EP0518027A1 - Compresseur centrifugal - Google Patents

Compresseur centrifugal Download PDF

Info

Publication number
EP0518027A1
EP0518027A1 EP92106288A EP92106288A EP0518027A1 EP 0518027 A1 EP0518027 A1 EP 0518027A1 EP 92106288 A EP92106288 A EP 92106288A EP 92106288 A EP92106288 A EP 92106288A EP 0518027 A1 EP0518027 A1 EP 0518027A1
Authority
EP
European Patent Office
Prior art keywords
impeller
centrifugal compressor
exit
air
annular space
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
EP92106288A
Other languages
German (de)
English (en)
Other versions
EP0518027B1 (fr
Inventor
Koichiro C/O Nagasaki Shipyard & Eng. Imakiire
Keiichi C/O Nagasaki Shipyard & Eng. Shiraishi
Masanori C/O Nagasaki Shipyard & Eng. Kimura
Masayoshi C/O Nagasaki Shipyard & Eng. Tagawa
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of EP0518027A1 publication Critical patent/EP0518027A1/fr
Application granted granted Critical
Publication of EP0518027B1 publication Critical patent/EP0518027B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel
    • 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5846—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling by injection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B3/00—Engines characterised by air compression and subsequent fuel addition
    • F02B3/06—Engines characterised by air compression and subsequent fuel addition with compression ignition

Definitions

  • the present invention relates to a centrifugal compressor to be applied, for example, as a supercharger of an engine.
  • Fig. 3 is a longitudinal section showing the structure of a centrifugal compressor of the prior art
  • Fig. 4 is a section for explaining the operations of the same.
  • a labyrinth packing 5 which seals up a seal space 7 between the exit and back of the impeller 1.
  • the seal space 7 is vented to the outside through a ventilation hole 8 for releasing a slight amount of air, which comes into the seal space 7 along the labyrinth packing 5, to the outside thereby to drop the pressure in the seal space 7.
  • the air temperature at the exit of the impeller 1 becomes the higher at the higher pressure ratio of the centrifugal compressor. Even in case the air at the room temperature is sucked, for example, its temperature reaches 200°C or more at exit of the impeller 1 if the pressure ratio is about 4.0.
  • This hot air is additionally heated, while passing through the labyrinth packing 5, by the heat of friction which is produced by the rotations of the fins of the labyrinth packing 5 so that the impeller 1 has its back heated.
  • the centrifugal compressor of this single stage type inhaling the atmospheric air usually has its impeller made of an aluminum alloy, and the impeller 1 has its strength degraded due to its temperature rise when heated by the air at its back. This make it difficult to retain the high pressure ratio if it is made of an aluminum alloy.
  • the temperature rise of the impeller 1 in turn leads to a rise in the air temperature, thus causing an efficiency drop of the compressor.
  • An object of the present invention is to provide a centrifugal compressor which can solve the above-specified difficulty.
  • a centrifugal compressor which comprises: an impeller; a seal member arranged annularly and multiplexly at the back of said impeller for sealing up a gap between the exit of said impeller and a space at the back of said impeller and for forming an annular space; and a passage for feeding a cold gas under a higher pressure than that at the exit of said impeller into said annular space.
  • the seal member is so arranged annularly and multiplexly at the back of the impeller that it seals up the gap between the exit of the impeller and a space at the back of the impeller and forms the annular space.
  • This annular space is fed through the passage with a cold gas under a higher pressure than that at the exit of the impeller. Since the cold gas fed through the passage has a higher pressure than that at the exit of the impeller, the hot gas at the impeller exit is prevented from flowing into the space at the impeller back, but a small amount of cold gas will flow out of the space toward the impeller exit. As a result, the back of the impeller is not heated by the gas at the impeller exit but cooled by the cold gas fed through the passage.
  • Fig. 1 shows the structure of a centrifugal compressor according to one embodiment of the present invention
  • Fig. 2 illustrates the operations of the centrifugal compressor.
  • the centrifugal compressor according to the present embodiment is used as a supercharger of an engine.
  • a labyrinth packing 15 for sealing up a seal space 7 between the exit and back of the impeller 1.
  • the seal space 7 is vented to the outside through a ventilation hole 8 for releasing a slight amount of air, which comes into the seal space 7 along the labyrinth packing 5, to the outside thereby to drop the pressure in the seal space 7.
  • the air temperature at the exit of the impeller 1 is the higher at the higher pressure ratio of the centrifugal compressor. Even in case the air at the room temperature is sucked, for example, its temperature reaches 200°C or more at exit of the impeller 1 if the pressure ratio is about 4.0.
  • the labyrinth packing 15 of the present centrifugal compressor has its fines classified into two outer and inner groups, which form an annular space 6 inbetween. This annular space 6 is fed, as better seen from Fig. 2, through an air passage 9 from the outside with the cold air which has a higher pressure P2 than a pressure P1 at the exit of the impeller 1.
  • the air having left the centrifugal compressor has a higher pressure than that P1 at the exit of the impeller 1, like the compressed cold air under a high pressure to be fed from the supercharger through a cooler to the engine, and the compressed air is cooled down by an air cooler before it is used.
  • this cooled air may be guided to the labyrinth packing 15 at the back of the impeller 1.
  • the labyrinth packing 15 of the present centrifugal compressor has two outer and inner groups of fins and its intervening annular space 6 fed with the air under the higher pressure P2 than the pressure P1 at the exit of the impeller 1.
  • the air thus fed has the higher pressure P2 so that the air at the exit of the impeller 1 will not flow along the labyrinth packing 15 into the annular space 6.
  • a small amount of air fed to the annular space 6 will flow toward the exit of the impeller 1.
  • the back of the impeller 1 is not exposed to and accordingly heated by the air, which might otherwise flow from the exit of the impeller 1, but is cooled by the cold air fed from the outside via the air passage 9.
  • the impeller 1 can have its temperature rise suppressed so that its strength can be prevented from being degraded by the temperature rise.
  • the seal space 7 at the back of the impeller 1 and the annular space 6 are sealed up by the labyrinth packing 15, the air flow, if any to the seal space 7, is released from the ventilation hole 8 to drop a pressure P3 in the seal space 7.
  • the load upon the main thrust bearing 3 is not increased by the balanced thrust unlike the centrifugal compressor of the prior art.
  • the impeller back is not heated by the gas at the impeller exit but is cooled down by the cold gas.
  • the high pressure ratio can be retained even if the impeller is made of an aluminum alloy, and the temperature of the gas to be compressed by the impeller can be dropped to raise the compression efficiency.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP92106288A 1991-06-14 1992-04-10 Compresseur centrifugal Expired - Lifetime EP0518027B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP143231/91 1991-06-14
JP3143231A JP2934530B2 (ja) 1991-06-14 1991-06-14 遠心圧縮機

Publications (2)

Publication Number Publication Date
EP0518027A1 true EP0518027A1 (fr) 1992-12-16
EP0518027B1 EP0518027B1 (fr) 1995-07-05

Family

ID=15333954

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92106288A Expired - Lifetime EP0518027B1 (fr) 1991-06-14 1992-04-10 Compresseur centrifugal

Country Status (5)

Country Link
EP (1) EP0518027B1 (fr)
JP (1) JP2934530B2 (fr)
KR (1) KR950006873B1 (fr)
DE (1) DE69203293T2 (fr)
FI (1) FI921758A (fr)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0961033A1 (fr) 1998-05-25 1999-12-01 Asea Brown Boveri Ag Compresseur radial
EP0961034A1 (fr) * 1998-05-25 1999-12-01 Asea Brown Boveri Ag Compresseur radial
WO2001029426A1 (fr) * 1999-10-20 2001-04-26 Abb Turbo Systems Ag Procede et dispositif de refroidissement indirect de l'ecoulement dans des entrefers radiaux formes entre les rotors et les stators de turbomachines
WO2001029425A1 (fr) * 1999-10-20 2001-04-26 Abb Turbo Systems Ag Procede et dispositif de refroidissement de l'ecoulement dans les fentes radiales formees entre les rotors et les stators de turbomachines
WO2005028813A1 (fr) * 2003-09-12 2005-03-31 Mes International, Inc. Systeme d'etancheification dans un compresseur
WO2007035699A2 (fr) * 2005-09-19 2007-03-29 Ingersoll-Rand Company Impulseur destine a un compresseur centrifuge
WO2007035698A3 (fr) * 2005-09-19 2007-05-18 Ingersoll Rand Co Compresseur centrifuge comprenant un systeme de joints
WO2014163702A3 (fr) * 2013-03-08 2014-11-20 Lunsford Patrick L Roue à ailettes multi-pièce
ITFI20130237A1 (it) * 2013-10-14 2015-04-15 Nuovo Pignone Srl "sealing clearance control in turbomachines"
CN104712380A (zh) * 2013-12-16 2015-06-17 霍尼韦尔国际公司 具有背盘密封件和排出口的压缩机或涡轮机
DE102016102923A1 (de) 2016-02-19 2017-08-24 Abb Turbo Systems Ag Verdichterradrückseitige Radialturbine
EP3343044A1 (fr) * 2016-12-28 2018-07-04 Nidec Corporation Dispositif de ventilation et aspirateur le comprenant
EP3456980A1 (fr) * 2017-09-15 2019-03-20 Mitsubishi Heavy Industries Compressor Corporation Compresseur avec équilibrage de poussée axiale par pression sur la face arrière du rouet
US11002291B2 (en) 2016-03-30 2021-05-11 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Compressor impeller
WO2021105047A1 (fr) * 2019-11-25 2021-06-03 Robert Bosch Gmbh Turbomachine
CN115450950A (zh) * 2022-11-08 2022-12-09 中国核动力研究设计院 压气机和超临界二氧化碳发电系统
WO2023273232A1 (fr) * 2021-07-02 2023-01-05 鑫磊压缩机股份有限公司 Compresseur auto-correcteur de précision d'assemblage

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4810599A (en) 1987-03-27 1989-03-07 Japan Synthetic Rubber Co., Ltd. Structure suitable for solid electrochemical elements
DE59709283D1 (de) * 1997-12-23 2003-03-13 Abb Turbo Systems Ag Baden Verfahren und Vorrichtung zum berührungsfreien Abdichten eines zwischen einem Rotor und einem Stator ausgebildeten Trennspalts
DE19845375A1 (de) 1998-10-02 2000-04-06 Asea Brown Boveri Verfahren und Vorrichtung zur indirekten Kühlung der Strömung in zwischen Rotoren und Statoren von Turbomaschinen ausgebildeten Radialspalten
KR100414103B1 (ko) * 2001-08-17 2004-01-07 엘지전자 주식회사 터보 압축기의 디퓨져 장착구조
CN101297118B (zh) * 2005-09-19 2011-09-28 英格索尔-兰德公司 用于离心压缩机的静止密封环
US7402020B2 (en) * 2005-12-14 2008-07-22 Hamilton Sundstrand Corporation ACM cooling flow path and thrust load design
JP5135981B2 (ja) * 2007-10-05 2013-02-06 株式会社Ｉｈｉ 遠心圧縮機
JP2010168968A (ja) * 2009-01-21 2010-08-05 Toyota Motor Corp ターボチャージャ
DE102010037356B8 (de) * 2010-09-06 2014-05-22 Kompressorenbau Bannewitz Gmbh Verdichterradkühlung
JP5700999B2 (ja) * 2010-10-06 2015-04-15 三菱重工業株式会社 遠心圧縮機
US9228497B2 (en) * 2010-12-30 2016-01-05 Rolls-Royce Corporation Gas turbine engine with secondary air flow circuit
JP2014111905A (ja) 2012-12-05 2014-06-19 Mitsubishi Heavy Ind Ltd 遠心圧縮機およびこれを備えた過給機ならびに遠心圧縮機の運転方法
WO2014128877A1 (fr) * 2013-02-21 2014-08-28 トヨタ自動車株式会社 Dispositif de refroidissement d'appareil de suralimentation de moteur à combustion interne comprenant un dispositif de circulation de gaz perdu
JP6225092B2 (ja) * 2014-10-17 2017-11-01 三菱重工業株式会社 ラビリンスシール、遠心圧縮機及び過給機
CN105240280A (zh) * 2015-10-30 2016-01-13 江苏大学 一种具有矩形齿泵前腔结构的离心泵

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE249336C (fr) * 1900-01-01
FR379125A (fr) * 1907-06-21 1907-10-25 Wilhelm Heinrich Eyermann équilibrage de la pression axiale dans les turbines, pompes rotatives et compresseurs
US3650634A (en) * 1970-11-06 1972-03-21 Carrier Corp Centrifugal refrigeration compressor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE249336C (fr) * 1900-01-01
FR379125A (fr) * 1907-06-21 1907-10-25 Wilhelm Heinrich Eyermann équilibrage de la pression axiale dans les turbines, pompes rotatives et compresseurs
US3650634A (en) * 1970-11-06 1972-03-21 Carrier Corp Centrifugal refrigeration compressor

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0961033A1 (fr) 1998-05-25 1999-12-01 Asea Brown Boveri Ag Compresseur radial
EP0961034A1 (fr) * 1998-05-25 1999-12-01 Asea Brown Boveri Ag Compresseur radial
US6190123B1 (en) 1998-05-25 2001-02-20 Asea Brown Boverti Ag Centrifugal compressor
US6238179B1 (en) 1998-05-25 2001-05-29 Asea Brown Boveri Ag Centrifugal compressor
WO2001029426A1 (fr) * 1999-10-20 2001-04-26 Abb Turbo Systems Ag Procede et dispositif de refroidissement indirect de l'ecoulement dans des entrefers radiaux formes entre les rotors et les stators de turbomachines
WO2001029425A1 (fr) * 1999-10-20 2001-04-26 Abb Turbo Systems Ag Procede et dispositif de refroidissement de l'ecoulement dans les fentes radiales formees entre les rotors et les stators de turbomachines
WO2005028813A1 (fr) * 2003-09-12 2005-03-31 Mes International, Inc. Systeme d'etancheification dans un compresseur
US7252474B2 (en) 2003-09-12 2007-08-07 Mes International, Inc. Sealing arrangement in a compressor
WO2007035699A2 (fr) * 2005-09-19 2007-03-29 Ingersoll-Rand Company Impulseur destine a un compresseur centrifuge
WO2007035698A3 (fr) * 2005-09-19 2007-05-18 Ingersoll Rand Co Compresseur centrifuge comprenant un systeme de joints
WO2007035699A3 (fr) * 2005-09-19 2007-05-31 Ingersoll Rand Co Impulseur destine a un compresseur centrifuge
WO2014163702A3 (fr) * 2013-03-08 2014-11-20 Lunsford Patrick L Roue à ailettes multi-pièce
US10527055B2 (en) 2013-03-08 2020-01-07 Rolls-Royce Corporation Multi-piece impeller
US9759225B2 (en) 2013-03-08 2017-09-12 Rolls-Royce Corporation Multi-piece impeller
CN105814284A (zh) * 2013-10-14 2016-07-27 诺沃皮尼奥内股份有限公司 涡轮机中的密封间隙控制
ITFI20130237A1 (it) * 2013-10-14 2015-04-15 Nuovo Pignone Srl "sealing clearance control in turbomachines"
WO2015055542A1 (fr) * 2013-10-14 2015-04-23 Nuovo Pignone Srl Contrôle de jeu d'étanchéité dans des turbomachines
CN105814284B (zh) * 2013-10-14 2019-04-23 诺沃皮尼奥内股份有限公司 涡轮机中的密封间隙控制
US10280932B2 (en) 2013-10-14 2019-05-07 Nuovo Pignone Srl Sealing clearance control in turbomachines
CN104712380A (zh) * 2013-12-16 2015-06-17 霍尼韦尔国际公司 具有背盘密封件和排出口的压缩机或涡轮机
US11377954B2 (en) 2013-12-16 2022-07-05 Garrett Transportation I Inc. Compressor or turbine with back-disk seal and vent
CN104712380B (zh) * 2013-12-16 2018-11-02 盖瑞特交通一公司 具有背盘密封件和排出口的压缩机或涡轮机
EP2884047A1 (fr) * 2013-12-16 2015-06-17 Honeywell International Inc. Compresseur ou turbine avec joint de disque arrière et évent
EP3553275A1 (fr) * 2013-12-16 2019-10-16 Garrett Transportation I Inc. Compresseur ou turbine avec joint de disque arrière et évent
DE102016102923A1 (de) 2016-02-19 2017-08-24 Abb Turbo Systems Ag Verdichterradrückseitige Radialturbine
US11002291B2 (en) 2016-03-30 2021-05-11 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Compressor impeller
EP3343044A1 (fr) * 2016-12-28 2018-07-04 Nidec Corporation Dispositif de ventilation et aspirateur le comprenant
US10876535B2 (en) 2017-09-15 2020-12-29 Mitsubishi Heavy Industries Compressor Corporation Compressor
EP3456980A1 (fr) * 2017-09-15 2019-03-20 Mitsubishi Heavy Industries Compressor Corporation Compresseur avec équilibrage de poussée axiale par pression sur la face arrière du rouet
WO2021105047A1 (fr) * 2019-11-25 2021-06-03 Robert Bosch Gmbh Turbomachine
WO2023273232A1 (fr) * 2021-07-02 2023-01-05 鑫磊压缩机股份有限公司 Compresseur auto-correcteur de précision d'assemblage
CN115450950A (zh) * 2022-11-08 2022-12-09 中国核动力研究设计院 压气机和超临界二氧化碳发电系统
CN115450950B (zh) * 2022-11-08 2023-03-03 中国核动力研究设计院 压气机和超临界二氧化碳发电系统

Also Published As

Publication number Publication date
DE69203293D1 (de) 1995-08-10
DE69203293T2 (de) 1996-01-25
FI921758A0 (fi) 1992-04-21
JPH04365997A (ja) 1992-12-17
KR930000807A (ko) 1993-01-15
KR950006873B1 (ko) 1995-06-23
FI921758A (fi) 1992-12-15
JP2934530B2 (ja) 1999-08-16
EP0518027B1 (fr) 1995-07-05

Similar Documents

Publication Publication Date Title
EP0518027B1 (fr) Compresseur centrifugal
US5297928A (en) Centrifugal compressor
US4503683A (en) Compact cooling turbine-heat exchanger assembly
US6416281B1 (en) Method and arrangement for cooling the flow in radial gaps formed between rotors and stators of turbomachines
US5344160A (en) Shaft sealing of steam turbines
US3754766A (en) Spring type ring seal
US6190123B1 (en) Centrifugal compressor
US2973136A (en) Compressor
EP0552281B1 (fr) Joint inter-etages de moteur a turbine ameliore
EP1108858A2 (fr) Cône de support à double paroi
JPH03121294A (ja) 遠心圧縮機用シール装置及びそのシール加圧方法
JPS58203268A (ja) 流体機械用パツキン
JPH05195812A (ja) エンジン冷却を改良する方法および装置
US4978278A (en) Turbomachine with seal fluid recovery channel
US5233824A (en) Turbine engine interstage seal
US4099727A (en) Seal system for a gas turbine engine or the like
US6079944A (en) Gas turbine stationary blade double cross type seal device
US6764081B2 (en) Supplemental seal for the chordal hinge seals in a gas turbine and methods of installation
CA2244442A1 (fr) Structure de joint de l'enveloppe d'une aube fixe de turbine a gaz
US2588122A (en) Arrangement for collecting and utilizing natural gas leakage from a centrifugal compressor employed on a pipe line
JPH11173103A (ja) ガスタービンのスピンドルボルトシール装置
US3936651A (en) Turboset including a helium turbine and a helium-cooled generator
JPH06193591A (ja) 遠心コンプレッサ
US5505588A (en) Compressor with gas sealing chamber
JPS61142328A (ja) 排気タ−ビン過給機の潤滑機構

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: 19920507

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH DE FR GB LI

EL Fr: translation of claims filed
17Q First examination report despatched

Effective date: 19940621

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE FR GB LI

ET Fr: translation filed
REF Corresponds to:

Ref document number: 69203293

Country of ref document: DE

Date of ref document: 19950810

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

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19970401

Year of fee payment: 6

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

Ref country code: FR

Payment date: 19970409

Year of fee payment: 6

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

Ref country code: GB

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

Effective date: 19980410

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

Ref country code: DE

Payment date: 19980417

Year of fee payment: 7

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

Ref country code: FR

Free format text: THE PATENT HAS BEEN ANNULLED BY A DECISION OF A NATIONAL AUTHORITY

Effective date: 19980430

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

Ref country code: CH

Payment date: 19980505

Year of fee payment: 7

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

Effective date: 19980410

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

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

Ref country code: LI

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

Effective date: 19990430

Ref country code: CH

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

Effective date: 19990430

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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: 20000201