EP0054116B1 - Anordnung eines Turbinenstators und Methode zu seiner Montage und Demontage - Google Patents

Anordnung eines Turbinenstators und Methode zu seiner Montage und Demontage Download PDF

Info

Publication number
EP0054116B1
EP0054116B1 EP19810107994 EP81107994A EP0054116B1 EP 0054116 B1 EP0054116 B1 EP 0054116B1 EP 19810107994 EP19810107994 EP 19810107994 EP 81107994 A EP81107994 A EP 81107994A EP 0054116 B1 EP0054116 B1 EP 0054116B1
Authority
EP
European Patent Office
Prior art keywords
diaphragm
housing
stator blade
blade assembly
casing
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.)
Expired
Application number
EP19810107994
Other languages
English (en)
French (fr)
Other versions
EP0054116A1 (de
Inventor
Carl H. Geary
Arthur J. Miller
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.)
Carrier Corp
Original Assignee
Carrier Corp
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 Carrier Corp filed Critical Carrier Corp
Publication of EP0054116A1 publication Critical patent/EP0054116A1/de
Application granted granted Critical
Publication of EP0054116B1 publication Critical patent/EP0054116B1/de
Expired legal-status Critical Current

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • This invention generally relates to rotary machines, and more specifically to stator blade assemblies thereof.
  • rotor or stator blades of a rotary machine such as a compressor or expander must be removed from the machine for cleaning, maintenance, or replacement.
  • rotary machines are often used with fluids containing a significant amount of particulates or debris. Over an extended period, these particulates and debris may accumulate on or erode the blade surfaces, necessitating periodic removal of the rotor or stator blades from the machine to clean or replace the blade surfaces. Routine inspection and maintenance, for example to repair or realign a rotor seal or blade, may also require removal of the rotor or stator blades from the machine.
  • U.S. Patent 3,628,884 discloses a method of securing stator blades in a turbomachine for a different application.
  • a string is provided including a compressor and combustion section as well as a turbine.
  • a large section of the turbine casing is removed to expose the turbine blades. Prior to removal certain bolts must be in the appropriate position.
  • the turbomachine of the present invention is designed to facilitate assembly and servicing. To this end the rotor is removed axially from the machine.
  • the structure of U.S. Patent 3,628,884 prevents axial displacement of the rotor due to the other contained components, furthermore the connecting means by which the relative position of the stator blade assembly is determined, are fixed directly to the outer casing.
  • the present invention relates to a turbomachine having a stator blade assembly which may be easily installed in and removed from the turbomachine.
  • a turbomachine including bladed rotor means having axially spaced first and second stage rotor blade rows; an inlet duct for directing a fluid past the bladed rotor means, a fluid casing for receiving fluid flowing past the bladed rotor means, and a stator blade assembly including stator blade means axially located between the first and second stage rotor blade rows, the inlet duct including an outwardly projecting duct flange; the fluid casing including an outwardly projecting casing flange; the stator blade assembly having outwardly projecting flanges positioned contiguous to the duct and casing flanges, and wherein there is provided means for releasably securing the stator blade assembly to the fluid casing and the inlet duct; the stator blade assembly further including a generally annular housing and a generally annular diaphragm disposed within the housing and supporting said stator blades, and further characterized in that the housing includes separable upper and lower
  • Machine 10 such as a multi-stage turbine incorporating teachings of the present invention.
  • Machine 10 includes an axially extending rotor 12, first and second stage rotor blades 14 and 16, inlet duct 18, fluid casing 20, and stator blade assembly 22.
  • Assembly 22 comprises housing 24, diaphragm 26, stator blades 30, and connecting means 32, discussed in greater detail below.
  • Fluid casing 20 annularly extends around rotor 12, and rotor blades 14 and 16 are rigidly secured to rotor 12 and radially extend outward therefrom, forward to the left as viewed in Figure 1, of the fluid casing.
  • two axially spaced sets of rotor blades 14 and 16 are shown in Figure 1, it will be apparent to those skilled in the art that the present invention may be employed with a rotary compressor or expander having more than two spaced sets of rotor blades.
  • Housing 24 is located between fluid casing 20 and inlet duct 18 and annularly extends around rotor blades 14 and 16, stator blades 30, and diaphragm 26.
  • housing 24 is comprised of separable annular rings 34 and 36, and these rings are comprised of separable upper and lower sections, which preferably are both of semi-annular form disengageably joined together, for example by bolts, along adjacent horizontal flanges.
  • band 34 includes top section 34a and bottom section 34b
  • band 36 includes top section 36a and bottom section 36b. Rings 34 and 36 are releasably joined together, to fluid casing 20, and to inlet duct 18.
  • outwardly extending flange portion 38 of band 34 is bolted to contiguous flange portion 40 of inlet duct 18; back, outwardly extending flange portion 42 of band 36 is bolted to contiguous flange portion 44 of fluid casing 20; and bands 34 and 36 are bolted together along adjacent, intermediate flanges 46 and 48.
  • seals may be disposed between contiguous surfaces of inlet duct 18, fluid casing 20, and housing 24 to inhibit or to retard fluid flow between these surfaces.
  • Diaphragm 26 is disposed within housing 24 and preferably is radially spaced therefrom to allow radial expansion and contraction of the diaphragm.
  • Diaphragm 26 annularly extends around rotor blades 14 and 16 and comprises separable upper and lower diaphragm sections 50 and 52, which also preferably are both of semi-annular form disengageably joined together along a horizontal split line in any suitable manner such as by bolts.
  • Stator blades 30 are secured to diaphragm 26 in any conventional manner and radially extend inward therefrom, between rotor blade rows 14 and 16.
  • a horizontal split sealing member 54 is conventionally secure to stator blades 30 and radially extends inward therefrom substantially to impeller rotor 12 to inhibit fluid flow through the area between the rotor and the stator blades.
  • Connecting means 32 releasably connects diaphragm 26 to housing 24 and limits relative rotation therebetween.
  • connecting means 32 includes inside rib portion 56 of housing band 36, annular ring 58, and one or more pins 60.
  • Ring 58 which may be integral with rib 56, axially extends from the rib, radially outside diaphragm 26, and pins 60 extend through ring 58 into engagement with diaphragm 26 to prevent substantially relative rotation between the diaphragm and ring 58.
  • ring 58 defines a plurality of pin holes 62, for example 8 or 12 equally spaced about the ring; diaphragm 26 defines a like number of diaphragm sockets 64, with sockets 64 aligned with pin holes 62; and pins 60 extend through holes 62 and into sockets 64 to engage securely the diaphragm.
  • set screws 66 may be threaded into diaphragm 26 to engage cooperating annular recesses (not shown) of pins 60, releasably maintaining pins 60 in position, as shown in Figure 1.
  • upper portions of pins 60 may define threaded pin sockets 68 to facilitate moving the pins into and out of diaphragm sockets 64.
  • abutting contact between pins 60 and the surfaces of ring 58 defining pin holes 62 substantially prevents rotational or axial movement of diaphragm 26.
  • Rearward axial movement of diaphragm 26 is further prevented by rib 56 or, preferably, by a seal (not shown) which may be axially located between rib 56 and outside flange 70 of the diaphragm.
  • rib 56 provides radial support for diaphragm 26 within housing 24.
  • housing 24 may form an integral portion of inlet duct 18, and preferably the housing comprises an integral band portion encircling diaphragm 26 and stator blades 30.
  • diaphragm 26 and stator blades 30 are supported within housing 24 via inside rib portion 80 of fluid casing 20, annular ring 82, and one or more pins 60.
  • Annular ring 82 is separable from rib portion 80, and preferably is bolted thereto.
  • ring 82 preferably defines a plurality of pin holes 62, with pins 60 extending through these holes and into diaphragm sockets 64, and set screws 66 may be used to maintain releasably pins 60 in sockets 64.
  • a fluid is induced to flow through inlet duct 18 and past blades 14 and 16. If machine 10 is a compressor, then rotor blade rows 14 and 16 are rotated to compress the fluid flowing therepast. Alternately, if machine 10 is an expander, then the fluid causes rotation of blade rows 14 and 16. In either case, the fluid flows past blades 14 and 16, through fluid casing 20, and thence is discharged from machine 10.
  • stator blade assembly 22 described above may be both removed from and installed in machine 10 in a relatively fast and inexpensive manner.
  • top and bottom sections 34a and 34b of housing ring 34 are disconnected from each other. Then housing band 34 is disconnected from inlet duct 18 and housing band 36, and band 34 is removed from machine 10. Set screws 66 are loosened or removed and pins 60 are pulled out of diaphragm sockets 64, freeing housing band 36 from diaphragm 26. Top and bottom sections 36a and 36b of housing ring 36 are disconnected from each other, the whole band 36 is disconnected from casing 20, and band 36 is removed. With housing 24 thus removed, top and bottom sections 50 and 52 of diaphragm 26 are disengaged from each other and taken away from machine 10.
  • stator housing assembly 22 may be removed without removing either inlet duct 18 or fluid casing 20.
  • FIG. 1A to disassemble stator blade assembly 22 shown therein, flanges 42 and 44 are first disconnected, freeing housing 24 and inlet duct 18 from fluid casing 20. Inlet duct 18, including annular housing portion 24, is then removed. Set screws 66 are loosened or removed, and then pins 60 are removed. Ring 82 is then disconnected from rib 80 and removed. Top and bottom sections 50 and 52 of diaphragm 26 are then disengaged from each other and radially moved out of machine 10.
  • stator blade assembly 22 may be utilized to remove stator blade assembly 22 from machine 10, and one arrangement for removing and installing the stator blade assembly 22 shown in Figure 1B will be described herein in detail.
  • posts 102 including support platforms 104 and top flanges 106, are positioned adjacent to the stator blade assembly, with top flanges 106 overlaying portions of flanges 108 of lower housing section 24b. Flanges 106 and 108 are then secured together by any conventional means wherein posts 102 provide additional support for stator blade assembly 22.
  • guide rods 110 are lowered through aligned apertures defined by flanges 106 and 108 into abutting contact with support platforms 104, wherein the guide rods help to guide vertical movement of lower diaphragm section 52 and lower housing section 24b.
  • inlet duct 18 is disengaged from the stator blade assembly and removed in any suitable manner, for example by an overhead crane.
  • Pins 60 connecting upper diaphragm section with upper housing section 24a are removed, freeing this housing section from diaphragm 26.
  • Upper housing section 24a is then disengaged from lower housing section 24b and from fluid casing 20 and removed in any conventional manner, again for example by an overhead crane.
  • Upper diaphragm section 50 is then disengaged from lower diaphragm section 52 and also removed in any conventional manner such as by an overhead crane.
  • Rails 112 are positioned adjacent machine 10, extending forward thereof between posts 102. Screw jacks 114, having top plates 116, are placed on platforms 104 of posts 102, and the screw jacks are extended to bring plates 116 into abutting contact with flanges 108 of lower housing section 24b. Lower housing section 24b is disengaged from fluid casing 20, and flanges 108 are disengaged from flanges 106. Lower housing and diaphragm sections 24b and 52 are now free to move downward; and by retracting screw jacks 114, plates 116, housing section 24b, and diaphragm section 52 are lowered toward rails 112.
  • wheels 120,122, and 124 are secured to the lower housing section in any suitable manner to support diaphragm section 52 and housing section 24b for movement along the rails. With wheels 120,122, and 124 secured in place, screw jacks 114 are retracted to lower these wheels onto rails 112, as shown in Figures 4 and 5. It should be pointed out that preferably machine 10 and rails 112 are positioned on a baseplate having a recessed or lowered central portion, allowing the bottom of housing section 24b to extend lower than the bottom of rails 112 when wheels 120, 122, and 124 are lowered thereonto.
  • housing section 24b and diaphragm section 52 are then manually moved along the rails, away from machine 10. Housing section 24b and diaphragm section 52 may thence be transported to a remove location in any conventional manner. Once removed from machine 10, pin covers 72 and pins 60 connecting lower housing section 24b with the lower diaphragm section 52 may be removed, separating sections 24b and 52.
  • Lower diaphragm section 52 with a plurality of stator blades 30 secured thereto and radially extending inward therefrom and with the lower half of sealing member 54 secured to and radially extending inward from these stator blades is positioned within lower housing section 24b, slightly spaced therefrom.
  • Diaphragm and housing sections 52 and 24b are connected together by inserting pins 60 and into diaphragm sockets 64.
  • Wheels 120, 122, and 124 are secured to lower housing section 24b.
  • Diaphragm and housing sections 52 and 24b and wheels 120,122, and 124 are mounted on rails 112 and moved therealong until the lower diaphragm and housing sections are adjacent fluid casing 20 and below rotor 12, as shown in Figure 5.
  • Posts 102 are located outside rails 112, with flanges 108 of lower housing section 24b directly between support platforms 104 and top flanges 106.
  • Guide rods 110 are inserted through flanges 108 and 106.
  • Screw jacks 114 are positioned on platforms 104 and extended to bring plates 116 into abutting contact with flanges 108 and raise lower housing section 24b off rails 112. Wheels 120, 122, and 124 are removed from lower housing section 24b.
  • Screw jacks 112 are extended to raise housing section 24b and diaphragm section 52 into their assembled positions and bring flanges 108 into abutting contact with top flanges 106. Flanges 106 and 108 are joined together, guide rods 110 are removed, and lower housing section 24b is disengageably secured to fluid casings 20. Rails 112 may be removed.
  • Upper diaphragm section 50 also with a plurality of stator blades 30 secured thereto and with the upper half of sealing member 54 secured to these stator blades, is positioned, for example via an overhead crane, over lower diaphragm section 52 and rotor 12, and the upper and lower diaphragm sections are disengageably secured together, forming diaphragm 26.
  • Upper housing section 24a is positioned over diaphragm 26, again for example by an overhead crane, and disengageably secured to both lower housing section 24b and fluid casing 20.

Landscapes

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

Claims (2)

1. Turbomaschine mit einer schaufelntragenden Läuferanordnung (12, 14, 16), die je einen Laufschaufelkranz (14, 16) einer ersten und einer zweiten Stufe besitzt, die im Axialabstand voneinander angeordnet sind, ferner mit einem Zuleitungsrohr (18) zum Vorbeiführen eines Fluids an der schaufeltragenden Läuferanordnung, einem Fluidgehäuse (20) zum Empfangen von Fluid, das an der schaufeltragenden Läuferanordnung (12, 14, 16) vorbeiströmt, und einer Leitschaufelanordnung (22) mit Leitschaufeln (30), die axial zwischen den Laufschaufelkränzen (14, 16) der ersten und der zweiten Stufe angeordnet sind, wobei das Zuleitungsrohr (18) einen auswärts vorstehenden Rohrflansch (40) besitzt, das Fluidgehäuse (20) einen auswärts vorstehenden Gehäuseflansch (44) besitzt, die Leitschaufelanordnung (22) auswärts vorstehende Flansche (38, 42) besitzt, die den Rohrflansch (40) und den Gehäuseflansch (44) berühren, eine Einrichtung zum lösbaren Befestigen der Leitschaufelanordnung (22) an dem Fluidgehäuse (20) und dem Zuleitungsrohr (18) vorgesehen ist, die Leitschaufelanordnung ferner ein allgemein ringförmiges Gehäuse (24) und eine im dem ringförmigen Gehäuse (24) angeordnete und die Leitschaufeln tragende, allgemein ringförmige Membran (26) besitzt, das ringförmige Gehäuse (24) einen oberen (24a) und einen unteren (24b) Gehäuseteil besitzt, die voneinander trennbar sind, sowie einen Vorderteil (34) und einen hinteren Teil (36), die voneinander trennbar sind, die Membran (26) einen oberen (50) und einen unteren (52) Membranteil besitzt, die voneinander trennbar sind, und eine Verbindungseinrichtung (32) vorgesehen ist, die einen ringförmigen Rippenteil (56) besitzt, der von dem ringförmigen Gehäuse (24) radial einwärts vorsteht, dadurch gekennzeichnet, daß eine Ringleiste (58) vorgesehen ist, die von dem ringförmigen Rippenteil (56) axial vorsteht, ferner eine Zapfenanordnung (60), die die Ringleiste radial durchsetzt und an der Membran (26) angreift, und eine Einrichtung zum lösbaren Halten der Zapfenanordnung (60) in der Ringleiste (58).
2. Turbomaschine nach Anspruch 1, dadurch gekennzeichnet, daß die Membran (26) eine Mehrzahl von Membranfassungen (64) und die Zapfenanordnung (60) eine Mehrzahl von Zapfen (60) aufweist, die sich radial in die Membranfassungen (64) erstrecken, und daß die Einrichtung zum lösbaren Halten der Zapfenanordnung (60) in der Ringleiste (58) eine Mehrzahl von Klemmschrauben (66) umfaßt, die sich in die Membran (26) erstrecken und an den Zapfen (60) angreifen.
EP19810107994 1980-10-30 1981-10-06 Anordnung eines Turbinenstators und Methode zu seiner Montage und Demontage Expired EP0054116B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US20209180A 1980-10-30 1980-10-30
US202091 1980-10-30

Publications (2)

Publication Number Publication Date
EP0054116A1 EP0054116A1 (de) 1982-06-23
EP0054116B1 true EP0054116B1 (de) 1986-09-10

Family

ID=22748465

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19810107994 Expired EP0054116B1 (de) 1980-10-30 1981-10-06 Anordnung eines Turbinenstators und Methode zu seiner Montage und Demontage

Country Status (3)

Country Link
EP (1) EP0054116B1 (de)
JP (1) JPS5925092B2 (de)
DE (1) DE3175308D1 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6224332B1 (en) * 1999-05-14 2001-05-01 General Electric Co. Apparatus and methods for installing, removing and adjusting an inner turbine shell section relative to an outer turbine shell section
US6287091B1 (en) * 2000-05-10 2001-09-11 General Motors Corporation Turbocharger with nozzle ring coupling
GB0811501D0 (en) * 2008-06-24 2008-07-30 Rolls Royce Plc A Method of forming a blade assembly
RU2451793C1 (ru) * 2010-12-20 2012-05-27 Открытое акционерное общество "Авиадвигатель" Турбина газотурбинного двигателя
DE102012211950A1 (de) * 2012-07-09 2014-05-08 Abb Turbo Systems Ag Abgasturbine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1692537A (en) * 1923-08-02 1928-11-20 Westinghouse Electric & Mfg Co Elastic-fluid turbine
GB679916A (en) * 1949-04-29 1952-09-24 Geoffrey Bertram Robert Feilde Improvements in gas turbines
US2828105A (en) * 1955-07-28 1958-03-25 Vickers Armstrongs Ltd Turbines
US2960306A (en) * 1956-01-16 1960-11-15 Gen Motors Corp Turbine
DE1045177B (de) * 1956-03-27 1958-11-27 Maschf Augsburg Nuernberg Ag Mehrstufige, axial durchstroemte Turbomaschine mit hohen Arbeitsmitteltemperaturen, insbesondere Gasturbine
US3169748A (en) * 1962-12-06 1965-02-16 Westinghouse Electric Corp Turbine apparatus
US3628884A (en) * 1970-06-26 1971-12-21 Westinghouse Electric Corp Method and apparatus for supporting an inner casing structure

Also Published As

Publication number Publication date
DE3175308D1 (en) 1986-10-16
EP0054116A1 (de) 1982-06-23
JPS57105504A (en) 1982-07-01
JPS5925092B2 (ja) 1984-06-14

Similar Documents

Publication Publication Date Title
CN1894485B (zh) 用于在轴向方向上拆下和安装燃气涡轮机的所选喷嘴段的装置和方法
US3628884A (en) Method and apparatus for supporting an inner casing structure
US3365173A (en) Stator structure
US3056583A (en) Retaining means for turbine shrouds and nozzle diaphragms of turbine engines
US7097415B2 (en) Low-pressure turbine of a turbomachine
US3746463A (en) Multi-casing turbine
US6202302B1 (en) Method of forming a stator assembly for rotary machine
CA1283609C (en) Thermal distortion isolation system for turbine blade rings
KR100814170B1 (ko) 증기 터빈용 증기로
US6752589B2 (en) Method and apparatus for retrofitting a steam turbine and a retrofitted steam turbine
US6722846B2 (en) Endface gap sealing of steam turbine bucket tip static seal segments and retrofitting thereof
CN102852566A (zh) 涡轮机密封系统
EP0054116B1 (de) Anordnung eines Turbinenstators und Methode zu seiner Montage und Demontage
EP1387043A2 (de) Abdichtungsvorrichtung für Dampfturbinenleitapparate und Nachrüstverfahren dafür
US7048504B2 (en) Machine stator and mounting and dismounting methods
DE2544953A1 (de) Axialstromturbine mit elastischem treibmittel
EP2692995B1 (de) Stationäre Gasturbinenmotor und Verfahren zur Durchführung von Instandhaltungsarbeit
RU2214514C2 (ru) Цилиндрическое опорное устройство для узла статора газотурбинного двигателя и узел статора газотурбинного двигателя
KR100228931B1 (ko) 복류식 증기 터어빈내의 이용되는 재가열 터브 및 이의 개장방법
US6109843A (en) Shield assembly for masking a stator of a rotary machine
US6648332B1 (en) Steam turbine packing casing horizontal joint seals and methods of forming the seals
US2972470A (en) Turbine construction
EP0051178B1 (de) Vorrichtung und Verfahren zum Montieren und Demontieren
US20200056481A1 (en) Method for maintaining a turbomachine
US1704481A (en) Rotary machine, particularly in centrifugal pump

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

Designated state(s): CH DE GB IT NL

17P Request for examination filed

Effective date: 19820824

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE GB IT LI NL

ITF It: translation for a ep patent filed

Owner name: ING. C. GREGORJ S.P.A.

REF Corresponds to:

Ref document number: 3175308

Country of ref document: DE

Date of ref document: 19861016

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: NL

Payment date: 19871031

Year of fee payment: 7

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

Ref country code: GB

Effective date: 19881006

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

Ref country code: LI

Effective date: 19881031

Ref country code: CH

Effective date: 19881031

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

Ref country code: NL

Effective date: 19890501

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee
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

Effective date: 19890701

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