CN102906500B - Turbulence blades, burner and gas turbine - Google Patents
Turbulence blades, burner and gas turbine Download PDFInfo
- Publication number
- CN102906500B CN102906500B CN201080048386.3A CN201080048386A CN102906500B CN 102906500 B CN102906500 B CN 102906500B CN 201080048386 A CN201080048386 A CN 201080048386A CN 102906500 B CN102906500 B CN 102906500B
- Authority
- CN
- China
- Prior art keywords
- turbulence blades
- fuel
- distributor
- fuel gas
- half portion
- 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 - Fee Related
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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- 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
- F23R3/36—Supply of different fuels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07001—Air swirling vanes incorporating fuel injectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/14—Special features of gas burners
- F23D2900/14004—Special features of gas burners with radially extending gas distribution spokes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/14—Special features of gas burners
- F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Manufacture, Treatment Of Glass Fibers (AREA)
Abstract
The present invention relates to a kind of turbulence blades (19), comprise the first fuel gas nozzle (21) and the second additional in addition fuel gas nozzle (23), wherein, first fuel gas nozzle (21) is supplied by the first distributor tube (61), and second fuel gas nozzle (23) supplied by the second distributor tube (65), here, distributor tube (61, 65) be integrated in turbulence blades (19), wherein, turbulence blades (19) is designed to, two turbulence blades half portion (19a are divided between the first distributor tube (61) and the second distributor tube (65), 19b).In addition the invention still further relates to a kind of burner and a kind of gas turbine.
Description
Technical field
The present invention relates to the turbulence blades of burner in a kind of especially gas turbine.In addition the invention still further relates to a kind of burner and a kind of gas turbine.
Background technology
In view of the emissions figure of burner in especially gas turbine is devoted to reduce in the whole world, developed the burner that some nitrogen oxide (NOx) discharge capacity is low especially in recent years.Very valuable in this respect, these burners not only can use a kind of fuel work, but also with different fuel works, such as, selectively can use oil and gas or their combination as far as possible, to improve supply of material security and operation flexibility.Such as in EP0276696B1, describe these burners.
The burner introduced in EP0276696B1 is a kind of mixed burner as being especially used in gas-turbine plant, for fuel gas and/or oily premixed work.This burner comprises a center fuel feedway, is wherein also integrated with a control combustion device system, and it is as so-called diffusion flame burner or can with fuel gas and/or oil work as independently premix burner.In addition also specify likely to supply inert substance.Center fuel feedway by main burner system around, this main burner system has an air fed circular passage system, and comprising being in wherein has the turbulence blades group of multiple blade and be located at blade upstream for the jet pipe with fuel gas premixed work.In addition, in fuel supply system, in turbulence blades group region, also there is the entry nozzle of oil, they can by main air flow and oily premixed.
Replace as in EP0276696B1 by the jet pipe being in blade upstream, also can spray in air duct by fuel gas by the spout being located at turbulence blades itself interior, that such as introduces in EP0580683B1 is such.
In order to control discharge and future can also improve combustion stability further, except such as passing through, except a fuel gas nozzle of blade, also should to utilize another fuel gas nozzle by blade in EP0580683B1 like that.This additional fuel gas nozzle should be able to acceptor's fuel gas level control separately, that is, except already present fuel gas so far and oily passage, must add the second additional fuel gas passage in the center fuel feedway of burner.Present difficult point is, the turbulence blades with additional fuel gas passage meets necessary strength specification, meanwhile has long service life.
Summary of the invention
Therefore the technical problem to be solved in the present invention is to provide a kind of favourable turbulence blades with the first fuel gas nozzle and the second additional in addition fuel gas nozzle.The technical problem that the present invention second will solve is, provides a kind of favourable burner.Another technical problem that will solve is to provide a kind of favourable gas turbine.
First technical problem is solved by turbulence blades according to claim 1 by one, second technical problem is by being solved by burner according to claim 9, and another technical problem is by being solved by gas turbine according to claim 10.Dependent claims contains favourable expansion more of the present invention design.
Here, by this turbulence blades of the present invention, comprise the first fuel gas nozzle and the second additional in addition fuel gas nozzle, wherein, first jet is supplied by the first distributor tube, and second nozzle is supplied by the second distributor tube, here, distributor tube is integrated in turbulence blades.Turbulence blades and there is a fuel flow direction to distributor tube supply fuel or a kind of fuel supply system of fuel mixture.
Known by the present invention, if blade nozzle designs equally in lower region and upper zone, then cause two cooperation (Doppelpassung).Therefore the adjustment of blades oriented is also no longer such as undertaken by the adjustment pad existed by a point of rotation.Now based on multiple nozzle-axis and two cooperation, so no longer there is the real point of rotation.
Therefore by the present invention, the turbulence blades between the first distributor tube and the second distributor tube, is designed to be divided into two turbulence blades half portion.
Advantageously, present blade or two blade half portion, their orientation can be undertaken by adjustment pad again.In addition, can by two independently distributor tube implement respectively fuel control.Partition type blade can also simply and cheaply manufacture.
Preferably, described two turbulence blades half portion operationally have a flow direction, and are connected with the first and second fuel distributor duct respectively in upstream, and wherein, the first and second fuel distributor duct are located in center fuel feedway.Here, these turbulence blades half portion are arranged in the annular air channel of supply combustion air.
Therefore, from the fuel of the first fuel distributor duct, from the fuel of the second fuel distributor duct, can spray into independently of one another in the first distributor tube or in the second distributor tube.These fuel distributor duct can be realized thus and " classification (staging) " that thus the fuel of turbulence blades half portion is different.When this just in time changes between full load and sub-load or be favourable when rinsing, because thermal stress can be avoided by supplying fuel completely independently, and very rapidly can realize on the other hand conversion.
Preferably, these turbulence blades half portion are arranged in the annular air channel of supply combustion air, it is around center fuel feedway, wherein, first fuel nozzle is supplied by the first fuel distributor feedway in center fuel feedway, and the second fuel nozzle is supplied by the second fuel distributor duct in center fuel feedway.
In addition, by preferred design, fuel distributor feedway has a flow direction and comprises a supply pipe, it is connected with one of turbulence blades in downstream, and comprise an annular adapter (Ringaufsatz), wherein, supply pipe is connected with annular adapter in upstream, wherein, annular adapter is seen along the flow direction and is connected to fuel distributor duct upstream.
Preferably, described two turbulence blades half portion have cooperation plug and have attached slide in upstream in downstream.Wherein, slide stretches in center fuel feedway at least partly in upstream.Here, described two blade half portion are preferably only inserted and are coordinated in plug.Therefore two blade half portion can thermal expansion.Thus can thermal stress be avoided.Thus can significant prolongation partition type turbulence blades service life and thus extend service life of whole burner.
By favourable design, these two turbulence blades half portion have nut respectively, can tighten turbulence blades half portion by it, make it be pressed against on boundary's wall in downstream.
Preferably, in a burner, this turbulence blades is provided with.In addition by preferred design, described burner is adopted in the gas turbine.
Accompanying drawing explanation
By referring to accompanying drawing in the explanation of embodiment, other features of the present invention, feature and advantage are provided.
Wherein:
The very schematic principle sketch of Fig. 1 represents by burner of the present invention;
Fig. 2 indicates the combustion chamber sleeve schematic diagram of two fuel gas levels and an oily passage;
Fig. 3 indicates the turbulence blades schematic diagram of two fuel gas levels;
Fig. 4 represents by the partition type turbulence blades of the present invention in sleeve (being cut open the cross section illustrated by blade) schematic diagram;
Fig. 5 represents by partition type turbulence blades (overlook) schematic diagram of the present invention in sleeve;
Fig. 6 represents the combustion chamber sleeve schematic diagram having annular adapter and partition type turbulence blades by the present invention; And
Fig. 7 indicates the annular adapter top view of partition type turbulence blades.
Detailed description of the invention
Referring to the Fig. 1 represented with very schematic principle sketch by burner of the present invention, its illustrates burner basic design scheme.
By burner of the present invention, it can such as be used in gas-turbine combustion chamber with multiple same burner combination if desired, comprises an internal control buner system and one with one heart around the main burner system of this control combustion device system.Not only control combustion device system, and main burner system, selectively can use gaseous state and/or liquid fuel work, such as natural gas or fuel oil.
Control combustion device system comprises an interior oil supply gallery 1, in it is annular by one fuel gas feed path 3 with one heart around.Interior fuel gas feed path 3 again by an interior air feed path or inert substance feed path 5 with one heart around.In addition can in this air feed path or on appropriate ignition system (not representing in figure) is set.Control combustion device system has an outlet 9 facing combustion chamber 7, in the region of outlet 9, establishes turbulence blades group 11 in air feed path.Fuel gas can be sprayed in turbulence blades group region from interior fuel gas feed path 3 by spout 13, or spray in air feed path 5 in turbulence blades group upstream.From the oil of oily feed path, by atomizer 15, can spray in turbulence blades group downstream in the air of supply or in the inert substance of supply.
Control combustion device system can in the known manner as diffusion flame burner oil and/or fuel gas work, and fuel directly sprays in flame in diffusion flame burner.But also there is such possibility, that is, control combustion device system is as premix burner work, and fuel thoroughly mixes with air in premix burner, then mixture is supplied flame.
Main burner system around control combustion device system comprises one radially at the air feed path 17 of outside, and also known as annular air road, multiple turbulence blades 19 of turbulence blades group extend through it.Turbulence blades 19 has the first fuel gas nozzle 21 and the second fuel gas nozzle 23, and gaseous fuel sprays into via in radial air feed path 17 leaked-in air by them.In addition in the air flowing through air feed path 17, oil can be sprayed into by atomizer 25 again.Oil and atomizer although touch upon in the present embodiment, this only should as the liquid fuel be suitable for and the representative of corresponding nozzle.
Be in the first fuel gas nozzle 21 in turbulence blades 19 and the second fuel gas nozzle 23 and atomizer 25, by being radially in inner fuel supply system, fuel supplied by so-called sleeve 27.In sleeve 27, arrange the first and second annular combustible gas distributors passages 29 and 31, they supply fuel gas to fuel gas nozzle 21 or 23.Turbulence blades 19 and fuel supply system have a fuel flow direction 100.In addition, establish the oil dispenser passage 33 of annular in sleeve 27, it gives atomizer 25 fuel feeding.Combustible gas distributors passage 29,31 and oil dispenser passage 33, supply corresponding fuel by fuel gas feed path 35,37 or by oily feed path 39.Fuel gas feed path 35,37 supplies fuel to combustible gas distributors passage 29,31.The oily supply pipe 43 of oneself is there is for oily feed path 39.
Fig. 2 indicates the fuel sleeve 27 of fuel distributor duct 29 and 31, and it has some fuel to be imported hole in blade 19.The substantially parallel laying of these two fuel distributor duct 29 and 31, and separated by dividing plate 50.
Fig. 3 indicates turbulence blades 7 schematic diagram of two fuel gas level B and D that are integrated, that can control independently of one another.
Turbulence blades 19 has two combustible gas distributors passages 29 and 31 independent of each other.One of them has the combustible gas distributors passage 29 of outlet nozzle 21, such as can be used in and spray into medium D, and it is different from the medium (medium B) that the second combustible gas distributors passage 31 is sprayed into by outlet nozzle 23.Preferably, these two kinds what sprayed into by the combustible gas distributors passage 29 and 31 of turbulence blades 19 is gaseous medium, and such as a kind of medium is natural gas and another kind of medium is coal gas.Spray into a kind of inert substance, such as steam by these outlet nozzles 21 and/or 23 equally when needed.
Known by the present invention, adopt the blade nozzle of dual same design to cause two two cooperations 51 in upper zone and lower region, cooperation 51 that it causes blade 19 especially no longer can comprise at least one adjustment pad by this adjusts blades oriented.Consequently, no longer there is now the point of rotation (fulcrum).Especially nozzle-axis can be regarded as the point of rotation in this case.Based on multiple nozzle-axis and two cooperation, thus no longer there is the point of rotation.
Turbulence blades 19 is equipped with the first fuel gas nozzle 21 and another the second additional fuel gas nozzle 23.Wherein, nozzle 21 is supplied by the first distributor tube 61, and nozzle 23 is supplied by the second distributor tube 65, and here distributor tube 61,65 is integrated in turbulence blades 19.
Be designed to by turbulence blades 19 of the present invention now, between the first distributor tube 61 and the second distributor tube 65, be divided into two turbulence blades half portion 19a, 19b (Fig. 4).The advantage done like this is, these nozzles control by spout 21 and 23 is independent.Can implement thus different " classification (staging) ".Thus control channel 31 and 29 can also be distinguished.This also plays a part favourable for service life, because also can control the thermic load of these two passages 31 and 29 now.This is changing from sub-load to full load, and when changing from full load to sub-load conversely, is all particularly advantageous.Have compared with two blade coordinating 51 with one, the faster and considerably cheaper of the manufacture of partition type blade 19a, 19b.In addition, the blades oriented of these two turbulence blades half portion 19a, 19b is undertaken by adjustment pad.
In addition turbulence blades half portion 19a, 19b have a kind of cooperation on the outer boundary wall 17b of air feed path 17, and that is, have so-called cooperation plug 90a, a 90b and slide 85a, a 85b, it is arranged in sleeve 27 itself.By coordinating plug 90a, 90b and slide 85a, a 85b, these two turbulence blades half portion 19a, 19b can separate thermal expansion now, reduce stress equally thus.The outer boundary wall 17b of air feed path 17 screws this two turbulence blades half portion 19a, 19b with nut 86a, 86b (Fig. 5), is pressed against on this outer boundary wall 17b.
Sleeve 27 can also comprise a supply pipe 55 (Fig. 6 and 7), it is connected with one of turbulence blades half portion 19a (19b) in downstream, and comprise an annular adapter 60, wherein, supply pipe 55 is connected with annular adapter 60 in upstream, here, annular adapter 60 is seen be connected to fuel distributor duct 31 (or 29) upstream along being flowed to 100.Therefore can say and one of distributor passage 29 or 31 is designed to supply pipe 55.
Supply pipe 55 imports distributor tube 61 (or 65) in downstream.Supply pipe 55 is connected with annular adapter 60 (Fig. 5) in upstream.Here, annular adapter 60 is seen along the flow direction and is connected to fuel distributor duct 31 (or 29) upstream.Original fuel distributor duct 31 (or 29) is made to be parallel to supply pipe 55 thus.Annular adapter 60 is supplied by independent pipe joint 75.Fuel distributor duct 31 (or 29) is originally supplied by another passage 80.So these two fuel gas guiding channels, that is supply pipe 55 and annular adapter 60 and original fuel distributor duct 31 (or 29), by the present invention's spatially decoupling.Annular adapter 60 plays a part as follows: it is removed heavily stressed in sleeve 27 and is distributed equably on component by stress.Thus by reducing stress elimination to the harm of structure space.
Reduce stress further to reach, the dividing plate 50 that fuel distributor duct 31 (or 29) and supply pipe 55 separate is designed to flexible.Here dividing plate 50 can with a kind of elastomeric material manufacture.Additional or unlike this, dividing plate 50 also can cause elasticity by corresponding geometry designs and thus offset stress.This such as can be caused by dividing plate 50 that is bending or waveform.
Claims (10)
1. one kind for being arranged on the turbulence blades (19) in air feed path, comprise a first fuel gas nozzle (21) and in addition additional along the second fuel gas nozzle (23) of air-flow direction in described first fuel gas nozzle (21) downstream, wherein, first fuel gas nozzle (21) is supplied by the first distributor tube (61), and second fuel gas nozzle (23) supply by along second distributor tube (65) of air-flow direction in described first distributor tube (61) downstream, here, distributor tube (61, 65) be integrated in turbulence blades (19), it is characterized by: turbulence blades (19) is designed to, two turbulence blades half portion (19a are divided between the first distributor tube (61) and the second distributor tube (65), 19b).
2. according to turbulence blades according to claim 1 (19), it is characterized by, described two turbulence blades half portion (19a, 19b) can separately manufacture.
3. according to the turbulence blades (19) described in claim 1 or 2, it is characterized by, described turbulence blades half portion (19a, 19b) is arranged in the annular air channel (17) of supply combustion air, and operationally there is a flow direction (100), and be connected with the first fuel distributor duct (29) and the second fuel distributor duct (31) respectively in upstream, wherein, the first and second fuel distributor duct (29,31) are arranged in center fuel feedway (27).
4. according to the turbulence blades (19) described in claim 1 or 2, it is characterized by, described turbulence blades half portion (19a, 19b) be arranged in the annular air channel (17) of supply combustion air, described annular air channel is around center fuel feedway (27), wherein, first fuel gas nozzle (21) is supplied by the first fuel distributor feedway in center fuel feedway (27), and second fuel gas nozzle (23) by center fuel feedway (27) the second fuel distributor duct (31) supply.
5. according to turbulence blades according to claim 4 (19), it is characterized by, described first fuel distributor feedway has a flow direction (100) and comprises supply pipe (55), this supply pipe is connected with one of turbulence blades (19a, 19b) in downstream, and comprise annular adapter (60), wherein, in upstream, adapter (60) annular with this is connected supply pipe (55), wherein, annular adapter (60) is seen along the flow direction and is connected to described second fuel distributor duct (31) upstream.
6. according to turbulence blades according to claim 2 (19), it is characterized by, described two turbulence blades half portion (19a, 19b) have in downstream to coordinate fills in (90a, 90b) and has slide (85a, 85b) in upstream.
7. according to turbulence blades according to claim 6 (19), it is characterized by, described slide (85a, 85b) stretches in center fuel feedway (27) at least partly in upstream.
8. according to turbulence blades according to claim 2 (19), it is characterized by, described two turbulence blades half portion (19a, 19b) have nut (86a, 86b) respectively, turbulence blades half portion (19a, 19b) can be tightened by described nut, make it be pressed against on boundary's wall (17b) in annular air channel (17) downstream.
9. a burner, has according to the turbulence blades (19) one of all claims in prostatitis Suo Shu.
10. a gas turbine, has at least one according to burner according to claim 9.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102009038845.1 | 2009-08-26 | ||
| DE102009038845A DE102009038845A1 (en) | 2009-08-26 | 2009-08-26 | Swirl vane, burner and gas turbine |
| PCT/EP2010/062214 WO2011023648A2 (en) | 2009-08-26 | 2010-08-23 | Swirl blade, burner and gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102906500A CN102906500A (en) | 2013-01-30 |
| CN102906500B true CN102906500B (en) | 2016-03-09 |
Family
ID=43525015
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201080048386.3A Expired - Fee Related CN102906500B (en) | 2009-08-26 | 2010-08-23 | Turbulence blades, burner and gas turbine |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP2470833A2 (en) |
| CN (1) | CN102906500B (en) |
| DE (1) | DE102009038845A1 (en) |
| RU (1) | RU2535433C2 (en) |
| WO (1) | WO2011023648A2 (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2633475C2 (en) * | 2012-08-06 | 2017-10-12 | Сименс Акциенгезелльшафт | Local improvement of air and fuel mixing in burners supplied with swirlers with blade ends crossed at outer area |
| US9267689B2 (en) * | 2013-03-04 | 2016-02-23 | Siemens Aktiengesellschaft | Combustor apparatus in a gas turbine engine |
| WO2015067482A1 (en) * | 2013-11-08 | 2015-05-14 | Siemens Aktiengesellschaft | Gas turbine burner having separately controllable fuel stages in pilot burner swirl vanes |
| DE102015206227A1 (en) * | 2015-04-08 | 2016-10-13 | Siemens Aktiengesellschaft | burner arrangement |
| EP3301368A1 (en) | 2016-09-28 | 2018-04-04 | Siemens Aktiengesellschaft | Swirler, combustor assembly, and gas turbine with improved fuel/air mixing |
| DE102018112540A1 (en) * | 2018-05-25 | 2019-11-28 | Kueppers Solutions Gmbh | Fuel nozzle system |
| CN109026175B (en) * | 2018-08-31 | 2020-12-29 | 中国航发动力股份有限公司 | Spoiler assembling structure and assembling method thereof |
| CN114110662B (en) * | 2021-11-25 | 2023-02-10 | 同济大学 | Low-nitrogen combustion chamber of gas turbine |
| US11835235B1 (en) * | 2023-02-02 | 2023-12-05 | Pratt & Whitney Canada Corp. | Combustor with helix air and fuel mixing passage |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5062792A (en) * | 1987-01-26 | 1991-11-05 | Siemens Aktiengesellschaft | Hybrid burner for a pre-mixing operation with gas and/or oil, in particular for gas turbine systems |
| US5451160A (en) * | 1991-04-25 | 1995-09-19 | Siemens Aktiengesellschaft | Burner configuration, particularly for gas turbines, for the low-pollutant combustion of coal gas and other fuels |
| EP1394471A1 (en) * | 2002-09-02 | 2004-03-03 | Siemens Aktiengesellschaft | Burner |
| EP1662202A1 (en) * | 2004-11-30 | 2006-05-31 | Siemens Aktiengesellschaft | Burner for a gas turbine and method to operate such a burner |
| GB2437977A (en) * | 2006-05-12 | 2007-11-14 | Siemens Ag | A swirler for use in a burner of a gas turbine engine |
| EP2090825A1 (en) * | 2008-02-14 | 2009-08-19 | Siemens Aktiengesellschaft | Burner element and burner with corrosion-resistant insert |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19549140A1 (en) * | 1995-12-29 | 1997-07-03 | Asea Brown Boveri | Method for operating a gas turbine group with low-calorific fuel |
| EP1507119A1 (en) * | 2003-08-13 | 2005-02-16 | Siemens Aktiengesellschaft | Burner and process to operate a gas turbine |
| EP1645807A1 (en) * | 2004-10-11 | 2006-04-12 | Siemens Aktiengesellschaft | Burner to burn a low BTU fuel gas and method to use such a burner |
| US20080078183A1 (en) * | 2006-10-03 | 2008-04-03 | General Electric Company | Liquid fuel enhancement for natural gas swirl stabilized nozzle and method |
| EP1918638A1 (en) * | 2006-10-25 | 2008-05-07 | Siemens AG | Burner, in particular for a gas turbine |
-
2009
- 2009-08-26 DE DE102009038845A patent/DE102009038845A1/en not_active Ceased
-
2010
- 2010-08-23 RU RU2012111257/06A patent/RU2535433C2/en not_active IP Right Cessation
- 2010-08-23 CN CN201080048386.3A patent/CN102906500B/en not_active Expired - Fee Related
- 2010-08-23 EP EP10749630A patent/EP2470833A2/en not_active Withdrawn
- 2010-08-23 WO PCT/EP2010/062214 patent/WO2011023648A2/en active Application Filing
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5062792A (en) * | 1987-01-26 | 1991-11-05 | Siemens Aktiengesellschaft | Hybrid burner for a pre-mixing operation with gas and/or oil, in particular for gas turbine systems |
| US5451160A (en) * | 1991-04-25 | 1995-09-19 | Siemens Aktiengesellschaft | Burner configuration, particularly for gas turbines, for the low-pollutant combustion of coal gas and other fuels |
| EP1394471A1 (en) * | 2002-09-02 | 2004-03-03 | Siemens Aktiengesellschaft | Burner |
| EP1662202A1 (en) * | 2004-11-30 | 2006-05-31 | Siemens Aktiengesellschaft | Burner for a gas turbine and method to operate such a burner |
| GB2437977A (en) * | 2006-05-12 | 2007-11-14 | Siemens Ag | A swirler for use in a burner of a gas turbine engine |
| EP2090825A1 (en) * | 2008-02-14 | 2009-08-19 | Siemens Aktiengesellschaft | Burner element and burner with corrosion-resistant insert |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2470833A2 (en) | 2012-07-04 |
| WO2011023648A3 (en) | 2012-11-15 |
| RU2535433C2 (en) | 2014-12-10 |
| DE102009038845A1 (en) | 2011-03-03 |
| DE102009038845A8 (en) | 2011-06-01 |
| RU2012111257A (en) | 2013-10-10 |
| CN102906500A (en) | 2013-01-30 |
| WO2011023648A2 (en) | 2011-03-03 |
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