EP1084368A1 - Fuel injector - Google Patents
Fuel injectorInfo
- Publication number
- EP1084368A1 EP1084368A1 EP99936291A EP99936291A EP1084368A1 EP 1084368 A1 EP1084368 A1 EP 1084368A1 EP 99936291 A EP99936291 A EP 99936291A EP 99936291 A EP99936291 A EP 99936291A EP 1084368 A1 EP1084368 A1 EP 1084368A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- mouth
- fuel nozzle
- nozzle
- fuel
- axis
- 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
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/48—Nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/38—Nozzles; Cleaning devices therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2206/00—Burners for specific applications
- F23D2206/10—Turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2210/00—Noise abatement
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
Definitions
- the invention relates to a fuel nozzle with an orifice area in which an orifice channel extends along a nozzle axis.
- the fuel nozzle is particularly suitable for liquid fuel.
- DE 32 35 080 AI describes a return injection nozzle in which two opposite liquid feeds open tangentially into a circular cylindrical swirl space.
- An injection channel is connected to the swirl chamber on the one hand and a return bore is connected on the other hand.
- the return injection nozzle is particularly suitable for the atomization of liquid fuel in gas turbine combustion chambers. Atomization is achieved in that fuel flows tangentially into the swirl chamber and is combined to form a main stream, a swirl being given to the main stream by a circular guide in the swirl chamber, which swirl is retained in the injection channel. As a result, the fuel jet fans out in a conical shape when the fuel exits the injection channel. On the other hand, fuel is returned via the return hole. While maintaining a constant fuel flow to the return injector, the amount of fuel injected is controlled by adjusting the amount of fuel returned.
- DE-OS 20 33 118 shows a gas burner for a gas-fired melting furnace.
- the gas burner In order to create a high flame temperature, the gas burner has a nozzle converging in the area of the mouth in the form of a gap. This ensures a high heat concentration.
- the object of the invention is to provide a fuel nozzle through which a combustion oscillation is at least reduced.
- this object is achieved by a fuel nozzle with a mouth area in which a mouth channel extends along a nozzle axis, which mouth channel does not end convergingly at a mouth edge, the mouth edge not being rotationally symmetrical about the nozzle axis.
- the mouth channel is non-converging in the mouth area, that is, it does not narrow, so that there is no pressure loss.
- the jet expands, ie a divergent, fanned out fuel jet is obtained.
- the divergent fuel jet is also not rotationally symmetrical.
- a distorted fuel cone is thus obtained, which is at least in two spatial directions has a different extent perpendicular to the beam direction.
- the spatial area in which the combustion takes place is distorted accordingly. This distortion of the combustion area influences the occurrence of a combustion oscillation.
- the area of combustion is shifted and pulled apart so that the acoustic system of burner and burner environment is detuned.
- the fuel nozzle and thus the emerging fuel cone are oriented in such a way that there is a reduction in the combustion oscillations up to hm to a complete suppression of the combustion oscillations.
- the rim of the mouth is preferably asymmetrical about the nozzle axis. This means that the edge of the mouth has to undergo a complete turn around the nozzle axis in order to come back into alignment with its original position.
- the rim of the mouth preferably has a double symmetry.
- the mouth edge is further preferably an ellipse or a rectangle, in particular with rounded corners.
- the two-fold symmetry means that the mouth edge is half a turn, i.e. 180 °, must experience in order to come with its original position in the cover.
- the edge of the mouth preferably corresponds to a contour which is formed by a rectangle and a circle, the center of the circle being on the center of gravity of the rectangle and projecting beyond the narrow side of the rectangle, and the contour being the outer edge of the rectangle and the circle. encloses it.
- the mouth edge preferably corresponds to a contour which is formed by two rectangles which are perpendicular to one another and have a common center of gravity, the contour enclosing the outer edge of both rectangles.
- the mouth channel preferably has a channel wall, each point of the channel wall having an axial distance from the nozzle axis and an axial position along the nozzle axis, and the axial distance being different for at least two points on the channel wall which have the same axial position.
- the axis spacing for points on the channel wall of the same axial position preferably changes continuously along a circumferential direction around the nozzle axis.
- the outlet channel is therefore not rotationally symmetrical about the nozzle axis.
- the mouth canal preferably widens towards the edge of the mouth.
- the rim of the mouth preferably has a notch.
- Such an indentation deflects fuel more strongly in the direction of the indentation when it emerges from the fuel nozzle than in the other directions of the mouth rim.
- Such a notch in turn ensures that fuel is not deflected to the same extent in all spatial directions.
- a distorted fuel cone is also formed.
- the fuel nozzle is preferably used in a burner for a gas turbine, in particular for a stationary gas turbine.
- FIG. 1 shows the side view of a fuel nozzle
- FIG. 2 shows the top view of the fuel nozzle of FIG. 1,
- FIG. 3 shows a plan view of a further fuel nozzle
- FIG. 4 shows a longitudinal section through the mouth area of a fuel nozzle
- FIG. 5 shows a top view of a further fuel nozzle
- Figure 6 is a side view of the fuel nozzle of Figure 5 and
- FIG. 7 shows a burner arrangement in an annular combustion chamber.
- FIG. 1 shows the side view of a fuel nozzle 1.
- a cylindrical nozzle body 3 tapers in a frustoconical section to a likewise cylindrical mouth area 5 with an end face 5A.
- a mouth channel 7 Directed along a nozzle axis 2 in the fuel nozzle 1 is a mouth channel 7, which ends at the end of the mouth region 5 with a mouth edge 9.
- a right-angled cut is made through the mouth area 5 so that a bevel 10 of the channel wall 8 of the mouth channel 7 is visible. Due to this bevel 10, the mouth rim 9 is not rotationally symmetrical about the nozzle axis 2. This is clear in FIG. 2.
- FIG. 2 shows a top view of the fuel nozzle 1 from FIG.
- the mouth edge 9 thus corresponds to a contour defined by the outer edge of a rectangle 11 and one Circle 13 is formed, the circle 13 with its center 15 is on the center of gravity 17 of the rectangle 11 and protrudes beyond the narrow side of the rectangle 11.
- a non-rotationally symmetrical, distorted fuel cone 33 is formed when fuel emerges from the fuel nozzle 1 (see also FIG. 4).
- This distorted fuel cone 33 means that the combustion area is also distorted.
- an acoustic interaction between the fuel nozzle 1 and its surroundings can be detuned in such a way that at most slight combustion vibrations are formed. Such suppression of combustion vibrations is possible particularly effectively if a plurality of fuel nozzles 1 are arranged in a combustion chamber.
- Such fuel nozzles 1 are preferably used in burners for gas turbines. The large-volume, high-energy burns in gas turbines can cause combustion vibrations, which not only cause considerable noise pollution, but also material damage.
- the fuel nozzle 1 also has a favorable influence on a nitrogen oxide reduction. Due to the distorted fuel cone, a better fine distribution of fuel can be achieved. In particular, there is a small droplet size for the fuel. The better distribution and the small droplet size of the fuel result in a comparison of the flame temperatures of the combustion. As a result, the maximum temperatures are not so high, which largely determine nitrogen oxide production. Furthermore, there is better mixing with water sprayed at the same time, if necessary. Water is injected to lower flame temperatures in the combustion, which reduces nitrogen oxide formation. With a non-rotationally symmetrical fuel cone 33 (see FIG. 4), there is a better penetration of fuel and water.
- FIG. 3 shows a top view of a fuel nozzle 1. The difference from the fuel nozzle 1 from FIGS. 1 and 2 is that the mouth rim 9 represents a contour which is formed by a rectangle 21 and a rectangle 23 perpendicular to it. The two rectangles 21, 23 have a common center of gravity 25, 27.
- FIG. 4 shows a longitudinal section through the mouth area 5 of a fuel nozzle 1.
- the fuel channel 7 widens towards the mouth rim 9.
- Two opposite points P1, P2 on the channel wall 8 have an axial position B along the nozzle axis 2 compared to an arbitrarily selected zero position.
- the point P1 is at a distance AI from the nozzle axis 2.
- the point P2 is at a distance A2 from the nozzle axis 2.
- the distance AI is greater than the distance A2.
- the respective distance A to the nozzle axis 2 changes continuously along a circumferential direction U around the nozzle axis 2, that is to say for points P on the channel wall 8, which all have the same axial position B along the nozzle axis 2.
- a non-rotationally symmetrical shape is impressed on a fuel flow in the mouth channel 7. This manifests itself when the fuel emerges from the orifice channel 7 in a non-rotationally symmetrical, distorted fuel cone 33. This has the advantages explained above with regard to the suppression of combustion vibrations and the reduction of nitrogen oxide emissions.
- FIG. 5 shows a top view of a fuel nozzle 1.
- FIG. 6 shows the fuel nozzle 1 of FIG. 5 in a side view.
- a semicylindrical notch 31 is cut or said, which cuts the mouth of the mouth channel 7.
- the rim of the mouth 9 also has a notch 31.
- Fuel is sprayed particularly far to the side at this notch 31. This results in a non-rotationally symmetrical fuel cone 33 for that from the fuel nozzle 1 leaking fuel. This in turn results in the advantages already mentioned for reducing combustion vibrations and nitrogen oxide emissions.
- FIG. 7 shows a burner arrangement 40 comprising a plurality of burners 42 in an annular combustion chamber 44 of a gas turbine, which is not shown in detail.
- the annular combustion chamber 44 is rotationally symmetrical about a combustion chamber axis 46. It has an inner wall 48 and an outer wall 50 which enclose an annular space 51. The inside of the outer wall 50 and the outside of the inner wall 48 are provided with a fire-resistant outer lining 52.
- the mouth edges 9 of the burner 42 are not rotationally symmetrical and irregularly oriented to one another. This results in a reduced tendency to form a combustion oscillation, since the combustion oscillations emanating from the individual burners 42 overlap irregularly and largely extinguish them in the process.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Gas Burners (AREA)
- Spray-Type Burners (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19825028 | 1998-06-04 | ||
DE19825028 | 1998-06-04 | ||
PCT/DE1999/001514 WO1999063268A1 (en) | 1998-06-04 | 1999-05-20 | Fuel injector |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1084368A1 true EP1084368A1 (en) | 2001-03-21 |
EP1084368B1 EP1084368B1 (en) | 2002-08-14 |
EP1084368B2 EP1084368B2 (en) | 2005-11-02 |
Family
ID=7869930
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99936291A Expired - Lifetime EP1084368B2 (en) | 1998-06-04 | 1999-05-20 | Fuel injector |
Country Status (5)
Country | Link |
---|---|
US (1) | US6676048B1 (en) |
EP (1) | EP1084368B2 (en) |
JP (1) | JP2002517700A (en) |
DE (1) | DE59902355D1 (en) |
WO (1) | WO1999063268A1 (en) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6805832B2 (en) * | 2001-07-09 | 2004-10-19 | Jonathan Mohler | Thermite torch cutting nozzle |
GB0219461D0 (en) * | 2002-08-21 | 2002-09-25 | Rolls Royce Plc | Fuel injection arrangement |
EP1730447A1 (en) * | 2004-03-31 | 2006-12-13 | Alstom Technology Ltd | Burner |
US7572997B2 (en) * | 2007-02-28 | 2009-08-11 | Caterpillar Inc. | EDM process for manufacturing reverse tapered holes |
US8146365B2 (en) * | 2007-06-14 | 2012-04-03 | Pratt & Whitney Canada Corp. | Fuel nozzle providing shaped fuel spray |
EP2423589A1 (en) * | 2010-08-27 | 2012-02-29 | Siemens Aktiengesellschaft | Burner assembly |
DE102012002465A1 (en) * | 2012-02-08 | 2013-08-08 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustor with unsymmetrical fuel nozzles |
GB201222304D0 (en) * | 2012-12-12 | 2013-01-23 | Rolls Royce Plc | A fuel injector and a gas turbine engine combustion chamber |
JP6563687B2 (en) * | 2014-06-18 | 2019-08-21 | リンナイ株式会社 | Double nozzle for the stove burner |
CA2968854A1 (en) * | 2014-12-04 | 2016-06-09 | Exxonmobil Research And Engineering Company | Fluid injection nozzle for fluid bed reactors |
WO2019177947A1 (en) * | 2018-03-12 | 2019-09-19 | Buckner Todd T | Drying system for car wash facility |
US20230204215A1 (en) * | 2021-12-29 | 2023-06-29 | General Electric Company | Fuel nozzle and swirler |
Family Cites Families (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2583726A (en) * | 1948-01-26 | 1952-01-29 | Chalom Joseph Aaron | Nozzle |
US3101906A (en) * | 1962-01-11 | 1963-08-27 | Carl R Webber | Spray nozzle |
US3521824A (en) * | 1968-10-11 | 1970-07-28 | Delavan Manufacturing Co | Air-liquid flat spray nozzle |
DE2033118A1 (en) | 1970-07-03 | 1972-01-05 | Pensenskij Kompressornyj Sawod | Gas burner |
US3638865A (en) * | 1970-08-31 | 1972-02-01 | Gen Electric | Fuel spray nozzle |
DE2739102A1 (en) * | 1977-08-30 | 1979-03-15 | Patra Patent Treuhand | Variable output welding torch - has non-circular discharge orifices to elongate, flatten, flame |
DD134976B1 (en) * | 1978-03-16 | 1980-12-24 | Helmut Nehrig | INJECTION DEVICE FOR INTERNAL COMBUSTION ENGINES |
CH635171A5 (en) * | 1978-06-08 | 1983-03-15 | Bbc Brown Boveri & Cie | DEVICE ON A DIFFUSER FOR SUPPRESSING RESONANCES. |
US4218020A (en) * | 1979-02-23 | 1980-08-19 | General Motors Corporation | Elliptical airblast nozzle |
DE3235080A1 (en) | 1982-09-22 | 1984-03-22 | Kraftwerk Union AG, 4330 Mülheim | Return-flow injection nozzle for the atomisation of liquids |
US4638636A (en) * | 1984-06-28 | 1987-01-27 | General Electric Company | Fuel nozzle |
KR930004967B1 (en) * | 1988-07-13 | 1993-06-11 | 가부시기가이샤 히다찌세이사꾸쇼 | Electronic fuel injector |
US4970865A (en) * | 1988-12-12 | 1990-11-20 | Sundstrand Corporation | Spray nozzle |
US5095696A (en) * | 1990-01-02 | 1992-03-17 | General Electric Company | Asymmetric flameholder for gas turbine engine afterburner |
IT223984Z2 (en) * | 1990-01-17 | 1995-10-05 | Weber Srl | VALVE OF A POWER SUPPLY OF AN INTERNAL COMBUSTION ENGINE |
US5235813A (en) * | 1990-12-24 | 1993-08-17 | United Technologies Corporation | Mechanism for controlling the rate of mixing in combusting flows |
DE4104019C1 (en) * | 1991-02-09 | 1992-04-23 | Robert Bosch Gmbh, 7000 Stuttgart, De | |
FR2685452B1 (en) * | 1991-12-24 | 1994-02-11 | Snecma | FUEL INJECTION DEVICE FOR A TURBOMACHINE COMBUSTION CHAMBER. |
JP3052525B2 (en) * | 1992-01-30 | 2000-06-12 | 株式会社日立製作所 | Processing method of electromagnetic fuel injection valve |
US5373694A (en) * | 1992-11-17 | 1994-12-20 | United Technologies Corporation | Combustor seal and support |
DE29511384U1 (en) * | 1995-07-14 | 1995-10-12 | Fa. J. Eberspächer, 73730 Esslingen | Evaporation combustion chamber for a heater operated with liquid fuel |
US5515814A (en) * | 1995-09-06 | 1996-05-14 | Transglobal Technologies, Limited | Apparatus and method for supplying fuel to internal combustion engines |
DE19541303A1 (en) | 1995-11-06 | 1997-05-28 | Siemens Ag | Gas turbine arrangement e.g.for driving electrical power generators |
FR2748088B1 (en) * | 1996-04-24 | 1998-05-29 | Snecma | OPTIMIZATION OF THE MIXTURE OF BURNED GASES IN AN ANNULAR COMBUSTION CHAMBER |
WO1999006767A1 (en) * | 1997-07-31 | 1999-02-11 | Siemens Aktiengesellschaft | Burner |
US6119459A (en) * | 1998-08-18 | 2000-09-19 | Alliedsignal Inc. | Elliptical axial combustor swirler |
-
1999
- 1999-05-20 US US09/701,980 patent/US6676048B1/en not_active Expired - Fee Related
- 1999-05-20 WO PCT/DE1999/001514 patent/WO1999063268A1/en active IP Right Grant
- 1999-05-20 DE DE59902355T patent/DE59902355D1/en not_active Expired - Fee Related
- 1999-05-20 EP EP99936291A patent/EP1084368B2/en not_active Expired - Lifetime
- 1999-05-20 JP JP2000552433A patent/JP2002517700A/en not_active Abandoned
Non-Patent Citations (1)
Title |
---|
See references of WO9963268A1 * |
Also Published As
Publication number | Publication date |
---|---|
EP1084368B1 (en) | 2002-08-14 |
US6676048B1 (en) | 2004-01-13 |
JP2002517700A (en) | 2002-06-18 |
DE59902355D1 (en) | 2002-09-19 |
WO1999063268A1 (en) | 1999-12-09 |
EP1084368B2 (en) | 2005-11-02 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE3642122C1 (en) | Fuel injector | |
EP0794383B1 (en) | Method of operating a pressurised atomising nozzle | |
EP0892212B1 (en) | Pressure spray nozzle | |
DE10205839B4 (en) | Premix burner for reducing combustion-driven vibrations in combustion systems | |
DE69519849T2 (en) | FUEL NOZZLE WITH TANGENTIAL INJECTION | |
DE69116837T2 (en) | Liquid burner | |
EP0638769A2 (en) | Fuel injector for liquid and/or gaseous fuels and method for its operation | |
EP0029619A1 (en) | Gas-turbine combustor with premixing-prevaporizing elements | |
EP1730447A1 (en) | Burner | |
EP1030109B1 (en) | Fuel injector for injecting liquid and/or gas fuels in a combustion chamber | |
DE69413479T2 (en) | Fuel nozzle with non-rotationally symmetrical, secondary atomization | |
EP0902233A1 (en) | Combined pressurised atomising nozzle | |
DE19839085A1 (en) | Burner arrangement with primary and secondary pilot burner | |
EP1084368A1 (en) | Fuel injector | |
WO1999006767A1 (en) | Burner | |
EP0742411B1 (en) | Air supply for a premix combustor | |
DE4440558A1 (en) | Premix burner | |
EP0924461B1 (en) | Two-stage pressurised atomising nozzle | |
CH682009A5 (en) | ||
DE1964040A1 (en) | Device for mixing at least two fluid media, in particular for producing combustible mixtures of fluid media | |
EP0043908B1 (en) | Spray nozzle for continuous fuel injection | |
EP0167049A2 (en) | Process for burning fuel | |
DE3132948A1 (en) | "METHOD FOR VAPORIZING AND COMBUSTIONING LIQUID FUELS AND BURNER THEREFOR" | |
EP0789193B1 (en) | Method and apparatus for suppressing flame and pressure vibrations in a furnace | |
DE19854382B4 (en) | Method and device for atomizing liquid fuel for a firing plant |
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: 20001108 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): CH DE FR GB IT LI |
|
17Q | First examination report despatched |
Effective date: 20010629 |
|
GRAG | Despatch of communication of intention to grant |
Free format text: ORIGINAL CODE: EPIDOS AGRA |
|
GRAG | Despatch of communication of intention to grant |
Free format text: ORIGINAL CODE: EPIDOS AGRA |
|
GRAH | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOS IGRA |
|
GRAH | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOS IGRA |
|
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 IT LI |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: NV Representative=s name: SIEMENS SCHWEIZ AG |
|
REF | Corresponds to: |
Ref document number: 59902355 Country of ref document: DE Date of ref document: 20020919 |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20021028 |
|
ET | Fr: translation filed | ||
PLBI | Opposition filed |
Free format text: ORIGINAL CODE: 0009260 |
|
PLBF | Reply of patent proprietor to notice(s) of opposition |
Free format text: ORIGINAL CODE: EPIDOS OBSO |
|
26 | Opposition filed |
Opponent name: ALSTOM (SCHWEIZ) AG INTELLECTUAL PROPERTY (CHSP) Effective date: 20030514 |
|
PLAX | Notice of opposition and request to file observation + time limit sent |
Free format text: ORIGINAL CODE: EPIDOSNOBS2 |
|
PLBB | Reply of patent proprietor to notice(s) of opposition received |
Free format text: ORIGINAL CODE: EPIDOSNOBS3 |
|
PUAH | Patent maintained in amended form |
Free format text: ORIGINAL CODE: 0009272 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: PATENT MAINTAINED AS AMENDED |
|
27A | Patent maintained in amended form |
Effective date: 20051102 |
|
AK | Designated contracting states |
Kind code of ref document: B2 Designated state(s): CH DE FR GB IT LI |
|
GBTA | Gb: translation of amended ep patent filed (gb section 77(6)(b)/1977) | ||
REG | Reference to a national code |
Ref country code: CH Ref legal event code: AEN Free format text: AUFRECHTERHALTUNG DES PATENTES IN GEAENDERTER FORM |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20060505 Year of fee payment: 8 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20060523 Year of fee payment: 8 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20060531 Year of fee payment: 8 |
|
ET3 | Fr: translation filed ** decision concerning opposition | ||
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20060724 Year of fee payment: 8 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: CH Payment date: 20060808 Year of fee payment: 8 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20070520 |
|
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: 20070531 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20070531 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST Effective date: 20080131 |
|
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: 20071201 |
|
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: 20070520 |
|
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: 20070531 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20070520 |