US20110129331A1 - System for controlling the thrust affecting a shaft - Google Patents

System for controlling the thrust affecting a shaft Download PDF

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Publication number
US20110129331A1
US20110129331A1 US12/629,326 US62932609A US2011129331A1 US 20110129331 A1 US20110129331 A1 US 20110129331A1 US 62932609 A US62932609 A US 62932609A US 2011129331 A1 US2011129331 A1 US 2011129331A1
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United States
Prior art keywords
chamber
fluid
rotor
valve
port
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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
US12/629,326
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English (en)
Inventor
James E. Olson
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General Electric Co
Original Assignee
General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US12/629,326 priority Critical patent/US20110129331A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: OLSON, JAMES E.
Priority to EP10192797A priority patent/EP2333345A2/en
Priority to JP2010266080A priority patent/JP2011117600A/ja
Priority to KR1020100121903A priority patent/KR20110063352A/ko
Publication of US20110129331A1 publication Critical patent/US20110129331A1/en
Abandoned legal-status Critical Current

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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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/051—Axial thrust balancing
    • F04D29/0516—Axial thrust balancing balancing pistons

Definitions

  • the present invention relates generally to the operation of a turbomachine, and more particularly, to a system for reducing the axial thrust load acting on a turbomachine rotor.
  • Turbomachines such as steam turbines, gas turbines, and the like, operate in a wide variety of applications, including, but not limited to, power generation and propulsion.
  • the turbomachine As the turbomachine operates, the turbomachine rotor experiences high levels of axial thrust (hereinafter “thrust”, “thrust load”, or the like).
  • Thrust axial thrust
  • a known solution for transferring the thrust load from rotating to stationary components employs thrust bearings, which absorb the thrust load without interfering with the rotation of the rotor and associated components.
  • the level of thrust experienced by thrust bearings varies. Differences in rotor manufacture, and changes in flow path pressure, can produce large fluctuations in the thrust load.
  • Some turbomachines employ large thrust bearings to reduce these large fluctuations.
  • Turbomachines tend to operate best when the thrust load remains relatively constant or varies slowly. Large thrust bearings require substantial amounts of fluid and experience large friction losses; which may cause excessive power losses and reduce the overall efficiency of the turbomachine.
  • Some known solutions for addressing those issues transfer a portion of an operating fluid (derived from the turbomachine) to provide a force that opposes the thrust. However, this solution decreases the overall efficiency of the turbomachine.
  • An embodiment of the system may include a chamber that partially surrounds a portion of the rotor (hereinafter “rotor portion”, or the like). This chamber may be substantially filled with a pressurized fluid that does not derive from the turbomachine.
  • the chamber may include a first port and a second port that allow the fluid to flow through the chamber.
  • the system may also include a seal system configured for operatively connecting the chamber and the rotor portion.
  • a controller may determine the position of the rotor portion; and utilize the pressurized fluid to move the rotor in a direction that lessens the thrust load.
  • the system may also include a fluid supply system that provides the external fluid to the chamber and regulates fluid pressure within the chamber.
  • the fluid supply system may comprise: an accumulator, an upper limit switch and a lower limit switch, a supply tank, and a pump. If an upper lower limit switch is triggered, a portion of the fluid within the accumulator may exit the chamber and return to the supply tank. If a lower limit switch is triggered, the pump may replenish the accumulator with the external fluid.
  • the system may contain a pneumatic supply system that provides pneumatic fluid to the chamber.
  • the pneumatic supply system may include at least one pressure-reducing valve for regulating pressure of the pneumatic fluid within the chamber.
  • FIG. 1 is a schematic illustrating an embodiment of a chamber in a turbomachine, in accordance with an embodiment of the present invention.
  • FIG. 2 is a schematic illustrating an embodiment of a chamber in a turbomachine, in accordance with an alternate embodiment of the present invention.
  • FIG. 3 is a block diagram illustrating a system for adjusting the thrust acting on a rotor, in accordance with an embodiment of the present invention.
  • FIG. 4 is a block diagram illustrating a system for adjusting the thrust acting on a rotor, in accordance with an alternate embodiment of the present invention.
  • FIG. 5 is a block diagram illustrating a system using a pneumatic fluid to control the thrust on the rotor, in accordance with an embodiment of the present invention.
  • FIG. 6 is a schematic diagram illustrating a system using a pneumatic fluid to control the thrust on the rotor, in accordance with an alternate embodiment of the present invention.
  • An embodiment of the present invention provides a system for controlling the thrust experienced by a rotor in a turbomachine.
  • This turbomachine may take the form of, but is not limited to, a steam turbine, a heavy-duty gas turbine, an aero-derivative gas turbine, and the like.
  • the system may employ a chamber, enclosing a rotor portion.
  • the chamber may be filled with a pressurized fluid, such as, but not limiting of, a hydraulic fluid.
  • the fluid may derive from a source external to the turbomachine.
  • a seal system may engage the rotor portion, dividing the chamber into separate portions. Each portion may include at least one port and structure to move the fluid into and out of (through) the chamber.
  • a control system may vary the pressure of the fluid within the chamber in order to bias the rotor in a desired direction. This may control the overall thrust, and may prevent large variations in the overall thrust. This may reduce the energy losses in the turbomachine.
  • first, second, etc. may be used herein to describe various elements, these elements should not be limited by these terms. These terms are only used to distinguish one element from another. For example, a first element could be termed a second element, and, similarly, a second element could be termed a first element, without departing from the scope of example embodiments.
  • the term “and/or” includes any, and all, combinations of one or more of the associated listed items.
  • Embodiments of the present invention provide systems that comprise a fluid filled chamber that partially surrounds a portion of a turbomachine rotor.
  • the chamber may be filled with a pressurized fluid that creates a pressure distribution around the rotor portion.
  • the pressure distribution may be considered a force that counteracts the thrust experience by the rotor by impacting the rotor position, possibly moving the rotor and/or lessening the thrust load on the rotor.
  • FIG. 1 illustrates a section of a turbomachine with a chamber 100 that may actively control the overall thrust of the rotor.
  • An embodiment of the chamber 100 may enclose one end of a rotor portion 102 ; and the other portions of the rotor (not illustrated in the FIGS.) may be connected to working components, such as, but not limiting of: the power train, load, or other components associated with the turbomachine.
  • the chamber 100 may be filled with a pressurized fluid deriving from a source independent of the turbomachine.
  • a pressurized fluid deriving from a source independent of the turbomachine.
  • the fluid within the chamber 100 may be separate from the steam path.
  • the operating fluid steam
  • An embodiment of the chamber 100 may also be referred to as a hydraulic chamber; which may be filled with a fluid that may substantially surrounds the rotor portion 102 .
  • the fluid may be a hydraulic fluid.
  • the fluid may be compressed air, or any other hydraulic or pneumatic fluid capable of use in similar applications.
  • the rotor portion 102 rotates within the chamber 100 .
  • a circular rotor portion 103 may extend outward from the rotor portion 102 , substantially filling the chamber 100 .
  • the rotor portion 102 may be a machined structure of the turbomachine rotor.
  • the rotor portion 103 may be a new structure added, via welding or the like, to the turbomachine rotor.
  • a sealing system 104 may seal the inner gap between the rotor portion 102 and the chamber wall; dividing the interior of the chamber 100 into portions 106 and 108 .
  • the operative connection between the seal system 104 and the chamber 100 may be of a conventional design known in the art.
  • Ports 110 and 112 may be located on one side of chamber 100 , and ports 114 and 116 , may be located on the opposite side, as illustrated in FIG. 1 .
  • the ports 110 , 112 , 114 , and 116 may serve to connect the interiors of the two portions 106 and 108 to a fluid supply system. Fluid flow into and out of the portions 106 and 108 may be facilitated via the fluid supply system, which receives the fluid via an external source.
  • the ports 110 and 112 may be located upstream of the sealing system 104 , and the ports 114 and 116 located downstream.
  • the sealing system 104 may establish a seal between a stationary wall and a rotating member, within operating parameters of a pressurized fluid at a pressure of ranging up to approximately 3000 psi.
  • the pressurized fluid may enter the chamber 100 via at least one of the ports 110 , 112 , 114 or 116 .
  • the pressurized fluid may then impact the rotor portion 102 ; possibly with sufficient force to bias the net thrust a desired amount and/or to move the rotor in a desired direction.
  • the external pressure sources connected to ports 110 , 112 , 114 , 116 coupled with normal operating variances, may cause one portion 106 , 108 of the chamber 100 to experience a higher pressure than does the other portion 106 , 108 creating “high pressure” and “low pressure” portions of the chamber 100 .
  • either portion 106 , 108 may function as the “high pressure” portion.
  • FIG. 2 is a schematic illustrating an embodiment of a chamber 200 in a turbomachine, in accordance with an alternate embodiment of the present invention.
  • the chamber 200 may be located intermediately on the rotor.
  • the chamber 200 may be conveniently located on the rotor, such as, but not limiting of, near the center of the rotor 202 .
  • the chamber 200 may allow the ends of the rotor to connect with other components.
  • a rotor portion 203 mounted integral with, the rotor 202 , may be partially enclosed by the chamber 200 .
  • a sealing system 204 may create a seal between the rotor portion 203 and the inner surface, dividing the inner volume of the chamber 200 into separate portions 206 and 208 .
  • each portion may include ports to allow entry or exit of fluid within the chamber 200 .
  • An embodiment of the present invention may include ports 210 , 212 , 214 , and 216 . Aside from the location of the chamber 200 on the rotor, the operation may be identical to the embodiment of the present invention, discussed in relation to FIG. 1 .
  • the high-pressure fluid may be pumped into the upstream end of the rotor portion 102 / 202 to reduce the thrust load.
  • the thrust acting on each portion 106 , 108 // 206 , 208 of the chamber 100 may be controlled independently, as further described in connection with FIGS. 3-6 .
  • the systems described in FIGS. 3-6 may be integrated with the embodiments of the present invention discussed in FIGS. 1 and 2 .
  • FIG. 3 is a block diagram illustrating a system for adjusting the thrust acting on a rotor, in accordance with embodiments of the present invention.
  • the chamber 100 may enclose rotor portion 102 , dividing the chamber 100 into separate portions 106 , 108 on either side of the rotor portion 102 , as described.
  • the system 300 may include pressure sources, such as, but limiting of pressure tanks, 302 , 306 connected to each side of the chamber 100 .
  • the upstream port 112 of the chamber 100 may be connected to pressure tank 302 and the downstream port 116 may be connected to pressure tank 304 .
  • the pressure tanks 302 and 304 may contain a fluid used to control the pressure acting on each portion of the chamber 100 , which may reduce the rotor thrust.
  • the pressure tank 302 may be connected to an accumulator 306 , an upper limit switch 308 , and a lower limit switch 310 , as illustrated.
  • the pressure tank 304 may be connected to an accumulator 312 , an upper limit switch 314 , and a lower limit switch 316 .
  • the accumulators 306 and 312 may be configured to regulate fluid pressure within the chamber 100 .
  • the system 300 may also include a fluid supply system 318 supplying fluid to or receiving fluid from the pressure tanks 302 and 304 .
  • the fluid supply system 318 may be connected to control valves 320 , 322 , 324 , and 326 ; and a pump 328 , to allow entry or exit of fluid.
  • the upstream portion of the chamber 100 may experience greater thrust of the rotor portion 102 than the downstream portion. This pressure difference typically results in leakage of the pressurized fluid from the high-pressure side to the low-pressure side, (illustrated in FIG. 3 as from the left to right).
  • a pump 330 may pump the pressurized fluid from the pressure tank 302 into the upstream port 112 of the chamber 100 .
  • This high-pressure fluid serves to oppose the thrust load, as described.
  • Downstream fluid leakage may result in a constant reduction of the fluid level in the pressure tank 302 .
  • the pump 328 may restore the fluid level to the desired range.
  • the downstream fluid leakage may result in a continuous rise in the pressure tank 304 via a pump 332 .
  • the control valve 326 may allow the extra fluid from the pressure tank 304 to flow into the fluid supply system 318 .
  • the system 300 may include independent pressure controls on either side of the chamber 100 .
  • the lower limit switch 310 and the upper limit switch 314 may operate to maintain the fluid level between selected levels.
  • a variety of control mechanisms and strategies can be employed to accomplish this control result.
  • the system 300 may also include a control system, such as, but not limiting of, a controller 340 to monitor the position of the rotor portion 102 .
  • the controller 340 may control the fluid pressure from the pressure source (pressure tank 302 or 304 ) to the chamber 100 , with the goal of reducing the thrust load to a desirable value and/or positioning the rotor at a desire position.
  • the controller 340 may also drive the activation or deactivation of the control valves ( 320 , 322 , 324 , and 326 ) and the limit switches ( 308 , 310 , 314 , and 316 ), with the goal of maintaining the fluid on either side of the chamber 100 to a desired range.
  • the independent pressure source of an embodiment of the present invention may be connected to each side of the chamber 100 , and varied to manipulate the rotor thrust to a desired range and/or to keep the thrust biased in a desired direction.
  • the system 300 may also include a cooler 334 , which may be connected to the chamber 100 through the ports 110 and 114 .
  • the cooler 334 may absorb the heat associated with the rotor thrust and with the process of pumping high-pressure fluid to counter that thrust. The heat absorption may reduce power losses within the turbomachine, possibly increasing the efficiency.
  • FIG. 4 is a block diagram illustrating a system 400 for adjusting the thrust acting on a rotor portion 102 , in accordance with an alternate embodiment of the present invention.
  • the system 400 may represent a simplified system for providing rotor thrust control.
  • the system 400 includes the chamber 100 .
  • the upstream ports 110 and 112 may be connected to control valves, such as control valves 402 and 404 ; and the downstream ports 114 and 116 of the chamber 100 may be connected to control valves 406 and 408 .
  • the control valves 402 and 406 may operate in tandem, and similarly, control valves 404 and 408 can operate jointly.
  • the system 400 may also include a fluid supply system, for example, but not limiting of a conventional lube oil system 410 that provides oil to the chamber 100 .
  • a pump 412 which may be connected to a downstream port of the lube oil system 410 , may provide constant pressure output to the chamber 100 .
  • a bypass valve 414 may be attached to the lube oil system 410 to vary the pressure exerted by the oil entering the chamber 100 .
  • An embodiment of the present invention may include a bypass valve 414 that may operate from a fully open position to a fully closed position. In the fully closed position, the oil flowing from the lube oil system 410 may exert maximum pressure on the upstream end of the rotor 102 . If the bypass valve 414 operates in the fully open position, the oil may apply minimum pressure on the upstream end of the rotor 102 . Furthermore, the position of the bypass valve 414 may vary the thrust acting on the rotor 102 .
  • An embodiment of the system 400 may operate in multiple modes, one with control valves 402 and 406 activated, and another with control valves 404 and 408 activated.
  • control valves 402 and 406 may be open and the control valves 404 and 408 may be closed.
  • the pump 412 may provide high-pressure fluid to the upstream end of the rotor 102 , through the control valve 402 , to control the thrust.
  • the leakage fluid from the downstream port 114 of the chamber 100 may return to the lube oil system 410 through the control valve 406 .
  • control valves 404 and 408 may be open and the control valves 402 and 406 may be closed.
  • the pump 412 may provide fluid from the lube oil system 410 to the high-pressure side, and the leakage fluid may be returned to the lube oil system 410 via the control valve 408 .
  • a control system 440 may monitor the thrust acting on the chamber 100 and control the operation of the bypass valve 414 to maintain a desired thrust within the chamber 100 .
  • FIG. 5 is a block diagram illustrating a system using a pneumatic fluid to control the thrust on the rotor 102 , in accordance with an embodiment of the present invention.
  • This embodiment may provide the capability to control thrust with a pneumatic fluid, such as, but not limiting of, compressed air.
  • a pneumatic fluid such as, but not limiting of, compressed air.
  • the system the present embodiment may be easily integrated with readily available compressed air system, common in various industrial locations.
  • An embodiment of the system 500 may include the chamber 100 (illustrated in FIG. 1 ), filled with a pneumatic fluid, and partially surrounding the rotor portion 102 .
  • the chamber 100 may be connected to a set of control valves 502 , 504 , 506 , and 508 that allow the pneumatic fluid to enter or exit the chamber 100 .
  • the control valves 502 and 504 may work in tandem and similarly the control valves 506 and 508 may operate in tandem.
  • the pressure on either side of the chamber 100 may be adjusted using reducing valves, such as reducing valves 510 and 512 , which may be configured to regulate the pressure of the pneumatic fluid within the chamber 100 .
  • the system 500 may activate the reducing valve located upstream of the high-pressure side to control the overall thrust.
  • FIG. 5 also illustrates one side of the chamber 100 experiencing high pressure by the pneumatic fluid.
  • This high pressure may trigger the reducing valve 510 , and the corresponding control valves 506 and 508 to activate.
  • the reducing valve 510 may supply high-pressure pneumatic fluid to the upstream port 110 of the chamber 100 via control valve 508 . This may provide an opposing force on the rotor portion 102 to counteract act the thrust acting on the rotor. This may result in leakage flowing from the high-pressure side to the low-pressure side.
  • An embodiment of the system 500 may also include a reducing valve 514 , which may operate in a manner opposite to that of the reducing valves 510 and 512 .
  • the reducing valve 514 located upstream of the control valves 502 and 506 , may function as a backpressure regulator, controlling the pressure acting on the low-pressure side.
  • the reducing valve 514 may be configured for regulating a supply pressure of the pneumatic fluid.
  • the system 500 functions to provide capabilities of controlling the thrust on the upstream end and the downstream end of the rotor 102 .
  • a control system 540 may operate the system 500 to control the thrust acting on the rotor, as described.
  • FIG. 6 is a block diagram illustrating a system 600 using a pneumatic fluid to control the thrust on the rotor, in accordance with an alternate embodiment of the present invention.
  • FIG. 6 illustrates an embodiment of a system 600 using a blocking valve 602 .
  • the blocking valve 602 may be positioned downstream of a lube oil system 604 , and may be connected to upstream of the ports 112 and 116 of the chamber 100 .
  • the lube oil system 604 may be attached to a pump 606 and a bypass valve 608 , as discussed in relation with FIG. 4 .
  • the pump 606 may provide pressurized fluid to the chamber 100 and the bypass valve 608 may serve to regulate the pressure of the pressurized fluid.
  • An embodiment of the blocking valve 602 may include a single valve conventionally used in hydraulic systems and may operate in three positions. As illustrated in FIG. 6 , a solid line and a dotted line illustrate two possible positions. Position 610 may represent a parallel position and 612 may represent a crossed position of the blocking valve 602 respectively. In the position 610 , high-pressure fluid may be supplied to the upstream port 112 through the pump 606 . Subsequently, due to leakage, the fluid can be supplied to the lube oil system 604 through the blocking valve 602 .
  • a controller 640 may monitor the thrust exerted on the rotor and control the position of the blocking valve 602 to manipulate the overall thrust of the turbomachine via the rotor portion 102 .
  • Embodiments of the present invention may provide the benefit of allowing for a smaller thrust bearing.
  • at least two thrust bearings are typically employed to absorb the thrust.
  • an embodiment of the chamber 100 may be employed to keep this thrust biased in the desired direction. Controlling the thrust in the desired direction and reducing the overall net thrust may allow for one thrust bearing.
  • an embodiment of the present invention may eliminate the need of a second thrust bearing and/or reduce the size of the bearing(s) needed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US12/629,326 2009-12-02 2009-12-02 System for controlling the thrust affecting a shaft Abandoned US20110129331A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US12/629,326 US20110129331A1 (en) 2009-12-02 2009-12-02 System for controlling the thrust affecting a shaft
EP10192797A EP2333345A2 (en) 2009-12-02 2010-11-26 System for controlling the thrust affecting a shaft
JP2010266080A JP2011117600A (ja) 2009-12-02 2010-11-30 軸に影響するスラストを制御するシステム
KR1020100121903A KR20110063352A (ko) 2009-12-02 2010-12-02 스러스트 로드 제어 시스템

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/629,326 US20110129331A1 (en) 2009-12-02 2009-12-02 System for controlling the thrust affecting a shaft

Publications (1)

Publication Number Publication Date
US20110129331A1 true US20110129331A1 (en) 2011-06-02

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Family Applications (1)

Application Number Title Priority Date Filing Date
US12/629,326 Abandoned US20110129331A1 (en) 2009-12-02 2009-12-02 System for controlling the thrust affecting a shaft

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US (1) US20110129331A1 (ja)
EP (1) EP2333345A2 (ja)
JP (1) JP2011117600A (ja)
KR (1) KR20110063352A (ja)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016215482A1 (de) * 2016-08-18 2018-02-22 Siemens Aktiengesellschaft Axiallageranordnung zur Lagerung eines Turbinenrotors

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2523310A (en) * 1947-06-02 1950-09-26 Kirkpatrick John Graham Hydraulic thrust bearing
US3806208A (en) * 1971-10-16 1974-04-23 Leitz Ernst Gmbh Hydrostatic bearing systems
US3816028A (en) * 1972-10-25 1974-06-11 Graco Inc Pumps and painting installations
US3832095A (en) * 1971-08-30 1974-08-27 Honda Motor Co Ltd Fluid pressure accumulating apparatus
US4325583A (en) * 1980-06-30 1982-04-20 General Electric Company Low axial stiffness thrust bearing
US4578018A (en) * 1983-06-20 1986-03-25 General Electric Company Rotor thrust balancing
US4884942A (en) * 1986-06-30 1989-12-05 Atlas Copco Aktiebolag Thrust monitoring and balancing apparatus
US4915510A (en) * 1986-11-12 1990-04-10 Cellwood Machinery Ab Hydrostatic thrust bearing system

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JPS63143703U (ja) * 1987-03-13 1988-09-21
JP3185391B2 (ja) * 1992-08-19 2001-07-09 石川島播磨重工業株式会社 スラスト軸受
JPH07259855A (ja) * 1994-03-17 1995-10-09 Hitachi Ltd スラストバランス室付ガス軸受タービン
JP3438994B2 (ja) * 1995-04-26 2003-08-18 三菱重工業株式会社 スラストガス軸受の面圧調整装置
JPH09170401A (ja) * 1995-12-21 1997-06-30 Mitsubishi Heavy Ind Ltd スラスト制御装置
JP2001140604A (ja) * 1999-11-19 2001-05-22 Ishikawajima Harima Heavy Ind Co Ltd 圧縮空気貯蔵型ガスタービンのスラスト調整装置及び方法
JP2002257080A (ja) * 2001-03-02 2002-09-11 Mitsubishi Heavy Ind Ltd 遠心圧縮機の軸位置自動調整装置
JP2002310081A (ja) * 2001-04-12 2002-10-23 Hitachi Ltd 燃料電池用スクリュー式流体機械
JP4050657B2 (ja) * 2003-05-14 2008-02-20 株式会社前川製作所 バランスピストン装置を備えたスクリュー圧縮機
JP4066920B2 (ja) * 2003-09-16 2008-03-26 日本精工株式会社 トロイダル型無段変速機用試験装置
JP4829193B2 (ja) * 2007-09-11 2011-12-07 日立建機株式会社 液圧開閉弁
JP2009191638A (ja) * 2008-02-12 2009-08-27 Jtekt Corp ターボ機械

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2523310A (en) * 1947-06-02 1950-09-26 Kirkpatrick John Graham Hydraulic thrust bearing
US3832095A (en) * 1971-08-30 1974-08-27 Honda Motor Co Ltd Fluid pressure accumulating apparatus
US3806208A (en) * 1971-10-16 1974-04-23 Leitz Ernst Gmbh Hydrostatic bearing systems
US3816028A (en) * 1972-10-25 1974-06-11 Graco Inc Pumps and painting installations
US4325583A (en) * 1980-06-30 1982-04-20 General Electric Company Low axial stiffness thrust bearing
US4578018A (en) * 1983-06-20 1986-03-25 General Electric Company Rotor thrust balancing
US4884942A (en) * 1986-06-30 1989-12-05 Atlas Copco Aktiebolag Thrust monitoring and balancing apparatus
US4915510A (en) * 1986-11-12 1990-04-10 Cellwood Machinery Ab Hydrostatic thrust bearing system

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JP2011117600A (ja) 2011-06-16
KR20110063352A (ko) 2011-06-10
EP2333345A2 (en) 2011-06-15

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AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:OLSON, JAMES E.;REEL/FRAME:023592/0842

Effective date: 20091202

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION