EP1793081A2 - Appareil d' équilibrage de la poussée axiale d'un rotor et méthode - Google Patents

Appareil d' équilibrage de la poussée axiale d'un rotor et méthode Download PDF

Info

Publication number
EP1793081A2
EP1793081A2 EP06125145A EP06125145A EP1793081A2 EP 1793081 A2 EP1793081 A2 EP 1793081A2 EP 06125145 A EP06125145 A EP 06125145A EP 06125145 A EP06125145 A EP 06125145A EP 1793081 A2 EP1793081 A2 EP 1793081A2
Authority
EP
European Patent Office
Prior art keywords
piston cavity
balance piston
air
air flow
air pressure
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
EP06125145A
Other languages
German (de)
English (en)
Other versions
EP1793081A3 (fr
EP1793081B1 (fr
Inventor
Amid Ansari
Emil Nelson Chouinard
Edward Joseph Stiftar
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP1793081A2 publication Critical patent/EP1793081A2/fr
Publication of EP1793081A3 publication Critical patent/EP1793081A3/fr
Application granted granted Critical
Publication of EP1793081B1 publication Critical patent/EP1793081B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
    • F01D3/04—Machines or engines with axial-thrust balancing effected by working-fluid axial thrust being compensated by thrust-balancing dummy piston or the like
    • 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
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F05D2240/52—Axial thrust bearings

Definitions

  • This invention relates generally to a system for balancing loads on a thrust bearing of a gas turbine engine, and more particularly, to a system for increasing the range of control for rotor thrust balancing.
  • Gas turbine engines include a rotor assembly which is rotatable relative to stationary engine structures, including rotor mounting structure.
  • the rotor assembly includes a number of rotatable components, such as a central shaft, shaft cones, compressor blades and disks, turbine buckets and wheels, and dynamic air seals. Each component is reacted upon by static and/or dynamic axial pressure forces. The vector sum of these forces is a net axial force or thrust in either the forward or aft direction. This net thrust places axial loads on the stationary mounting structure, and a thrust bearing is employed in order to absorb this load without interfering with the free rotation of the rotor assembly.
  • a rotor thrust bearing is a ball bearing encased within a thrust bearing housing.
  • a thrust bearing The load on a thrust bearing varies as the pressures on the various rotor parts change. If net axial thrust is excessive, considerable wear and premature failure of the thrust bearing may occur.
  • a gas turbine engine rotor generates a high thrust, and a rotor thrust bearing must be able to sustain the axial thrust load.
  • a thrust balance system is utilized to limit thrust loads on the bearing.
  • cross-over Under certain operating conditions net rotor axial thrust may change direction, a condition known as "cross-over". If cross-over occurs, unloaded ball bearings may allow radial movement of the rotor which may adversely affect seal clearances resulting in deterioration of engine operating characteristics.
  • an apparatus for balancing thrust bearing load on a rotor thrust bearing employs a first thrust balance piston cavity for exerting an aft directed thrust balancing force and a second balance piston cavity for exerting an independently controlled forward directed thrust balancing force.
  • balancing thrust bearing load on a rotor thrust bearing is accomplished by controlling air pressure in a first balance piston cavity configured to provide an aft directed thrust balancing force to an engine rotor component; and independently controlling air pressure in a second balance piston cavity configured to provide a forward directed thrust balancing force.
  • FIG. 1 schematically depicts an aeroderivative gas turbine engine 10.
  • Engine 10 comprises in axial alignment in serial flow sequence a low pressure compressor 12, a high pressure compressor 14, a combustor 16, a high pressure turbine 18, and a low pressure turbine 20, disposed concentrically about longitudinal axis 22.
  • the standard configuration for engines of this type is a dual concentric shaft arrangement, in which low pressure turbine 20 is drivingly connected to low pressure compressor 12 by low pressure drive shaft 24 and is typically connected to a load (not shown) at its downstream end 29.
  • High pressure turbine 18 is similarly drivingly connected to high pressure compressor 14 by high pressure drive shaft 26 disposed external to low pressure drive shaft 24 and concentrically with longitudinal axis 22 and supported from the stator 25.
  • air is drawn into engine inlet 28, and compressed through low pressure compressor 12 and high pressure compressor 14.
  • Compressed air is delivered to combustor 16 where it is mixed with fuel and ignited to produce air flow through high pressure turbine 18 and low pressure turbine 20, and exits through exhaust nozzle 30.
  • thrust forces are produced within gas turbine engine 10 which act axially at different points or portions in the engine. While a compressor driven by a turbine can compensate to some degree for a net force directed axially downstream in the turbine, at least one rotor thrust bearing is normally used to react the net rotor thrust.
  • At least some known gas turbine engines use compressor bleed air, to pressurize a forward balance piston cavity 32 and an aft balance piston cavity 34, each of which is a defined volume pressurized by air bled from a selected compressor stage.
  • a crossover tube 36 connects the balance piston cavities 32, 34 to equalize the pressure in the interiors of balance piston cavities 32, 34 in flow communication to limit the thrust load on thrust bearing 38.
  • thrust balance operation essentially equal pressure is maintained inside balance piston cavities 32 and 34, so that the pressure applied to piston area having radius 37 of rotating surface 33 of forward balance piston cavity 32 is essentially identical to the pressure applied to piston area having radius 39 of rotating surface 35 of aft balance piston cavity 34.
  • the respective radii 37, 39 of surfaces 33 and 35 are selected as a design feature to establish respective fixed design surface areas to establish a fixed ratio of forces to be applied to the rotor, which have been determined by engine design to be optimal for protecting the thrust bearing 38 during engine operation under anticipated operating conditions.
  • the air pressure in the respective balance piston cavities 32, 34 acts to maintain the force ratio to counter anticipated loads acting on the thrust bearing 38 during engine opertion.
  • thrust load on rotor thrust bearing 40 is controlled by a thrust balance system which includes a forward balance piston cavity 42 located upstream of the rotor thrust bearing 40 of the engine 10 and an aft balance piston cavity 46 located downstream of the rotor thrust bearing 40.
  • Balance piston cavity 46 is a closed volume defined at its aft end by rotatable member 43 connected to the high pressure drive shaft 26 of the rotor and defined at the axially opposite forward end by stationary surface 45 connected to the stator 25, and is pressurized by high pressure compressor discharge air flow via air pressurized volume 72 through seal 41.
  • High pressure compressor discharge air from a compressor stage selected to provide the required air pressure and flow rate pressurizes air pressurized volume 72 and air flow through seal 41 flows into and pressurizes the interior of balance piston cavity 46.
  • the magnitude of force acting in the axially aft direction represented by arrow 74 which can be supplied by balance piston cavity 46 is determined by the air pressure inside balance piston cavity 46 applied to an annular surface area having radius 51 of rotatable member 43.
  • Air pressure relief tube 47 connects the interior of balance piston cavity 46 in flow communication to a control system shown in Figure 5 and described hereinafter.
  • balance piston cavity 42 is defined at its axially forward end by the annular plate 53 connected to high pressure drive shaft 26 of the rotor and at its axially aft end by annular plate 55 connected to the stator 25.
  • High pressure compressor discharge air from a compressor stage selected to provide the required air pressure and flow rate pressurizes air pressurized volume 70 and air flow through seal 52 flows into and pressurizes the interior of balance piston cavity 42.
  • the magnitude of force acting in the axially forward direction represented by arrow 76 which can be supplied by balance piston cavity 42 is determined by the air pressure inside balance piston cavity 42 applied to annular surface area having radius 54 of plate 53.
  • Air pressure relief tube 56 connects the balance piston cavity 42 in flow communication to a control system shown in Figure 5 and described hereinafter.
  • a thrust balance control system is shown in block diagram form in Figure 5.
  • Balance piston cavity 42 pressurized by discharge from high pressure compressor 69 via air pressurized volume 70 through seal 52, is connected via air pressure relief tube 56 to air flow control valve 58 and air exhaust tube 62.
  • Balance piston cavity 46 pressurized by discharge from high pressure compressor 69 via air pressurized volume 72 through seal 41, is connected via air pressure relief tube 47 and air flow control valve 59 to air exhaust tube 64.
  • Exhaust tubes 62, 64 direct air to a downstream area 66 of the engine, which allows the air to contribute to overall engine efficiency, or alternatively may be exhausted to ambient.
  • Control unit 60 receives pressure measurements from respective sensors 82 and 84 in balance piston cavities 42 and 46, respectively.
  • Control unit 60 is operatively connected to provide independent control of air flow control valves 58 and 59.
  • Control unit 60 may be a manually operated system providing readout of the pressure measurements from sensors 82 and 84, so that an operator may manually activate air flow control valves 58 or 59.
  • control unit 60 may be an automatically controlled unit which adjusts settings of air flow control valves 58 or 59 in accordance with a numerical control system
  • air flow control valves 58 and 59 may be independently activated by control unit 60 to raise or lower the pressure in each or both of balance piston cavities 42 or 46.
  • the pressure in one balance piston cavity may be raised by a certain pressure, while the pressure in the other may be raised an identical amount, a lesser amount, a greater amount or may be lowered by any amount within the pressure range capability of the system.
  • control unit 60 may operate air flow control valves 58 and 59 independently to control pressure levels in the respective balance piston cavities 42 and 46.
  • Air pressure inside balance piston cavity 46 is controlled via air pressure relief tube 47 by activation of air flow control valve 59.
  • air flow control valve 59 When air flow control valve 59 is closed, the pressure inside balance piston cavity 46 is held at essentially the maximum pressure available from the high pressure compressor source 72 output to apply proportional pressure to the annular plate 43 as a generally downstream force, represented by arrow 74 in Figure 3, to balance the load on thrust bearing 40.
  • air flow control valve 59 When air flow control valve 59 is fully opened, the pressure inside balance piston cavity 46 drops to approximately the low pressure of downstream area 66 or ambient, and little pressure is applied to annular plate 43.
  • Air pressure inside balance piston cavity 42 is controlled via air pressure relief tube 56 by controlling air flow control valve 58.
  • air flow control valve 58 When air flow control valve 58 is closed, the pressure inside balance piston cavity 42 is held at essentially the maximum pressure available from the high pressure compressor source 70 output and applies that pressure to the annular plate 53 as a generally upstream force, represented by arrow 76 in Figure 3, to balance the load on thrust bearing 40.
  • air flow control valve 58 When air flow control valve 58 is opened the pressure inside balance piston cavity 42 drops to the low pressure of downstream area 66 or ambient, and little pressure is applied to annular plate 53.
  • Intermediate valve settings for air flow control valve 58 allow the pressure inside balance piston cavity 46 to be maintained at an intermediate level below the maximum pressure available from high pressure compressor source 70.
  • Control unit 60 selectively activates air flow control valve 58 to maintain, raise or lower the pressure inside balance piston cavity 42 and/or selectively activates air flow control valve 59 to maintain, raise or lower the pressure inside balance piston cavity 46.
  • Air flow from balance piston cavity 42 via air pressure relief tube 56 is adjustable independently from air flow from balance piston cavity 46 via air pressure relief tube 47, so that the pressure inside one of balance piston cavities 42, 46 may be lowered while pressure inside the other is maintained or raised.
  • This independent pressure control allows the ratio of aft and forward forces to be adjusted during engine operation, in contrast to the fixed ratio of the prior art system.
  • the separate control of pressure in balance piston cavity 42 from that of balance piston cavity 46 provides considerably higher thrust pressure level control and flexibility in controlling thrust loads on rotor thrust bearing 40.
  • control unit 60 If control unit 60 is automatically operated, the pressure control will be determined by an algorithm designed to predict rotor thrust levels during engine operation on the basis of measurements of pressure within the balance piston cavities.
  • the control system will selectively adjust the pressure within the respective balance pressure cavities to maintain the proper loads on the thrust bearing 40. As a result, the useful life of a bearing assembly is extended in a highly reliable and cost-effective manner.
  • the piston areas By separately controlling the pressure supplied to each of the balance piston cavities, i.e. lowering air pressure in one balance piston cavity while raising the air pressure in the other balance piston cavity by the same amount, the piston areas may be effectively added, so that the thrust balance may handle higher total thrust loads.
  • Figure 6 graphically illustrates the bearing load versus horsepower relationship and balance pistoncavity pressure versus horsepower in the upper and lower graphs, respectively, for a gas turbine engine of the type shown in Figure 3.
  • the top graph of Figure 6 illustrates a typical relationship, but many factors affecting the bearing load, i.e. net rotor thrust, can cause the bearing load versus horsepower relationship to vary so that the curves may have many shapes.
  • the gas turbine engine is designed so that during normal operation the thrust bearing 40 is operating within an acceptable thrust loading range of a nominal design thrust load level relative to horsepower shown at 106 between the maximum acceptable bearing load, shown at 108, and the minimum acceptable load, shown at 110. The difference between maximum load 108 and minimum load 110 at any horsepower setting determines the available range of thrust balancing control.
  • the anticipated thrust bearing load increases and balance piston cavities including air relief tubes and valves are sized to accommodate the anticipated load balancing requirement.
  • the engine is designed so that nominal valve settings for the air flow control valves 58 and 59 maintain the air pressures within the respective balance piston cavities 42, 46 approximately equal along a curve shown at 100 in the lower graph of Figure 6, within a range between maximum operating pressure, approximately the compressor bleed for a particular horsepower, shown by curve 102, and a minimum pressure of ambient shown by curve 104.
  • the difference between the maximum balance piston cavity pressure 102 and minimum balance piston cavity pressure 104 represents the available range of pressure adjustment at a particular engine horsepower level.
  • Air flow control valve 58 may be activated to lower pressure on balance piston cavity 42 while the pressure in balance piston cavity 46 is maintained to effectively lower the force level applied to piston area 54 increasing net bearing load in the aft direction. If further adjustment is needed, the pressure in balance piston cavity 46 can also be raised by closing air flow control valve 59, hence providing larger adjustment.
  • the total force level adjustment available is the difference between the pressure 102 and the pressure 104 on piston area 51 and 54.
  • either or both of air flow control valves 58 and 59 may be activated to lower pressure in balance piston cavity 46 and/or raise the pressure in balance piston cavity 42 to apply forward axial pressure on balance piston area 54 and/or less force on piston area 51 to relieve the load on rotor thrust bearing 40, depending on level of adjustment needed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Non-Positive-Displacement Pumps (AREA)
EP06125145A 2005-11-30 2006-11-30 Appareil d' équilibrage de la poussée axiale d'un rotor et méthode Expired - Fee Related EP1793081B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/290,114 US20070122265A1 (en) 2005-11-30 2005-11-30 Rotor thrust balancing apparatus and method

Publications (3)

Publication Number Publication Date
EP1793081A2 true EP1793081A2 (fr) 2007-06-06
EP1793081A3 EP1793081A3 (fr) 2007-10-24
EP1793081B1 EP1793081B1 (fr) 2010-04-14

Family

ID=37763877

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06125145A Expired - Fee Related EP1793081B1 (fr) 2005-11-30 2006-11-30 Appareil d' équilibrage de la poussée axiale d'un rotor et méthode

Country Status (5)

Country Link
US (1) US20070122265A1 (fr)
EP (1) EP1793081B1 (fr)
JP (1) JP4854484B2 (fr)
CA (1) CA2569933A1 (fr)
DE (1) DE602006013579D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2050932A3 (fr) * 2007-10-20 2012-06-13 Rolls-Royce plc Système de palier d'arbre de turbine de moteur à turbine à gaz et procédé de fonctionnement d'un tel système
EP2246528A3 (fr) * 2009-04-24 2014-05-14 Pratt & Whitney Canada Corp. Système de distribution de charge pour moteur à turbine à gaz

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2011963B1 (fr) * 2007-07-04 2018-04-04 Ansaldo Energia Switzerland AG Procédé de fonctionnement d'une turbine à gaz à poussée axiale compensée
US8061970B2 (en) * 2009-01-16 2011-11-22 Dresser-Rand Company Compact shaft support device for turbomachines
NO330015B1 (no) * 2009-06-22 2011-02-07 Statoil Asa Et aksialt gasskyvekraftlager for rotorer i roterende maskineri
US8434994B2 (en) 2009-08-03 2013-05-07 General Electric Company System and method for modifying rotor thrust
US8994237B2 (en) 2010-12-30 2015-03-31 Dresser-Rand Company Method for on-line detection of liquid and potential for the occurrence of resistance to ground faults in active magnetic bearing systems
WO2013109235A2 (fr) 2010-12-30 2013-07-25 Dresser-Rand Company Procédé de détection en ligne de défauts de résistance à la masse dans des systèmes de palier magnétique actif
US9551349B2 (en) 2011-04-08 2017-01-24 Dresser-Rand Company Circulating dielectric oil cooling system for canned bearings and canned electronics
US8876389B2 (en) 2011-05-27 2014-11-04 Dresser-Rand Company Segmented coast-down bearing for magnetic bearing systems
US8851756B2 (en) 2011-06-29 2014-10-07 Dresser-Rand Company Whirl inhibiting coast-down bearing for magnetic bearing systems
US10815891B2 (en) 2012-09-28 2020-10-27 Raytheon Technologies Corporation Inner diffuser case struts for a combustor of a gas turbine engine
US10830092B2 (en) 2018-03-07 2020-11-10 General Electric Company Bearing rotor thrust control
US11203934B2 (en) 2019-07-30 2021-12-21 General Electric Company Gas turbine engine with separable shaft and seal assembly

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4907943A (en) * 1988-05-25 1990-03-13 United Technologies Corporation Method and apparatus for assessing thrust loads on engine bearings
EP1281836A2 (fr) * 2001-08-03 2003-02-05 Atlas Copco Energas Gmbh Turbomachine

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2647684A (en) * 1947-03-13 1953-08-04 Rolls Royce Gas turbine engine
US3505813A (en) * 1968-05-31 1970-04-14 Rolls Royce Turbine engine with axial load balancing means for thrust bearing
US4306834A (en) * 1979-06-25 1981-12-22 Westinghouse Electric Corp. Balance piston and seal for gas turbine engine
US4697981A (en) * 1984-12-13 1987-10-06 United Technologies Corporation Rotor thrust balancing
US4884942A (en) * 1986-06-30 1989-12-05 Atlas Copco Aktiebolag Thrust monitoring and balancing apparatus
US5167484A (en) * 1990-10-01 1992-12-01 General Electric Company Method for thrust balancing and frame heating
US5248239A (en) * 1992-03-19 1993-09-28 Acd, Inc. Thrust control system for fluid handling rotary apparatus
US5760289A (en) * 1996-01-02 1998-06-02 General Electric Company System for balancing loads on a thrust bearing of a gas turbine engine rotor and process for calibrating control therefor
US5862666A (en) * 1996-12-23 1999-01-26 Pratt & Whitney Canada Inc. Turbine engine having improved thrust bearing load control
US6457933B1 (en) * 2000-12-22 2002-10-01 General Electric Company Methods and apparatus for controlling bearing loads within bearing assemblies
ITMI20022337A1 (it) * 2002-11-05 2004-05-06 Nuovo Pignone Spa Assieme di bilanciamento di spinta assiale per un
US6957945B2 (en) * 2002-11-27 2005-10-25 General Electric Company System to control axial thrust loads for steam turbines
DE10358625A1 (de) * 2003-12-11 2005-07-07 Rolls-Royce Deutschland Ltd & Co Kg Anordnung zur Lagerentlastung in einer Gasturbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4907943A (en) * 1988-05-25 1990-03-13 United Technologies Corporation Method and apparatus for assessing thrust loads on engine bearings
EP1281836A2 (fr) * 2001-08-03 2003-02-05 Atlas Copco Energas Gmbh Turbomachine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2050932A3 (fr) * 2007-10-20 2012-06-13 Rolls-Royce plc Système de palier d'arbre de turbine de moteur à turbine à gaz et procédé de fonctionnement d'un tel système
EP2246528A3 (fr) * 2009-04-24 2014-05-14 Pratt & Whitney Canada Corp. Système de distribution de charge pour moteur à turbine à gaz

Also Published As

Publication number Publication date
JP2007154888A (ja) 2007-06-21
EP1793081A3 (fr) 2007-10-24
US20070122265A1 (en) 2007-05-31
JP4854484B2 (ja) 2012-01-18
EP1793081B1 (fr) 2010-04-14
CA2569933A1 (fr) 2007-05-30
DE602006013579D1 (de) 2010-05-27

Similar Documents

Publication Publication Date Title
EP1793081B1 (fr) Appareil d' équilibrage de la poussée axiale d'un rotor et méthode
US7555905B2 (en) Self-actuating bleed valve for gas turbine engine
EP2050925B1 (fr) Système de palier d'arbre de turbine et procédé de fonctionnement d'un tel système
JP5511158B2 (ja) 軸方向推力補償を備えるガスタービン
US4370560A (en) Compressor load control for an auxiliary power unit
US5312226A (en) Turbo compressor and method of controlling the same
EP1749253B1 (fr) Commande de soupape pneumatique presentant des caracteristiques d'ouverture ameliorees et un demarreur pneumatique comportant ladite commande
US5141389A (en) Control system for regulating the axial loading of a rotor of a fluid machine
US6058694A (en) Gas turbine engine commanded oil flow valve with failsafe
JPH0476020B2 (fr)
US4405290A (en) Pneumatic supply system having variable geometry compressor
EP1939426A2 (fr) Système pour alimenter d'air à un aéronef avec turboréacteur
US10502141B2 (en) Apparatus and method for controlling a pressure differential across a seal of a bearing chamber
JPS6027812B2 (ja) タ−ボチヤ−ジヤ機構の制御装置
USRE31835E (en) Pneumatic supply system having variable geometry compressor
US10717517B2 (en) Hydraulic actuation system
JP4050657B2 (ja) バランスピストン装置を備えたスクリュー圧縮機
JP2002257080A (ja) 遠心圧縮機の軸位置自動調整装置
JP7107730B2 (ja) 油冷式スクリュ圧縮機の運転制御方法及び油冷式スクリュ圧縮機
US7559696B2 (en) Active thrust management system
CN108301914B (zh) 具有窜油保护的涡轮增压器组件
CA1159900A (fr) Regulateur de la demande a un compresseur pour un generateur electrique de secours
JPH04351318A (ja) 気体軸受の給気制御方法及び装置
US11603853B2 (en) Compressor configured to control pressure against magnetic motor thrust bearings
US20160377000A1 (en) Method for operating a gas turbine installation and the same

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

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

17P Request for examination filed

Effective date: 20080424

17Q First examination report despatched

Effective date: 20080602

AKX Designation fees paid

Designated state(s): DE FR GB

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REF Corresponds to:

Ref document number: 602006013579

Country of ref document: DE

Date of ref document: 20100527

Kind code of ref document: P

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20101126

Year of fee payment: 5

26N No opposition filed

Effective date: 20110117

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20101124

Year of fee payment: 5

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20111128

Year of fee payment: 6

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20121130

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20130731

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602006013579

Country of ref document: DE

Effective date: 20130601

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130601

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121130

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121130