • F16C19/18—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with two or more rows of balls
    • F16C19/181—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with two or more rows of balls with angular contact
    • F16C19/183—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with two or more rows of balls with angular contact with two rows at opposite angles
    • F16C19/184—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with two or more rows of balls with angular contact with two rows at opposite angles in O-arrangement
    • 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

Definitions

  • the invention relates to the lubrication of turbomachines, and more specifically to a bearing lubrication system for a gas turbine engine.
  • Lubricant is supplied to the lubrication space through, e.g., a mist forming nozzle, and the lubricant is removed from the lubrication space through a drain by gravity or by means of a scavenging pumps.
  • the lubrication system of this type usually requires a separator to separate oil from the air, because the lubricant contains air and gas owing to the pressure fluctuations in the fluid space. The lubricant is recovered from the bottom of the separator, and the air escapes through an exhaust duct.
  • the gage pressure which normally prevails outside the lubrication chamber suddenly drops for a certain time period below the pressure in the lubrication chamber. This will cause lubricant to escape from the lubrication space, resulting in the lubricant entering the fluid space of the gas turbine engine.
  • the negative impact of such lubricant leak into the fluid space of a gas turbine engine is well known to those skilled in the art.
  • the lubricant tank level will drop substantially, and the system may lack lubricant.
  • a prior art depressurization device disclosed in US Patent No. 5,429,208 to Christian Largiller et ⁇ l. was aimed at eliminating this disadvantage.
  • the depressurization device is made in the form of a jet nozzle which communicates with the lubrication space.
  • the jet nozzle ejects air (with lubricant) from the lubrication space using air from the engine compressor as a carrier fluid.
  • a sensor in a control circuit sends a signal to a valve to open the jet nozzle to the compressor.
  • the excessive air (with lubricant) is removed from the lubrication space to establish a reduced pressure in the lubrication space.
  • Prior art bearing lubrication systems such as that described above require lubricant/air separators because the lubrication chamber is pressurized.
  • the lubricant/oil separators are devices that have to be manufactured and installed on the gas turbine engine.
  • the lubricant/air separators consume a certain amount of the engine output power, thus lowering engine efficiency.
  • the depressurization of the lubrication space during engine deceleration requires the provision of a jet nozzle or an evacuation pump and a control system with a sensor and controls to activate the depressurization system.
  • Apart from the added cost of these devices their use in gas turbine engine impairs its reliability. These devices require periodic checks and maintenance. A malfunction of one of these devices may result in lubricant entering the fluid space of the gas turbine engine.
  • Further object of the invention is to provide a bearing lubrication system for a turbomachine which requires minimum maintenance.
  • Still another object of the invention to provide a bearing lubrication system for a turbomachine which would be simple in design and easy to manufacture.
  • a bearing lubrication system for a turbomachine having a lubrication chamber that defines a lubrication space surrounding the bearings, lubricant feeding devices for supplying lubricant to the lubrication space, a lubricant removing device for removing lubricant from the lubrication space, and a buffer case surrounding the lubrication chamber, located in the fluid space of the turbomachine. and defining a buffer space communicating with the atmosphere. Shaft contact seals are provided between the buffer case and the fluid space and shaft seals are provided between the buffer space and the lubrication space.
  • Fig. 1 is a schematic sectional view that shows a bearing lubrication system for a turbomachine according to the invention
  • Fig. 2 is another embodiment of a bearing lubrication system for a turbomachine according to the invention, which shows details of sealing.
  • a turbomachine 10 which can be, among other machines, a gas turbine engine, has a fluid space 14 communicating with the gas turbine engine flow duct in which a gas turbine 12 and a compressor 15 are installed. Turbine 14 and compressor 15 are installed on a shaft 16. Shaft 16 is supported by bearings 18 and 20 which are installed in a lubrication chamber 22. Lubrication chamber 22 is made as a closed chamber in a turbomachine casing 23. The lubrication chamber 22 has a lubrication space shown at LS which is used to lubricate bearings 18 and 22. Devices 24 feed lubricant into the lubrication space LS.
  • Lubrication chamber 22 has a drain 26 to remove from lubrication space LS lubricant splashing from bearings 18 and 20. Drain 26 may be connected to a lubricant tank (not shown) to remove lubricant by gravity, or it may be connected to a scavenging pump (not shown) which removes lubricant and pumps it back to the lubricant tank.
  • a lubricant tank not shown
  • a scavenging pump not shown
  • a buffer case 28 is provided in fluid space 12, and this buffer case is surrounded by fluid space 12.
  • Buffer case 28 surrounds the lubrication chamber 22 and communicates with the atmosphere through an opening 30 as shown by arrow A. It will be understood that lubrication chamber 22 will be under the pressure that establishes in the interior or buffer space BF of buffer case 28 (which is about equal to the atmospheric pressure). The pressure in lubrication chamber 22 will never be higher than atmospheric pressure.
  • Buffer case 28 is separated from fluid space 12 of gas turbine engine 10 by contact seals 32 and 34.
  • Contact seals 32 and 34 allow only a minimal leak from fluid space 12 into buffer space BS if the fluid pressure in the fluid space is greater than atmospheric pressure, or they allow only a minimal leak of air or gas from buffer space BS into fluid space 12. In any case, the pressure in buffer space BS will always be about equal to atmospheric pressure.
  • the lubrication space LS of lubrication chamber 22 is separated from buffer space BS of buffer case 28 by seals 36 and 38. Seals 36 and 38 are provided to prevent oil from escaping from lubrication space LS 22 into buffer space BS 22 from which oil might escape into the atmosphere. As shown in Fig. 1, all contact seals 32 and 36 are made as brush seals.
  • Brush seals are known in the art. As an example, the construction of a brush seal is disclosed in U.S. Patent 5,201,530. Brush seals 32 and 34 ensure a minor gas leakage from fluid space 12 into buffer space BS of buffer case 22. Any leakage will escape to the atmosphere, so with any leakage flow through brush seals 32 and 34, the pressure in buffer space BS will be about atmospheric pressure.
  • Fig. 2 which illustrates another embodiment of the invention in which the same parts are shown at the same reference numerals as in Fig. 1 with the addition of 100, the construction of the lubrication system is the same as that shown in Fig. 1.
  • the shaft contact seals 132 and 134 are made as brush seals as shown in the left- hand part and in the right hand part of the drawing.
  • Shaft seals 136 separating the lubrication space LS of lubrication chamber 122 from buffer space BS of buffer case 128 may be made as the contact seals (as shown in left hand part of the drawing in Fig. 2).
  • shaft seals 138 separating the lubrication space LS of the lubrication chamber 122 from the buffer space BS of the buffer case 128 may be made as labyrinth seals (as shown in the right hand part of the drawing in Fig. 2) or any other type of seal.
  • Their main function is to minimize lubricant flow from lubrication space LS into buffer space BS.
  • the invention prevents lubricant from escaping into the fluid space of a turbomachine or into the atmosphere without using complicated mechanical devices and control systems.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A bearing lubrication system for a turbomachine having a lubrication chamber which defines a lubrication space (LS) surrounding the bearings (18, 20) has lubricant feeding devices (24) for supplying lubricant to the lubrication space (LS), a lubricant removing device (26) for removing lubricant from the lubrication space (LS), and a buffer case (BS) surrounding the lubrication chamber (22), that is located in the fluid space (BS) of the turbomachine, and defines a buffer space communicating with the atmosphere. Shaft contact seals (32, 34) are provided between the buffer case (BS) and the fluid space, and shaft seals (36, 38) are provided between the buffer space (BS) and the lubrication space (LS).

Description

BEARING LUBRICATION SYSTEM FOR A TURBOMACHINE
This application cross-references nine co-pending U.S. patent applications, Serial Nos. 09/161 ,104, 09/161,114, 09/161 ,115 and 09/161,170, all of which were filed on September 25, 1998, and Serial Nos. 09/267,893. 09/267,894, 09/267,895, 09/267,896 and 09/267,897 all of which were filed on March 1 1, 1999. and also four co-pending U.S. provisional patent applications, Serial Nos. 60/159,066. 60/159,065, 60/158,934 and 60/158/935, all of which were filed on October 12, 1999. Each of the above is incorporated by reference herein.
The invention relates to the lubrication of turbomachines, and more specifically to a bearing lubrication system for a gas turbine engine.
Background of the Invention
It is a common practice in gas turbine engines to provide a lubrication chamber surrounding the shaft bearings using seals that separate the interior space, or lubrication space, of the lubrication chamber from the fluid space of the gas turbine engine. Lubricant is supplied to the lubrication space through, e.g., a mist forming nozzle, and the lubricant is removed from the lubrication space through a drain by gravity or by means of a scavenging pumps. The lubrication system of this type usually requires a separator to separate oil from the air, because the lubricant contains air and gas owing to the pressure fluctuations in the fluid space. The lubricant is recovered from the bottom of the separator, and the air escapes through an exhaust duct. If the speed of the gas turbine engine falls below a certain level, the gage pressure which normally prevails outside the lubrication chamber suddenly drops for a certain time period below the pressure in the lubrication chamber. This will cause lubricant to escape from the lubrication space, resulting in the lubricant entering the fluid space of the gas turbine engine. The negative impact of such lubricant leak into the fluid space of a gas turbine engine is well known to those skilled in the art. In addition, if a large quantity of lubricant escapes from the lubrication system, the lubricant tank level will drop substantially, and the system may lack lubricant.
A prior art depressurization device disclosed in US Patent No. 5,429,208 to Christian Largiller et αl. was aimed at eliminating this disadvantage. The depressurization device is made in the form of a jet nozzle which communicates with the lubrication space. The jet nozzle ejects air (with lubricant) from the lubrication space using air from the engine compressor as a carrier fluid. When the speed of the gas turbine engine drops below a certain level, and there is a danger of the pressure in the fluid space of the engine falling below the pressure in the lubrication space, a sensor in a control circuit sends a signal to a valve to open the jet nozzle to the compressor. As a result, the excessive air (with lubricant) is removed from the lubrication space to establish a reduced pressure in the lubrication space.
Prior art bearing lubrication systems such as that described above require lubricant/air separators because the lubrication chamber is pressurized. The lubricant/oil separators are devices that have to be manufactured and installed on the gas turbine engine. In addition, the lubricant/air separators consume a certain amount of the engine output power, thus lowering engine efficiency. The depressurization of the lubrication space during engine deceleration requires the provision of a jet nozzle or an evacuation pump and a control system with a sensor and controls to activate the depressurization system. Apart from the added cost of these devices, their use in gas turbine engine impairs its reliability. These devices require periodic checks and maintenance. A malfunction of one of these devices may result in lubricant entering the fluid space of the gas turbine engine.
It should be added that even a small quantity of lubricant which inevitably escapes from the lubrication system with air leaving the lubricant/air separator (because even the best separators cannot ensure the 100% separation), as well as the lubricant that escapes from the jet nozzle is irrecoverably lost. Moreover, the discharge of the lubricant into the open air has an adverse effect on the environment.
It is thus an object of the invention to provide a bearing lubrication system for a turbomachine which would prevent pressure from increasing in the lubrication space. Another object of the invention is to provide a bearing lubrication system for a turbomachine which would be reliable in operation.
Further object of the invention is to provide a bearing lubrication system for a turbomachine which requires minimum maintenance.
Still another object of the invention to provide a bearing lubrication system for a turbomachine which would be simple in design and easy to manufacture.
One more, it is an object of the invention to prevent lubricant from being irrecoverably lost.
Finally, it is an object of the invention to prevent the adverse environmental effect of lubricant. Summary of the Invention
The above and other objects of the invention are accomplished by providing a bearing lubrication system for a turbomachine having a lubrication chamber that defines a lubrication space surrounding the bearings, lubricant feeding devices for supplying lubricant to the lubrication space, a lubricant removing device for removing lubricant from the lubrication space, and a buffer case surrounding the lubrication chamber, located in the fluid space of the turbomachine. and defining a buffer space communicating with the atmosphere. Shaft contact seals are provided between the buffer case and the fluid space and shaft seals are provided between the buffer space and the lubrication space. These and other objects and advantages of the invention will become apparent from the following detailed description of preferred embodiments of a bearing lubrication system for a turbomachine, in which:
Brief Description of the Drawings
Fig. 1 is a schematic sectional view that shows a bearing lubrication system for a turbomachine according to the invention;
Fig. 2 is another embodiment of a bearing lubrication system for a turbomachine according to the invention, which shows details of sealing.
Detailed Description of the Drawings
In Fig. 1, a turbomachine 10, which can be, among other machines, a gas turbine engine, has a fluid space 14 communicating with the gas turbine engine flow duct in which a gas turbine 12 and a compressor 15 are installed. Turbine 14 and compressor 15 are installed on a shaft 16. Shaft 16 is supported by bearings 18 and 20 which are installed in a lubrication chamber 22. Lubrication chamber 22 is made as a closed chamber in a turbomachine casing 23. The lubrication chamber 22 has a lubrication space shown at LS which is used to lubricate bearings 18 and 22. Devices 24 feed lubricant into the lubrication space LS. These devices may be spray nozzles for generating a lubricant mist in the lubrication space LS in proximity to bearings 18 and 20. Lubrication chamber 22 has a drain 26 to remove from lubrication space LS lubricant splashing from bearings 18 and 20. Drain 26 may be connected to a lubricant tank (not shown) to remove lubricant by gravity, or it may be connected to a scavenging pump (not shown) which removes lubricant and pumps it back to the lubricant tank. The systems for lubricant supply and removal are well known to those skilled in the art are not discussed in detail here. These systems would normally use lubricant/air separators to separate lubricant from the air and gas that would be present in the lubricant leaving the lubrication chamber in the conventional lubrication systems. Such lubricant/air separators are not used in the bearing lubrication system of a turbomachine according to the invention.
A buffer case 28 is provided in fluid space 12, and this buffer case is surrounded by fluid space 12. Buffer case 28 surrounds the lubrication chamber 22 and communicates with the atmosphere through an opening 30 as shown by arrow A. It will be understood that lubrication chamber 22 will be under the pressure that establishes in the interior or buffer space BF of buffer case 28 (which is about equal to the atmospheric pressure). The pressure in lubrication chamber 22 will never be higher than atmospheric pressure.
Buffer case 28 is separated from fluid space 12 of gas turbine engine 10 by contact seals 32 and 34. Contact seals 32 and 34 allow only a minimal leak from fluid space 12 into buffer space BS if the fluid pressure in the fluid space is greater than atmospheric pressure, or they allow only a minimal leak of air or gas from buffer space BS into fluid space 12. In any case, the pressure in buffer space BS will always be about equal to atmospheric pressure. The lubrication space LS of lubrication chamber 22 is separated from buffer space BS of buffer case 28 by seals 36 and 38. Seals 36 and 38 are provided to prevent oil from escaping from lubrication space LS 22 into buffer space BS 22 from which oil might escape into the atmosphere. As shown in Fig. 1, all contact seals 32 and 36 are made as brush seals. Brush seals are known in the art. As an example, the construction of a brush seal is disclosed in U.S. Patent 5,201,530. Brush seals 32 and 34 ensure a minor gas leakage from fluid space 12 into buffer space BS of buffer case 22. Any leakage will escape to the atmosphere, so with any leakage flow through brush seals 32 and 34, the pressure in buffer space BS will be about atmospheric pressure.
In Fig. 2, which illustrates another embodiment of the invention in which the same parts are shown at the same reference numerals as in Fig. 1 with the addition of 100, the construction of the lubrication system is the same as that shown in Fig. 1.
The shaft contact seals 132 and 134 are made as brush seals as shown in the left- hand part and in the right hand part of the drawing. Shaft seals 136 separating the lubrication space LS of lubrication chamber 122 from buffer space BS of buffer case 128 may be made as the contact seals (as shown in left hand part of the drawing in Fig. 2). On the other hand, shaft seals 138 separating the lubrication space LS of the lubrication chamber 122 from the buffer space BS of the buffer case 128 may be made as labyrinth seals (as shown in the right hand part of the drawing in Fig. 2) or any other type of seal. Their main function is to minimize lubricant flow from lubrication space LS into buffer space BS.
It will be apparent from the above description that the invention prevents lubricant from escaping into the fluid space of a turbomachine or into the atmosphere without using complicated mechanical devices and control systems.

Claims

I claim:
1. In a bearing lubrication system for a turbomachine having a fluid space and a shaft installed in bearings:
- a lubrication chamber, said lubrication chamber having a lubrication space surrounding said bearings;
- a lubricant feeding means for supplying lubricant to said lubrication space;
- a lubricant removing means for removing lubricant from said lubrication space:
- a buffer case located in said fluid space having a buffer space communicating with the atmosphere, said buffer case surrounding said lubrication chamber: - shaft contact sealing means provided between said buffer case and said fluid space; and
- shaft sealing means provided between said buffer space and said lubrication space.
2. The bearing lubrication system of claim 1, wherein said shaft contact sealing means comprises brush seals.
3. The bearing lubrication system of claim 1 , wherein said shaft sealing means comprises contact seals.
4. The bearing lubrication system of claim 2, wherein said shaft sealing means comprises contact seals.
EP00971984A 1999-10-12 2000-10-11 Bearing housing for a turbomachine Withdrawn EP1224382A1 (en)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US15892999P 1999-10-12 1999-10-12
US158929P 1999-10-12
US63256500A 2000-08-04 2000-08-04
US632565 2000-08-04
PCT/US2000/026250 WO2001027444A1 (en) 1999-10-12 2000-10-11 Bearing housing for a turbomachine

Publications (1)

Publication Number Publication Date
EP1224382A1 true EP1224382A1 (en) 2002-07-24

Family

ID=26855512

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00971984A Withdrawn EP1224382A1 (en) 1999-10-12 2000-10-11 Bearing housing for a turbomachine

Country Status (7)

Country Link
US (1) US20040003968A1 (en)
EP (1) EP1224382A1 (en)
JP (1) JP2003511618A (en)
KR (1) KR20020044164A (en)
CN (1) CN1399706A (en)
AU (1) AU1071001A (en)
WO (1) WO2001027444A1 (en)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7055303B2 (en) * 2003-12-22 2006-06-06 Pratt & Whitney Canada Corp. Gas turbine engine architecture
BE1015913A3 (en) * 2004-02-23 2005-11-08 Atlas Copco Airpower Nv Machine with improved bearing lubrication.
US7329048B2 (en) 2005-07-19 2008-02-12 Rolls-Royce Corporation Self contained squeeze film damping system
JP4369940B2 (en) * 2006-07-12 2009-11-25 アイシン・エーアイ株式会社 Lubricating structure of rotary shaft oil seal
FR2905414B1 (en) * 2006-08-29 2013-03-01 Snecma DEVICE FOR DRIVING THE ROTOR OF AN AUXILIARY EQUIPMENT OF A TURBOMOTEUR.
EP1947373A1 (en) * 2007-01-19 2008-07-23 ABB Turbo Systems AG Sealing arrangement
US7934871B2 (en) * 2007-03-12 2011-05-03 Jtekt Corporation Double row ball bearing
US20090078508A1 (en) * 2007-09-20 2009-03-26 Honeywell International, Inc. Electric motor driven lubrication supply system shutdown system and method
US7946554B2 (en) * 2008-12-30 2011-05-24 General Electric Company Self-aligning support assembly and method for rotatable cylindrical components
US20100270747A1 (en) * 2009-04-24 2010-10-28 General Electric Company Non-metallic brush seal
FR2957976B1 (en) * 2010-03-26 2013-04-12 Snecma SEALING DEVICE FOR AN OIL ENCLOSURE OF A TURBOJET ENGINE
DE102010003796A1 (en) * 2010-04-09 2011-10-13 Abb Turbo Systems Ag shaft seal
US20130270775A1 (en) * 2012-04-13 2013-10-17 General Electric Company Shaft sealing system for steam turbines
US9010100B2 (en) * 2012-04-30 2015-04-21 Caterpillar Inc. Seal assembly for torque converter
CN102767623A (en) * 2012-07-04 2012-11-07 联优机械(常熟)有限公司 External work output transmission and connection device
CN102767402A (en) * 2012-07-04 2012-11-07 联优机械(常熟)有限公司 Connecting shaft structure of external work output connection device of turbine expansion engine
US9677423B2 (en) * 2014-06-20 2017-06-13 Solar Turbines Incorporated Compressor aft hub sealing system
CN104791132A (en) * 2015-03-31 2015-07-22 奇瑞汽车股份有限公司 Automatic lubrication and cooling type turbojet engine
CN104847500B (en) * 2015-04-30 2016-08-17 中国科学院工程热物理研究所 Lubricant passage way system, bearing cavity configuration, gas-turbine unit altogether
ITMI20150661A1 (en) * 2015-05-12 2016-11-12 Nuovo Pignone Tecnologie Srl CONTAINMENT SLEEVE OF A BEARING OF A TURBOMACHINE, AND TURBOMACHINE EQUIPPED WITH SUCH SLEEVE
US10138942B2 (en) 2017-01-11 2018-11-27 Aurora Flight Sciences Corporation Passive fault-tolerant shaft seal configuration
DE102020203204A1 (en) * 2020-03-12 2021-09-16 Robert Bosch Gesellschaft mit beschränkter Haftung Bearing arrangement for a shaft of a turbo compressor
CN112228224B (en) * 2020-10-14 2021-04-27 上海尚实能源科技有限公司 Self-pressurization sealing pressure oil return bearing cavity of gas turbine engine

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH266731A (en) * 1948-08-11 1950-02-15 Siegfried Keller & Co Device to avoid loss of lubricant in high-speed turbo machines with a flying rotor arrangement.
DE897902C (en) * 1951-06-02 1953-11-26 Eberspaecher J Securing the lubricant space against oil loss in high-speed flow machines by venting
DE867634C (en) * 1951-07-31 1953-02-19 Kloeckner Humboldt Deutz Ag Labyrinth seal
US3527054A (en) * 1969-01-23 1970-09-08 Gen Electric Pressurization of lubrication sumps in gas turbine engines
US4046223A (en) * 1975-10-15 1977-09-06 General Electric Company Bearing sump cooling arrangement
DE3482915D1 (en) * 1983-05-31 1990-09-13 United Technologies Corp PROTECTION SYSTEM FOR STORAGE CHAMBER.
DE3817617A1 (en) * 1988-05-25 1989-07-20 Daimler Benz Ag Exhaust turbocharger for an internal combustion engine
US5201530A (en) 1991-10-18 1993-04-13 United Technologies Corporation Multi-layered brush seal
FR2705733B1 (en) 1993-05-25 1995-06-30 Snecma Device for depressurizing the lubrication chambers surrounding the bearings of a turbomachine.
US5415478A (en) * 1994-05-17 1995-05-16 Pratt & Whitney Canada, Inc. Annular bearing compartment
US5597167A (en) * 1994-09-28 1997-01-28 United Technologies Corporation Brush seal with fool proofing and anti-rotation tab
DE19524732A1 (en) * 1995-07-07 1997-01-09 Bmw Rolls Royce Gmbh Bearing chamber arrangement for a gas turbine shaft
EP0967424B1 (en) * 1998-06-26 2004-03-17 Techspace aero Turbomachine arrangement with a sealing arrangement
US6234746B1 (en) * 1999-08-04 2001-05-22 General Electric Co. Apparatus and methods for cooling rotary components in a turbine
US6331006B1 (en) * 2000-01-25 2001-12-18 General Electric Company Brush seal mounting in supporting groove using flat spring with bifurcated end

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO0127444A1 *

Also Published As

Publication number Publication date
WO2001027444A9 (en) 2002-10-03
AU1071001A (en) 2001-04-23
JP2003511618A (en) 2003-03-25
KR20020044164A (en) 2002-06-14
US20040003968A1 (en) 2004-01-08
CN1399706A (en) 2003-02-26
WO2001027444A1 (en) 2001-04-19

Similar Documents

Publication Publication Date Title
US20040003968A1 (en) Bearing lubrication system for a turbomachine
US5429208A (en) Depressurization device for the bearing lubricating chambers of a turbomachine
US4669263A (en) High-speed generator for a gas turbine engine
US6470666B1 (en) Methods and systems for preventing gas turbine engine lube oil leakage
RU2443881C2 (en) Gas turbine engine with stator mounted on gearbox of assembly units
US20100028127A1 (en) Turbine engine lubrication method and system
US8256575B2 (en) Methods and systems for sealing rotating machines
US10502081B2 (en) Turbomachine bearing housing
US20140096533A1 (en) Bearing chamber venting system for an aircraft engine and method for providing a required pressure ratio at bearing chamber seals of an air-sealed bearing chamber
US8915991B2 (en) Fluid separator
JPH07508576A (en) How to drain lubricant from bearing equipment
US6439836B1 (en) Cryogenic turbo-expander
US20080093805A1 (en) Sealing Device For A Rotating Machine
CA2195833C (en) Bearing device for vertical rotating machine
JP2000503199A (en) Rapid depressurization method and equipment in equipment, especially hydrogen cooled generator
US9097180B2 (en) Apparatus and method for reducing oil mist ingestion in a heavy duty gas turbine engine
JPH0972491A (en) Lubricating oil discharge structure for bearing
EP0500153A2 (en) Improved system for recovering the lubricating oil for the bearings of a centrifugal compressor with labyrinth seals
CN108868912B (en) Be applied to airtight oil shelves and turbo generator set of bearing
JP2002349462A (en) Oil injection type screw compressor
JP4503249B2 (en) Isolation of generator bearing housing from generator enclosure and method therefor
JP2542744B2 (en) Oil mist treatment device for bearing lubrication device
KR101886960B1 (en) Apparatus for sealing combined piston rod of air injection system
GB831770A (en) Compressor-turbine unit
KR200239747Y1 (en) Bearing oil curculation unit by using difference of specific gravity and pressure

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20020510

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20030502