EP0186797B1 - Novel cobalt-base superalloy and cast and welded industrial gas turbine components thereof - Google Patents
Novel cobalt-base superalloy and cast and welded industrial gas turbine components thereof Download PDFInfo
- Publication number
- EP0186797B1 EP0186797B1 EP85115301A EP85115301A EP0186797B1 EP 0186797 B1 EP0186797 B1 EP 0186797B1 EP 85115301 A EP85115301 A EP 85115301A EP 85115301 A EP85115301 A EP 85115301A EP 0186797 B1 EP0186797 B1 EP 0186797B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cobalt
- gas turbine
- superalloy
- industrial gas
- base superalloy
- 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
Links
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/07—Alloys based on nickel or cobalt based on cobalt
Definitions
- Cobalt-base superalloys having special utility in the production of industrial gas turbine hot gas path components because of their unique combination or properties including excellent hot corrosion resistance, creep rupture strength at high temperature, metallurgical stability, tensile ductility and weldability, are comprised of 0.3 to 0.6% carbon, 27-35% chromium, 9-16% nickel, 6-9% tungsten, 0.45 to 2.0% tantalum, up to 3.0% hafnium, up to 0.1 % niobium, up to 0.7% zirconium, not more than 2.0% iron, 1.5% manganese and silicon and 0.05% boron, balance cobalt and impurities, the carbide formers being selected to satisfy the following equation:
- This invention relates generally to the superalloy branch of the metallurgical art, and is more specifically concerned with new cobalt-base superalloys having an unique combination of properties and consequent special utility in the production of both cast articles and welded structures, and with novel industrial gas turbine hot gas path components of those new alloys.
- Cobalt-base superalloys disclosed and claimed in US-A-3,383,205 have superior oxidation and hot corrosion resistance and as a consequence have long been used extensively in commercial production of industrial gas turbine nozzles.
- one of those superalloys is the current first stage nozzle alloy of the Gas Turbine Division of General Electric Company, the assignee hereof.
- the creep rupture and fatigue strength of that alloy are marginal for new industrial gas turbine nozzle applications and in recognition of that fact, a program was launched to improve those properties without significantly diminishing the resistance of the superalloys either to oxidation or to hot corrosion.
- the present invention is a cobalt-base superalloy having an unique combination of properties at high temperature and consequent special utility in the production of industrial gas turbine hot gas path components, which alloy is comprised of 0.3-0.6% carbon, 27-35% chromium, 9-16% nickel, 6-9% tungsten, up to 3% hafnium, .45-2.0% tantalum, up to .7% zirconium, up to .5% titanium, up to 1 % niobium, manganese and silicon, up to .05% boron, up to 2.0% iron, remainder cobalt plus impurities.
- An additional important requirement is that the carbide-forming elements be so selected as to satisfy the relationship stated above and represented by the following equation:
- the present invention is a cast cobalt-base superalloy industrial gas turbine nozzle consisting of the new alloy set forth immediatley above. Also, in this aspect the invention takes the form of transition pieces and shrouds, and of a fabricated cobalt-base superalloy gas turbine combustion chamber comprising a plurality of sheets of the said new alloy rolled and formed in predetermined shape and assembled and welded together.
- the chromium content of these alloys is preferably targeted at 28-30% in recognition that departures in each direction can penalize alloy properties, specifically amounts less than about 27% result in loss of oxidation and hot corrosion resistance and amounts greater than about 35% result in loss of ductility without offsetting gain in either oxidation resistance or hot corrosion resistance.
- the cast and fabricated bodies of this invention being components of industrial gas turbines are quite different from aircraft jet engine components especially in respect to size and mass. Because of this, they represent problems unlike those of the relatively lighter weight counterparts such as marked cracking tendency associated with welding operations. This has significant implication for cast as well as fabricated industrial gas turbine components as it would obviously be highly desirable to be able to weld repair industrial gas turbine nozzles to avoid the time and expense of replacement. Gaining this advantage without forfeiting any other constitutes an important advance in the art. Likewise, the opportunity to build industrial gas turbine combustion chamber structures by welding preformed sheets or plates together which is enabled as a result of this invention, its alloys having excellent weldability, is an important new advance in the production of industrial gas turbines. In our practice of such welding operations as these we prefer to use the gas tungsten arc technique and equipment in general use in industry in the fabrication of both ferrous and nonferrous metal structures, including those of cobalt-base superalloys.
- the first stage nozzle 10 of an industrial gas turbine shown in Fig. 1 is a casting of our preferred alloy composition produced by the injection molding and investment casting technique in general use in the art. Also, the shape and size and the design details of nozzle 10 essentially duplicate those features of the present standard first stage nozzle. Transition piece 20 similarly resembles that which has long been in general use in industrial gas turbines differing importantly, however, in that it is constructed of parts of an alloy of this invention welded together to provide a strong crack-free assembly of integrally bonded elements. Thus, bracket 22 is fitted in place on body 23 and welded securely and fixed tightly thereto.
- the superalloys of this invention (Examples II and Example IIIC) have ultimate tensile strengths equal to or better than the commercial superalloy of Example I and have creep rupture strength substantially greater than that commercial superalloy. Further it is apparent from Table I that these new superalloys have good room temperature tensile elongation characteristics and as Table II shows and Fig. 3 graphically illustrates, the weldability of the superalloys of this invention is superior to commercial superalloys A and E and even spectacularly so in the case of the superalloy of Example II which as indicated above is our present preferred embodiment of the invention.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Materials For Medical Uses (AREA)
Description
- Cobalt-base superalloys having special utility in the production of industrial gas turbine hot gas path components because of their unique combination or properties including excellent hot corrosion resistance, creep rupture strength at high temperature, metallurgical stability, tensile ductility and weldability, are comprised of 0.3 to 0.6% carbon, 27-35% chromium, 9-16% nickel, 6-9% tungsten, 0.45 to 2.0% tantalum, up to 3.0% hafnium, up to 0.1 % niobium, up to 0.7% zirconium, not more than 2.0% iron, 1.5% manganese and silicon and 0.05% boron, balance cobalt and impurities, the carbide formers being selected to satisfy the following equation:
- This invention relates generally to the superalloy branch of the metallurgical art, and is more specifically concerned with new cobalt-base superalloys having an unique combination of properties and consequent special utility in the production of both cast articles and welded structures, and with novel industrial gas turbine hot gas path components of those new alloys.
- Cobalt-base superalloys disclosed and claimed in US-A-3,383,205 have superior oxidation and hot corrosion resistance and as a consequence have long been used extensively in commercial production of industrial gas turbine nozzles. In fact, one of those superalloys is the current first stage nozzle alloy of the Gas Turbine Division of General Electric Company, the assignee hereof. The creep rupture and fatigue strength of that alloy, however, are marginal for new industrial gas turbine nozzle applications and in recognition of that fact, a program was launched to improve those properties without significantly diminishing the resistance of the superalloys either to oxidation or to hot corrosion. While the resulting superalloys met those objectives as a consequence of their relatively high carbon contents (0.40 to 0.50%), they were still not the answer to the problem because of their inferior weldability and low tensile ductility. Moreover cobalt base alloys of the claimed type for structural parts of gas turbines are disclosed in US-A-3549356 and GB-A-891550.
- Through our discoveries and new concepts detailed below, we have created new cobalt-base super-alloys having a previously unobtainable combination of desirable properties. Thus we have found the way to avoid having to make the trade-offs of desirable properties exemplified by the problem mentioned above. This invention in providing the answers to that problem embodies those discoveries and new concepts of ours and they are epitomized in the appended claims directed both to alloy compositions and to articles of manufacture of those compositions.
- One of our concepts upon which this invention is based is that weldability and tensile ductility of cobalt-base superalloys need not be significantly compromised in order to increase creep strength and fatigue strength very substantially. In particular, beneficial effects of increased carbon content can be obtained without the normally attending detrimental effects thereof by addition of one or more of the following strong monocarbide MC-formers: hafnium, tantalum, niobium, zirconium and titanium.
- We have discovered that these additive elements are effective for this purpose in relatively small amounts and that within certain limits they can be used singly or together in any desired combination to secure consistently the new results and advantages of this invention.
- Still further, we have found that while the more reactive elements such as titanium and zirconium, and to some extent hafnium, are suitable for vacuum melting operations, it is preferable to substitute niobium for them in melting operations carried out in air. In addition, it is important that the amount of columbium not exceed about one percent because of its detrimental effect on superalloy hot corrosion resistance. For the same reason columbium is perferably not used in vacuum melting practice involving the new superalloys of this invention.
- In making this invention, we have established that the beneficial effects of carbon on creep strength and fatigue strength are not forfeited to any appreciable degree as a result of isolating the carbon in the form of monocarbide throughout the grains and in the grain boundaries of the superalloy. Further, we have established that such segregation and isolation of carbon results in good weldability, metallurgical stability and tensile ductility, all of which are normally adversely affected by carbon in proportions preferred in accordance with this invention.
- We have further discovered that the new results and advantages of this invention can consistently be obtained only through the use of at least 0.45% tantalum, and that while selection of other elements of the monocarbide MC-carbide former group is a matter of choice for the operator as to kind, the total amounts used are critically important. Thus the balance between the carbon content of the alloy and the total of those elements expressed as the ratio of the sum of the atomic percent of those elements to the atomic percent of carbon must be within the range of 0.4 to 0.8. In the superalloy of our present preference that ratio is 0.62.
- Briefly described in its composition of matter aspect, the present invention is a cobalt-base superalloy having an unique combination of properties at high temperature and consequent special utility in the production of industrial gas turbine hot gas path components, which alloy is comprised of 0.3-0.6% carbon, 27-35% chromium, 9-16% nickel, 6-9% tungsten, up to 3% hafnium, .45-2.0% tantalum, up to .7% zirconium, up to .5% titanium, up to 1 % niobium, manganese and silicon, up to .05% boron, up to 2.0% iron, remainder cobalt plus impurities. An additional important requirement is that the carbide-forming elements be so selected as to satisfy the relationship stated above and represented by the following equation:
- Similarly described in its article-of-manufacture aspect, the present invention is a cast cobalt-base superalloy industrial gas turbine nozzle consisting of the new alloy set forth immediatley above. Also, in this aspect the invention takes the form of transition pieces and shrouds, and of a fabricated cobalt-base superalloy gas turbine combustion chamber comprising a plurality of sheets of the said new alloy rolled and formed in predetermined shape and assembled and welded together.
- In the drawings accompanying and forming a part of this specification,
- Fig. 1 is a view in perspective of an industrial gas turbine nozzle of this invention;
- Fig. 2 is a Larson-Miller plot of the stress-rupture properties of an alloy of US-A-3,383,205 and one of this invention;
- Fig. 3 is a chart bearing curves illustrating varestraint welding test results of tests on five alloys of this invention and two prior art alloys including that of US-A-3,383,205 treated in Fig. 2, total crack length in mils being plotted against percent augmented strain; and,
- Fig. 4 is a view in perspective of an industrial gas turbine transition piece of this invention.
- While our present preference is to prepare these new alloys by the vacuum melting and vacuum casting procedure, we alternatively contemplate using the air melting, air casting approach. Additions of hafnium, titanium, zirconium and tantalum are made in the former while columbium and tantalum and optionally hafnium are employed in the air melting case. In any event the amounts of these additives used in producing the alloys of this invention are carefully controlled to insure that the cast of fabricated products of these alloys have all the desirable characteristics described above. Likewise, the best practice along each of of these two lines involves controlling the amounts of the elements other than these several monocarbide MC-carbide formers as to both the ranges of the major constituents and the maximum amounts of the minor or impurity elements such as iron, manganese, silicon and boron.
- As stated above and shown below, the consequence of failure to exert such control is the loss of one or more of the important advantages of this invention. The excellent weldability of these new alloys are forfeited, for example, when the amounts of monocarbide MC-carbide formers used are not in balance with the alloy carbon content as described above and set forth in the appended claims. Likewise, while we prefer to use niobium in air melting, air casting practice because it is not as reactive and so doesn't tend to oxidize as readily as titanium, zirconium or even hafnium, care is taken not to use an amount greater than about one percent because niobium detrimentally affects hot corrosion resistance. Further in this regard the chromium content of these alloys is preferably targeted at 28-30% in recognition that departures in each direction can penalize alloy properties, specifically amounts less than about 27% result in loss of oxidation and hot corrosion resistance and amounts greater than about 35% result in loss of ductility without offsetting gain in either oxidation resistance or hot corrosion resistance.
- The cast and fabricated bodies of this invention being components of industrial gas turbines are quite different from aircraft jet engine components especially in respect to size and mass. Because of this, they represent problems unlike those of the relatively lighter weight counterparts such as marked cracking tendency associated with welding operations. This has significant implication for cast as well as fabricated industrial gas turbine components as it would obviously be highly desirable to be able to weld repair industrial gas turbine nozzles to avoid the time and expense of replacement. Gaining this advantage without forfeiting any other constitutes an important advance in the art. Likewise, the opportunity to build industrial gas turbine combustion chamber structures by welding preformed sheets or plates together which is enabled as a result of this invention, its alloys having excellent weldability, is an important new advance in the production of industrial gas turbines. In our practice of such welding operations as these we prefer to use the gas tungsten arc technique and equipment in general use in industry in the fabrication of both ferrous and nonferrous metal structures, including those of cobalt-base superalloys.
- The
first stage nozzle 10 of an industrial gas turbine shown in Fig. 1 is a casting of our preferred alloy composition produced by the injection molding and investment casting technique in general use in the art. Also, the shape and size and the design details ofnozzle 10 essentially duplicate those features of the present standard first stage nozzle.Transition piece 20 similarly resembles that which has long been in general use in industrial gas turbines differing importantly, however, in that it is constructed of parts of an alloy of this invention welded together to provide a strong crack-free assembly of integrally bonded elements. Thus,bracket 22 is fitted in place onbody 23 and welded securely and fixed tightly thereto. - Those skilled in the art will gain a further and better understanding of this invention and its important new advantages and results from the following illustrative, but not limiting, examples.
-
- This superalloy is disclosed and claimed in US-A-3,383,205 and has long been in general use in the production of industrial gas turbine hot stage components, particularly cast non-rotating parts such as first stage nozzles.
- The cast test specimens were subjected to standard tensile, creep rupture and varestraint weldability tests, the tensile and creep rupture data being set out in Table I and the varestraint data illustrated in Fig. 2. Curve A of Fig. 2 illustrates the Larson-Miller data and curve AA of Fig. 3 represents the varestraint data.
-
- The resulting test data are set forth in Tables 1 and 2 for a ready comparison with those of Example I and those detailed below. Curve B of Fig. 2 illustrates the Larson-Miller data and curve BB of Fig. 3 represents the varestraint data. Further, this superalloy was found on the performance of standard tests to have the superior oxidation and hot corrosion resistance of the cobalt-base alloy of Example I.
-
- Again the test data developed in measuring the properties of this alloy as described above are stated in Tables 1 and 2.
-
- In regard to the tests carried out in the course of this experimental work to measure the properties of these various alloy compositions, as indicated above, standard test procedures were followed in every instance and the same procedures were applied for each respective alloy in the several tests so that comparisons could be made directly and conclusions could be drawn from the resulting data which were reliable. The ASTM procedures were used, therefore, in the tensile and creep rupture tests and in the case of the varestraint test the procedure followed was that described in Welding Research Council Bulletin 280 in the article entitled "The Varestraint Test". C.D. Ludlum, et al, August 1982.
- As evident from Table I, the superalloys of this invention (Examples II and Example IIIC) have ultimate tensile strengths equal to or better than the commercial superalloy of Example I and have creep rupture strength substantially greater than that commercial superalloy. Further it is apparent from Table I that these new superalloys have good room temperature tensile elongation characteristics and as Table II shows and Fig. 3 graphically illustrates, the weldability of the superalloys of this invention is superior to commercial superalloys A and E and even spectacularly so in the case of the superalloy of Example II which as indicated above is our present preferred embodiment of the invention. It will also be noted that as indicated in parentheses on that chart, the superalloys of this invention set forth in Examples II and III have carbideformer-carbon atomic percent ratios within the above prescribed critical range of 0.4 to 0.8, while the prior art alloys of Examples I and IV do not come close to meeting that important requirement.
Claims (5)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US67811884A | 1984-12-04 | 1984-12-04 | |
US678118 | 1984-12-04 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0186797A1 EP0186797A1 (en) | 1986-07-09 |
EP0186797B1 true EP0186797B1 (en) | 1989-06-21 |
Family
ID=24721479
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP85115301A Expired EP0186797B1 (en) | 1984-12-04 | 1985-12-03 | Novel cobalt-base superalloy and cast and welded industrial gas turbine components thereof |
Country Status (6)
Country | Link |
---|---|
EP (1) | EP0186797B1 (en) |
JP (1) | JPS61149450A (en) |
CN (1) | CN1011984B (en) |
DE (1) | DE3571146D1 (en) |
IN (1) | IN164571B (en) |
NO (1) | NO166542C (en) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2769024A1 (en) * | 1997-09-29 | 1999-04-02 | Saint Gobain Isover | COBALT-BASED ALLOY, ARTICLE PRODUCED FROM THE ALLOY AND METHOD FOR MANUFACTURING THE SAME |
US8252376B2 (en) * | 2001-04-27 | 2012-08-28 | Siemens Aktiengesellschaft | Method for restoring the microstructure of a textured article and for refurbishing a gas turbine blade or vane |
DE602004022327D1 (en) | 2003-11-25 | 2009-09-10 | Kyocera Corp | CERAMIC HEATING ELEMENT AND MANUFACTURING METHOD THEREFOR |
US6983599B2 (en) * | 2004-02-12 | 2006-01-10 | General Electric Company | Combustor member and method for making a combustor assembly |
US20070017906A1 (en) * | 2005-06-30 | 2007-01-25 | General Electric Company | Shimmed laser beam welding process for joining superalloys for gas turbine applications |
CN102021558B (en) * | 2009-09-09 | 2012-07-11 | 沈阳大陆激光技术有限公司 | Alloy powder for circulating fluidized bed boiler water wall tube laser cladded coating |
CN108070742A (en) * | 2016-11-15 | 2018-05-25 | 中国科学院金属研究所 | A kind of gas turbine guide vane cobalt base superalloy and its preparation method and application |
EP3650138B1 (en) * | 2018-11-06 | 2021-10-20 | Hamilton Sundstrand Corporation | Cold spray forming |
EP3677697A1 (en) * | 2019-01-07 | 2020-07-08 | Siemens Aktiengesellschaft | Co-alloy for additive manufacturing and method |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB891550A (en) * | 1959-08-28 | 1962-03-14 | Sierra Metals Corp | Metal alloys |
US3383205A (en) * | 1964-12-14 | 1968-05-14 | Gen Electric | Cobalt base alloys |
US3549356A (en) * | 1969-01-06 | 1970-12-22 | Gen Electric | High temperature corrosive resistant cobalt-base alloys |
US3582320A (en) * | 1969-12-22 | 1971-06-01 | Robert B Herchenroeder | Cobalt base alloy |
US3933484A (en) * | 1974-05-31 | 1976-01-20 | Owens-Corning Fiberglas Corporation | Cobalt-base alloy |
JPS5582741A (en) * | 1978-12-15 | 1980-06-21 | Hitachi Ltd | High-strength high-toughness cobalt alloy |
JPS5582744A (en) * | 1978-12-15 | 1980-06-21 | Hitachi Ltd | High-strength high-toughness cobalt alloy |
JPS5582743A (en) * | 1978-12-15 | 1980-06-21 | Hitachi Ltd | High-strength high-toughness cobalt alloy |
-
1985
- 1985-11-14 CN CN85109085A patent/CN1011984B/en not_active Expired
- 1985-11-18 IN IN818/CAL/85A patent/IN164571B/en unknown
- 1985-11-28 JP JP60266298A patent/JPS61149450A/en active Granted
- 1985-12-03 EP EP85115301A patent/EP0186797B1/en not_active Expired
- 1985-12-03 NO NO854859A patent/NO166542C/en unknown
- 1985-12-03 DE DE8585115301T patent/DE3571146D1/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
EP0186797A1 (en) | 1986-07-09 |
IN164571B (en) | 1989-04-15 |
JPH0459378B2 (en) | 1992-09-22 |
CN1011984B (en) | 1991-03-13 |
NO166542B (en) | 1991-04-29 |
NO166542C (en) | 1991-08-07 |
NO854859L (en) | 1986-06-05 |
JPS61149450A (en) | 1986-07-08 |
CN85109085A (en) | 1986-08-20 |
DE3571146D1 (en) | 1989-07-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US4078922A (en) | Oxidation resistant cobalt base alloy | |
EP0455752B1 (en) | Iron aluminide alloys with improved properties for high temperature applications | |
US3201233A (en) | Crack resistant stainless steel alloys | |
EP0269973A2 (en) | Carburization resistant alloy | |
GB2205857A (en) | Superplastic hot working method for duplex-phase stainless steel | |
US4533414A (en) | Corrosion-resistance nickel alloy | |
EP0186797B1 (en) | Novel cobalt-base superalloy and cast and welded industrial gas turbine components thereof | |
CA2146534C (en) | Heat-resistant nickel-based alloy excellent in weldability | |
US4938805A (en) | Novel cobalt-base superalloy and cast and welded industrial gas turbine components thereof and method | |
GB2116211A (en) | Oxidation resistant nickel alloy | |
US5882586A (en) | Heat-resistant nickel-based alloy excellent in weldability | |
US4585478A (en) | Heat resisting steel | |
US3304176A (en) | Nickel base alloy | |
EP0087923B1 (en) | Weldable oxide dispersion strengthened iron based alloys | |
WO1992003584A1 (en) | Controlled thermal expansion alloy and article made therefrom | |
EP0444483B1 (en) | Cobalt-base wrought alloy compositions and articles | |
US5223214A (en) | Heat treating furnace alloys | |
US3094414A (en) | Nickel-chromium alloy | |
US3984239A (en) | Filler metal | |
CA1260292A (en) | Cobalt-base superalloy and cast and welded industrial gas turbine components thereof | |
US3416916A (en) | Ductile cobalt-base alloy | |
US3304177A (en) | Method of producing la containing alloys | |
US4374084A (en) | Alloy composition suitable for use in making castings, and a casting made therefrom | |
US3393999A (en) | High temperature nickel base alloys | |
US3655462A (en) | Cast nickel-base alloy |
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: A1 Designated state(s): DE FR GB IT NL |
|
17P | Request for examination filed |
Effective date: 19861223 |
|
17Q | First examination report despatched |
Effective date: 19880212 |
|
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 IT NL |
|
REF | Corresponds to: |
Ref document number: 3571146 Country of ref document: DE Date of ref document: 19890727 |
|
ET | Fr: translation filed | ||
ITF | It: translation for a ep patent filed |
Owner name: SAIC BREVETTI S.R.L. |
|
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 | ||
ITTA | It: last paid annual fee | ||
REG | Reference to a national code |
Ref country code: GB Ref legal event code: IF02 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: NL Payment date: 20021121 Year of fee payment: 18 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20040701 |
|
NLV4 | Nl: lapsed or anulled due to non-payment of the annual fee |
Effective date: 20040701 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20041124 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20041217 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20050131 Year of fee payment: 20 |
|
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 EXPIRATION OF PROTECTION Effective date: 20051202 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: PE20 |