EP1651841A1 - Open-cooled component for a gas turbine, combustion chamber, and gas turbine - Google Patents
Open-cooled component for a gas turbine, combustion chamber, and gas turbineInfo
- Publication number
- EP1651841A1 EP1651841A1 EP04739955A EP04739955A EP1651841A1 EP 1651841 A1 EP1651841 A1 EP 1651841A1 EP 04739955 A EP04739955 A EP 04739955A EP 04739955 A EP04739955 A EP 04739955A EP 1651841 A1 EP1651841 A1 EP 1651841A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- cavity
- wall
- combustion chamber
- component
- 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
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
-
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M5/00—Casings; Linings; Walls
- F23M5/08—Cooling thereof; Tube walls
- F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
-
- 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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
Definitions
- the present invention relates to an open-cooled component for a gas turbine with a H adoptedgasbeetzmannten outer wall which at least partially defines a first cavity for a first means and are arranged in the fürgangso réelleen which fürgangso réelleen one hand into the cavity and on the other hand into the hot gas space and at least one second cavity for admixing a second means, which is in Strömungs- connection with the passage openings.
- the invention further relates to a combustion chamber and a gas turbine.
- Combustor walls as well as gas turbine blades are subject to high physical stress during normal operation of the gas turbine.
- these components are provided with a cooling. If air is used as a coolant, it is taken from a combustion chamber upstream compressor with diffuser and is lost to the combustion process. As a result, flame temperatures and NO x emissions increase.
- the wall of a combustion chamber is cooled either open or closed.
- the open cooling is designed as convective cooling, film cooling or as impact cooling with a cooling air outlet in the combustion chamber.
- the closed cooling requires a higher design effort and leads to an increased pressure loss due to the cooling air flow and the cooling itself.
- US Pat. No. 5,125,793 shows a turbine blade of a gas turbine with a double-walled outer wall enclosing a cavity.
- a flow channel for air is arranged in the double-walled outer wall.
- the cavity flows a liquid fuel, which is injected through through openings in the flow channel located in the double wall and there meets a catalyst.
- the catalyst Through the catalyst, the fuel decomposes endothermically into at least one combustible gas, which cools the blade.
- the air transports the gases to an outlet, from which the mixture can flow into the turbine and burn there.
- a disadvantage of the known concepts is that for the mixing of cooling air and fuel, a volume is to be provided by the reaction partners can ignite by auto-ignition or flashback in the components. As a result, under certain circumstances, stable combustion processes develop, so that the cooling effect of the fuel-air mixture is lost or the component can be damaged by the internal combustion.
- the second cavity is formed by supply channels provided in the outer wall, which are connected via transverse channels with the fürgangso réelleen formed as a passage bore, so that the two means are miscible only within the through holes.
- the invention further proposes a combustion chamber for a gas turbine with a wall element, which has a corresponding arrangement.
- the invention turns away.
- the previously formed between the double wall second cavity can be embedded as a supply channel in the outer wall, which is connected via separate transverse channels with the fürgangso réelleen.
- a possibility is thus created for the first time to substantially completely avoid a mixing volume in the component, as a result of which flashback and self-ignition in the component can be largely avoided.
- a component designed as a wall element of a combustion chamber it is possible to reduce a flame temperature increase in the case of open cooling, since the cooling air is now without the disadvantages described above can be enriched with fuel.
- the present invention therefore allows the cooling air flow to be increased without adversely affecting combustion.
- the present invention can also be achieved that the flame acoustics influenced, in particular detuned, can be.
- the fürgangs ⁇ réelle can be provided, for example, that the cooling air flows into the combustion chamber of the combustion chamber. Via the supply channel provided in the outer wall of the component, fuel can be supplied which mixes with the cooling air as it flows into the passage opening and thus forms a combustible mixture. A flashback is avoided insofar as there is no ignitable mixture in one of the supply channels or in the cavities before the mouth of the transverse channel in the fürgangs ⁇ réelle. Thus, the above-mentioned undesirable, sometimes dangerous, conditions can be avoided.
- the outer wall has a plurality of through holes, a plurality of supply channels extending between the holes, and a plurality of further transverse channels which crosslink the supply channels with the through holes. Due to the net-like structure of the channels and holes, a homogenization of the flowing mixture into the combustion chamber of fuel and cooling air can be achieved. In addition, it is possible to cool the component more uniformly, so that local overheating can be avoided.
- the component has at least two interconnectable layers.
- one layer may have the channel, while a second layer is formed on the combustion chamber side of a particularly resistant material.
- a high load capacity of the component can be achieved.
- the channel is introduced in at least one layer surface of one of the layers on the connection side. The channel can be introduced in this way by milling or similar material-removing processes in the surface of a layer, wherein by assembling the adjacent layers closed channels are formed. The channel can thereby be introduced into the component by means of known and also cost-effective methods.
- the cavity with a first fluid source and the supply channel with a second fluid source is connectable.
- Both fluids i.
- Means can be used to cool the blade so that the amount of air required for cooling is reduced. A larger amount of air is available to the combustion process, so that high flame temperatures and NO ⁇ emission can be reduced.
- the blade is basically the same principle as for the wall element of the combustion chamber at the bottom. Again, there is essentially no mixing volume, so that flashback and autoignition are largely avoided.
- the reliability of the gas turbine with respect to defective blades can be increased.
- the cooling air flow can be increased without negative effects on the combustion and the flame acoustics can be detuned.
- the invention also proposes that one of the two fluid sources is an oxidant source and the other fluid source is a fuel source.
- an ignitable mixture is formed only in the region of the mouth of the fürgangs ⁇ réelle in the flow channel of the gas turbine, when the mouth of the channels is arranged sufficiently close to the mouth of the passage opening in the flow channel.
- the invention also proposes a gas turbine, wherein the gas turbine is a combustion chamber according to the invention.
- the negative effects, as described above, can be largely reduced by supplying fuel, wherein the combustion chamber according to the invention enables safe operation with respect to auto-ignition and flashback. Furthermore, it is advantageous to influence the flame acoustics in order to reduce the stresses and wear caused by this.
- the invention also proposes a gas turbine with a component designed as a blade.
- the cooling effect for the blade of the turbine unit which can be designed as a fixed guide blade as well as a rotating rotor blade, can be improved by increasing the cooling air flow, wherein the negative effects on the combustion can be largely avoided.
- an influence on the detuning of the flame acoustics can be exerted. Wear and tear can be further reduced.
- FIG. 1 shows a section through an inventive wall element for a combustion chamber
- FIG. 2 shows a section through the wall element in Fig. 1 along a line II
- 3 shows a schematic representation of a system of channels in a wall element according to the present invention
- Fig. 4 is a schematic representation of a blade in a flow channel of a gas turbine
- FIG. 5 shows a section through a blade according to the invention.
- Fig. 1 shows a section through an inventive designed as a wall element 2 component with a plurality of fürgangso réelleen 3 can enter through the cooling air into the combustion chamber.
- the wall element 2 also has transverse channels 4, which open at one end in each case into a passage opening 3.
- a fluid fuel can be supplied, which is guided via the transverse channels 4 to the fürgangso réelleen 3 and is introduced there into the flow of cooling air.
- Fig. 2 illustrates this system of channels for the fuel supply.
- the wall element 2 has two interconnectable layers 6, 7. In the connection-side layer surface of the layer 6, the channel system is introduced by milling. By the connection of the layers 6 and 7 closed channels 4 and 9 are formed.
- Fig. 3 shows a plan view of the surface of the layer 6 of the wall element 2 in which the channels 4 and 9 are introduced.
- the connecting channel 9 is formed integrally with the wall element.
- the combustion chamber of a plurality of wall elements 2 is modular.
- the wall element 2 can also be advantageously used as a heat shield, liner and the like.
- a section of a flow channel of a gas turbine is shown schematically by a blade 10 is arranged.
- Hot gas space 21 open through openings 12, wherein in the mouth region junctions of transverse channels 13 are indicated schematically.
- FIG. 5 A section through such a blade 10 is shown in FIG. 5.
- a blade wall 14 encloses a cavity 15, wherein the blade wall 17 is provided with passage openings 12. Cooling air can be supplied via the cavity 15 and exits through the passage openings 12 into the flow channel 11.
- the blade wall 14 is further provided with a system of supply channels 13, which are connected via transverse channels 4 each with the fürgangso réelleen 12.
- the supply channels 13 are connected to a fluid fuel source in str ⁇ ungstechnischer connection.
- the blade 14 is constructed in two layers, consisting of an outer layer 16 and a cavity 15 forming the inner layer 17.
- the inner layer 17 has on its side facing the layer 16 by milling introduced recesses, which the channel system with the supply channels 13 form.
- air is conducted as cooling air for the blade 10 via fürgangso réelleen 12 as Oxidati ⁇ nsstoffs in the flow channel 11.
- the fluid fuel is introduced into the passage openings 12 of the blade wall 14, so that an ignitable mixture is formed.
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04739955A EP1651841B1 (en) | 2003-07-04 | 2004-06-16 | Open-cooled component for a gas turbine, combustion chamber, and gas turbine |
PL04739955T PL1651841T3 (en) | 2003-07-04 | 2004-06-16 | Open-cooled component for a gas turbine, combustion chamber, and gas turbine |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP03015216 | 2003-07-04 | ||
PCT/EP2004/006491 WO2005003517A1 (en) | 2003-07-04 | 2004-06-16 | Open-cooled component for a gas turbine, combustion chamber, and gas turbine |
EP04739955A EP1651841B1 (en) | 2003-07-04 | 2004-06-16 | Open-cooled component for a gas turbine, combustion chamber, and gas turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1651841A1 true EP1651841A1 (en) | 2006-05-03 |
EP1651841B1 EP1651841B1 (en) | 2007-08-22 |
Family
ID=33560756
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04739955A Not-in-force EP1651841B1 (en) | 2003-07-04 | 2004-06-16 | Open-cooled component for a gas turbine, combustion chamber, and gas turbine |
Country Status (7)
Country | Link |
---|---|
US (2) | US7658076B2 (en) |
EP (1) | EP1651841B1 (en) |
CN (1) | CN100353032C (en) |
DE (1) | DE502004004752D1 (en) |
ES (1) | ES2288687T3 (en) |
PL (1) | PL1651841T3 (en) |
WO (1) | WO2005003517A1 (en) |
Families Citing this family (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1847696A1 (en) * | 2006-04-21 | 2007-10-24 | Siemens Aktiengesellschaft | Component for a secondary combustion system in a gas turbine and corresponding gas turbine. |
EP1847684A1 (en) * | 2006-04-21 | 2007-10-24 | Siemens Aktiengesellschaft | Turbine blade |
US20080134685A1 (en) * | 2006-12-07 | 2008-06-12 | Ronald Scott Bunker | Gas turbine guide vanes with tandem airfoils and fuel injection and method of use |
US8291705B2 (en) * | 2008-08-13 | 2012-10-23 | General Electric Company | Ultra low injection angle fuel holes in a combustor fuel nozzle |
EP2411736B1 (en) * | 2009-02-26 | 2019-06-05 | 8 Rivers Capital, LLC | Apparatus and method for combusting a fuel at high pressure and high temperature, and associated system and device |
US8986002B2 (en) | 2009-02-26 | 2015-03-24 | 8 Rivers Capital, Llc | Apparatus for combusting a fuel at high pressure and high temperature, and associated system |
US9068743B2 (en) * | 2009-02-26 | 2015-06-30 | 8 Rivers Capital, LLC & Palmer Labs, LLC | Apparatus for combusting a fuel at high pressure and high temperature, and associated system |
US8397516B2 (en) * | 2009-10-01 | 2013-03-19 | General Electric Company | Apparatus and method for removing heat from a gas turbine |
US8959886B2 (en) * | 2010-07-08 | 2015-02-24 | Siemens Energy, Inc. | Mesh cooled conduit for conveying combustion gases |
US8894363B2 (en) | 2011-02-09 | 2014-11-25 | Siemens Energy, Inc. | Cooling module design and method for cooling components of a gas turbine system |
US8640974B2 (en) | 2010-10-25 | 2014-02-04 | General Electric Company | System and method for cooling a nozzle |
US9249977B2 (en) * | 2011-11-22 | 2016-02-02 | Mitsubishi Hitachi Power Systems, Ltd. | Combustor with acoustic liner |
US9284231B2 (en) | 2011-12-16 | 2016-03-15 | General Electric Company | Hydrocarbon film protected refractory carbide components and use |
DE102012205055B4 (en) * | 2012-03-29 | 2020-08-06 | Detlef Haje | Gas turbine component for high temperature applications, and method for operating and producing such a gas turbine component |
US9174309B2 (en) | 2012-07-24 | 2015-11-03 | General Electric Company | Turbine component and a process of fabricating a turbine component |
US9709274B2 (en) | 2013-03-15 | 2017-07-18 | Rolls-Royce Plc | Auxetic structure with stress-relief features |
EP2846096A1 (en) * | 2013-09-09 | 2015-03-11 | Siemens Aktiengesellschaft | Tubular combustion chamber with a flame tube and area and gas turbine |
DE102015111843A1 (en) * | 2015-07-21 | 2017-01-26 | Rolls-Royce Deutschland Ltd & Co Kg | Turbine with cooled turbine vanes |
US20170176012A1 (en) * | 2015-12-22 | 2017-06-22 | General Electric Company | Fuel injectors and staged fuel injection systems in gas turbines |
MX2019010632A (en) | 2017-03-07 | 2019-10-15 | 8 Rivers Capital Llc | System and method for operation of a flexible fuel combustor for a gas turbine. |
CA3055403A1 (en) | 2017-03-07 | 2018-09-13 | 8 Rivers Capital, Llc | System and method for combustion of solid fuels and derivatives thereof |
WO2020021456A1 (en) | 2018-07-23 | 2020-01-30 | 8 Rivers Capital, Llc | System and method for power generation with flameless combustion |
CN113202566B (en) * | 2021-04-19 | 2022-12-02 | 中国航发湖南动力机械研究所 | Turbine guide vane and gas turbine engine |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2647368A (en) * | 1949-05-09 | 1953-08-04 | Hermann Oestrich | Method and apparatus for internally cooling gas turbine blades with air, fuel, and water |
US2981066A (en) * | 1956-04-12 | 1961-04-25 | Elmer G Johnson | Turbo machine |
US3037351A (en) * | 1956-05-14 | 1962-06-05 | Paul O Tobeler | Combustion turbine |
US4347037A (en) * | 1979-02-05 | 1982-08-31 | The Garrett Corporation | Laminated airfoil and method for turbomachinery |
GB2049152B (en) * | 1979-05-01 | 1983-05-18 | Rolls Royce | Perforate laminated material |
US4302940A (en) * | 1979-06-13 | 1981-12-01 | General Motors Corporation | Patterned porous laminated material |
US4928481A (en) * | 1988-07-13 | 1990-05-29 | Prutech Ii | Staged low NOx premix gas turbine combustor |
US5405242A (en) * | 1990-07-09 | 1995-04-11 | United Technologies Corporation | Cooled vane |
US5125793A (en) | 1991-07-08 | 1992-06-30 | The United States Of America As Represented By The Secretary Of The Air Force | Turbine blade cooling with endothermic fuel |
US5486093A (en) * | 1993-09-08 | 1996-01-23 | United Technologies Corporation | Leading edge cooling of turbine airfoils |
GB2310896A (en) | 1996-03-05 | 1997-09-10 | Rolls Royce Plc | Air cooled wall |
US6047550A (en) | 1996-05-02 | 2000-04-11 | General Electric Co. | Premixing dry low NOx emissions combustor with lean direct injection of gas fuel |
DE19737845C2 (en) | 1997-08-29 | 1999-12-02 | Siemens Ag | Method for producing a gas turbine blade, and gas turbine blade produced using the method |
US20030024234A1 (en) * | 2001-08-02 | 2003-02-06 | Siemens Westinghouse Power Corporation | Secondary combustor for low NOx gas combustion turbine |
US7217088B2 (en) * | 2005-02-02 | 2007-05-15 | Siemens Power Generation, Inc. | Cooling fluid preheating system for an airfoil in a turbine engine |
-
2004
- 2004-06-16 PL PL04739955T patent/PL1651841T3/en unknown
- 2004-06-16 US US10/561,641 patent/US7658076B2/en not_active Expired - Fee Related
- 2004-06-16 DE DE502004004752T patent/DE502004004752D1/en active Active
- 2004-06-16 CN CNB2004800166533A patent/CN100353032C/en not_active Expired - Fee Related
- 2004-06-16 WO PCT/EP2004/006491 patent/WO2005003517A1/en active IP Right Grant
- 2004-06-16 ES ES04739955T patent/ES2288687T3/en active Active
- 2004-06-16 EP EP04739955A patent/EP1651841B1/en not_active Not-in-force
-
2009
- 2009-12-07 US US12/631,940 patent/US8347632B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2005003517A1 * |
Also Published As
Publication number | Publication date |
---|---|
US8347632B2 (en) | 2013-01-08 |
EP1651841B1 (en) | 2007-08-22 |
ES2288687T3 (en) | 2008-01-16 |
CN1806094A (en) | 2006-07-19 |
US7658076B2 (en) | 2010-02-09 |
CN100353032C (en) | 2007-12-05 |
PL1651841T3 (en) | 2008-01-31 |
DE502004004752D1 (en) | 2007-10-04 |
US20100083665A1 (en) | 2010-04-08 |
US20070101722A1 (en) | 2007-05-10 |
WO2005003517A1 (en) | 2005-01-13 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1651841B1 (en) | Open-cooled component for a gas turbine, combustion chamber, and gas turbine | |
DE2143012C3 (en) | Burner arrangement in a gas turbine combustor | |
DE602005001742T2 (en) | Aerodynamic foaming fuel / air injection system for a gas turbine combustor | |
EP2010757B1 (en) | Turbine blade | |
EP2010773B1 (en) | Blade for a turbine | |
EP2156095B1 (en) | Swirling-free stabilising of the flame of a premix burner | |
DE102006011326B4 (en) | circular burner | |
DE102014117621A1 (en) | Fuel injector with premix pilot nozzle | |
DE102005048815A1 (en) | Inexpensive dual fuel combustion chamber and associated method | |
WO2010066516A2 (en) | Fuel lance for a burner | |
DE2122696A1 (en) | Combustion chamber for a gas turbine | |
CH699760A2 (en) | Fuel nozzle having a fuel-air premixer for a gas turbine combustor. | |
DE102011000788A1 (en) | Combustion chamber flame tube for a turbine engine | |
EP1319895A2 (en) | Lean-burn premix burner for gas turbine and its method of operation | |
CH702737A2 (en) | Combustion chamber with two combustion chambers. | |
DE2730791A1 (en) | COMBUSTION CHAMBER FOR GAS TURBINE ENGINES | |
EP2307806A1 (en) | Burner arrangement for liquid fuels and method for producing a burner arrangement | |
DE19859210A1 (en) | Fuel-air mixing arrangement for combustion devices | |
EP1245806B1 (en) | Cooled gas turbine balde | |
EP2014978A1 (en) | Use of insert gases for shielding oxidiser from fuel | |
DE112015004643T5 (en) | Burner and gas turbine engine | |
DE102008002934A1 (en) | Secondary fuel nozzle arrangement for use in gas-turbine engine, has nozzle section with central passage and passages, and head section with set of inlets in flow-connection with nozzle passages | |
DE102007036953B3 (en) | burner | |
DE112021000904T5 (en) | BURNER ASSEMBLY, GAS TURBINE COMBUSTOR AND GAS TURBINE | |
EP2295858A1 (en) | Stabilising of the flame of a burner |
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: 20051110 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): CH DE ES GB IT LI PL |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
DAX | Request for extension of the european patent (deleted) | ||
RBV | Designated contracting states (corrected) |
Designated state(s): CH DE ES GB IT LI PL |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): CH DE ES GB IT LI PL |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20070822 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: NV Representative=s name: SIEMENS SCHWEIZ AG Ref country code: CH Ref legal event code: EP |
|
REF | Corresponds to: |
Ref document number: 502004004752 Country of ref document: DE Date of ref document: 20071004 Kind code of ref document: P |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FG2A Ref document number: 2288687 Country of ref document: ES Kind code of ref document: T3 |
|
REG | Reference to a national code |
Ref country code: PL Ref legal event code: T3 |
|
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 |
Effective date: 20080526 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PCAR Free format text: SIEMENS SCHWEIZ AG;INTELLECTUAL PROPERTY FREILAGERSTRASSE 40;8047 ZUERICH (CH) |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20120626 Year of fee payment: 9 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20130610 Year of fee payment: 10 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: PL Payment date: 20130522 Year of fee payment: 10 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: ES Payment date: 20130711 Year of fee payment: 10 Ref country code: CH Payment date: 20130909 Year of fee payment: 10 Ref country code: DE Payment date: 20130819 Year of fee payment: 10 |
|
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: 20130616 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 502004004752 Country of ref document: DE |
|
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: 20140616 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 502004004752 Country of ref document: DE Effective date: 20150101 |
|
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: 20140630 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20140630 Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20150101 |
|
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: 20140616 |
|
REG | Reference to a national code |
Ref country code: PL Ref legal event code: LAPE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PL Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20140616 |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FD2A Effective date: 20160201 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20140617 |