CN104024737B - For combustion chamber and the burner apparatus of gas turbine - Google Patents
For combustion chamber and the burner apparatus of gas turbine Download PDFInfo
- Publication number
- CN104024737B CN104024737B CN201280065621.7A CN201280065621A CN104024737B CN 104024737 B CN104024737 B CN 104024737B CN 201280065621 A CN201280065621 A CN 201280065621A CN 104024737 B CN104024737 B CN 104024737B
- Authority
- CN
- China
- Prior art keywords
- mixing passages
- fuel
- combustion
- air
- burner apparatus
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
-
- 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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The present invention relates to a kind of combustion chamber (10 for gas turbine (1), 20), comprise at least one combustion zone (23, 24), and at least one is in combustion zone (23, 24) burner apparatus (11 of combust fuel/air mixture, 28), wherein, burner apparatus (11, 28) comprise at least one and import combustion zone (23, 24) for the preparation of the pre-mixing passages (29) of fuel/air mixture in, and remittance one is included in burner apparatus (11 in pre-mixing passages (29), 28) air feeder (32) in and at least one fuel supply system (33).This combustion chamber can suppress chamber pressure to fluctuate especially effectively.For this purpose, air feeder (32) sectional design, thus outlet in the remittance pre-mixing passages (29) of described segmented air feedway (34,34a, 34b, 34c) can be given with different (τ time delay
1, τ
2, τ
3).
Description
Technical field
The present invention relates to a kind of combustion chamber for gas turbine, comprise at least one combustion zone, and at least one is for the burner apparatus of combustion fuel/air mixture, wherein, burner apparatus comprises at least one and imports pre-mixing passages for the preparation of fuel/air mixture in combustion zone, and in pre-mixing passages, imports one be included in air feeder in burner apparatus and at least one fuel supply system.
The invention still further relates to and a kind ofly there is the gas turbine of this combustion chamber and relate to a kind of burner apparatus.
Background technology
Known gas turbine also comprises compressor and turbine except the combustion chamber that foreword is mentioned.Air in compressor compression input gas turbine, wherein, portion of air is used in combustion chamber combust fuel, and portion of air is used in cooling gas turbine and/or combustion gas.The high-temperature gas provided by the combustion process in combustion chamber introduces turbine from combustion chamber, and now high-temperature gas expands and cools in turbine, meanwhile work done power output, and turbo blade is rotated.Gas turbine drives working machine by rotating energy.Working machine such as can relate to generator.
By fuel/air mixture prepared by least one burner apparatus described, premixed at least one pre-mixing passages described, is then lighted behind inflow combustion zone.Compared with the past injects fuel directly in combustion zone usually, the premixed of fuel and air reduces the harmful gas emission produced when burning.Certainly, the shortcoming of pre-mixed fuel is, this device is very responsive for the chamber pressure fluctuation formed.If cause pressure oscillation in combustion zone, also can cause the fluctuation of concentration of fuel/air mixture in pre-mixing passages, when burning, this fluctuation of concentration will cause thermal discharge to change.The unstability of this thermoacoustics again can the pressure oscillation of enhanced burning room, wherein, to fluctuate the frequency having some preferential in this device for this energized chamber pressure.Fluctuation of concentration in fuel/air mixture, that is air fuel ratio is over time, also can be called that volumetric efficiency fluctuates.Volumetric efficiency fluctuation comes from air feeder has different acoustics resistances from fuel supply system.In order to suppress chamber pressure to fluctuate, known gas turbine comprises the resonator be arranged in casing.Because resonator and combustion zone direct neighbor, and thus the heat shield arrangement blocked in casing also must cool, so the structure of combustion chamber is very complicated.Fluctuate to suppress this chamber pressure, a kind of design code alternatively of known combustion room, some fuel nozzles imported in pre-mixing passages are arranged along pre-mixing passages axial distribution, thus in pre-mixing passages, form the mixed zone with different time delay.This sectional design of fuel supply system, is achieved to alleviate and to fluctuate the fluctuation of concentration caused in the fuel internal cause chamber pressure sprayed into by fuel supply system.Fuel nozzle also can be called that fuel supply system exports.
Summary of the invention
The technical problem to be solved in the present invention is, the burner apparatus providing the combustion chamber of type described in a kind of foreword He have the gas turbine of this combustion chamber and be included in this combustion chamber, and this combustion chamber can suppress chamber pressure to fluctuate especially effectively.
Above-mentioned technical problem takes following measure to be solved by the present invention in the combustion chamber of type described in foreword: air feeder sectional design, thus the outlet can given in the remittance pre-mixing passages of segmented air feedway is with different time delay.
Have along the fuel nozzle that arranges of pre-mixing passages axial distribution ground by known fuel supply system, although the fluctuation of the fuel quantity mixed with air stream along pre-mixing passages caused that to be fluctuated by chamber pressure can be compensated, but based on the acoustics resistance that air is different with fuel, this known segmentation ability does not accomplish to make fuel spray in air stream by this way, that is what escape and enter combustion zone from pre-mixing passages is the constant fuel quantity of the fuel of proportions constant and air and time per unit.Therefore in order to suppress combustion around chamber pressure fluctuation and also suppress thermal discharge variation thus, advise by the present invention, import the air feeder sectional design of pre-mixing passages, therefore alleviate and cause the density fluctuation in the air stream flowing through pre-mixing passages by chamber pressure fluctuation.Based on the compressibility that air is high compared with such as liquid fuel, and with pressure lower in airflow pipe compared with the pressure in fuel tube, so described suggestion can especially effectively suppress combustion fluctuate around chamber pressure.
By the present invention, segmented air feedway comprises the outlet in some remittance pre-mixing passages, can give their different time delay.In addition, segmented air feedway can comprise the outlet that other can give the time delay of their redundancies.Also the time delay of convection current can be called time delay.Its is determined according to entering flowing element in pre-mixing passages for the time of arriving at required for combustion zone.Outlet also can be called outlet.
Burner apparatus such as can comprise a master control burner, and it has pre-mixing passages and is located at the master control combustor nozzle at pre-mixing passages center, and wherein master control combustor nozzle is connected with fuel supply system and comprises some fuel nozzles.Air feeder is imported in the pre-mixing passages of master control burner.Some can be set around master control burner and be included in main blender in burner apparatus.Each main blender can have one by cylinder blanket around premixed all, air feeder imports in pre-mixing passages, and in pre-mixing passages, arranges one to be vertically connected with fuel supply system and the jet pipe with fuel nozzle.Jet pipe can be such as bearing on shell by turbulence blades.By the present invention, in the burner apparatus exemplarily provided, one of them pre-mixing passages comprises segmented air feedway.The air feeder of such as each main blender can be sectional design, and the given difference of turbulence blades design in remittance pre-mixing passages postpones in the air outlet slit between elbow for this reason.Different time delay can preferably be chosen as, and making can by air outlet slit different time delay, at least in the frequency range of preferential chamber pressure fluctuation, eliminates or weakens the density fluctuation in institute's input air of being caused by this pressure oscillation.
A kind of favourable expansion design of the present invention can specify, except the air feeder of sectional design, same sectional design one imports the fuel supply system that also can add fuel gas in pre-mixing passages.
Because compared with air, fuel gas has high compressibility equally, so by the additional segment design of fuel supply system that can add fuel gas, can more effectively suppress by chamber pressure fluctuate cause flow into fuel/air mixture concentration in combustion zone and density fluctuation from pre-mixing passages.If pre-mixing passages comprises the fuel supply system that more than can add fuel gas, then one or more this fuel supply system that can add fuel gas can sectional design.
Advantageously can also specify, the outlet of segmented feedway can be given with time delay, wherein, minimum delay time τ
minwith maximum delay time τ
maxthe relation fluctuated with the chamber pressure of the frequency f that will suppress, applicable elements: τ
max-τ
min> 1/f.
Ensured by described condition, at least in the frequency range of the chamber pressure fluctuation that will suppress, effectively weaken and to be fluctuated the density fluctuation caused by chamber pressure in the fluid inputted by segmented feedway.Segmented feedway relates to segmented air feedway.If also have the feedway sectional design in other remittance pre-mixing passages, then described condition is also applicable to these feedwaies.Minimum and the maximum delay time represented in described condition, relates to the shortest and the longest time delay of some outlets of imparting feedway.
Also can think advantageously, outlet in the remittance pre-mixing passages of segmented feedway is arranged as, make by least one frequency f ' preferential chamber pressure fluctuate, density fluctuation by causing in the fluid of outlet input in pre-mixing passages, based on give outlet different time delays, be superposed to and these density fluctuations cancelled each other substantially.
Can specify by a kind of favourable expansion design of the present invention, burner apparatus is arranged in the region of axial second stage, comprise the pre-mixing passages at least one remittance combustion zone, wherein, combustion zone is in downstream after first combustion zone with the first burner apparatus.
By axial second stage, thermal discharge can distribute on a large scale along whole operational combustion space, thus reduces the trend of combustion system thermoacoustics instability further.In addition, the segmented air feedway of at least one pre-mixing passages of the burner apparatus of axial second stage, equipment especially easily realizes.
The present invention one preferably expansion design can specify, burner apparatus comprises the fuel arranged around combustion box in outside and distributes ring, wherein, its one end imports in combustion zone by pre-mixing passages in combustion box, and along separate routes fuel supply system is out corresponding to distribute ring with at least one from fuel, here, the outlet of segmented air feedway is at least set along one of them pre-mixing passages with distributing.
The segmented air feedway of at least one pre-mixing passages of the burner apparatus of axial second stage, equipment especially easily realizes.Pre-mixing passages such as can be designed to hose-like, is applicable to of the present invention in this case completely, and air outlet slit is along the position of pre-mixing passages or the time delay corresponding with air outlet slit, and the frequency that can fluctuate with the chamber pressure that will suppress matches.Such as, hose-like pre-mixing passages can use elastomeric material manufacture, its length, and thus also has the time delay corresponding with outlet, all can match with the frequency that will suppress.
Another technical problem that will solve of the present invention provides a kind of gas turbine comprising combustion chamber described at least one foreword, and this combustion chamber can suppress chamber pressure to fluctuate especially effectively.
For this reason, this gas turbine has the combustion chamber that at least one designs according to one of Claims 1-4.
Another technical problem that will solve of the present invention provides a kind of burner apparatus be included in combustion chamber described in foreword, and it can suppress chamber pressure to fluctuate especially effectively.
For this reason, this burner apparatus is the part according to the described combustion chamber of one of Claims 1-4.
Accompanying drawing explanation
Other appropriate expansion designs of the present invention and advantage are the technical themes that the embodiment of the present invention is described see accompanying drawing, the component that Reference numeral indicative function same in accompanying drawing is identical.
Wherein:
Fig. 1 diagrammatically illustrates the sectional view of the gas turbine by prior art;
Fig. 2 diagrammatically illustrates the partial sectional view by the axial second stage in the combustion chamber of an embodiment of the present invention; And
Fig. 3 diagrammatically illustrates the cutting detail drawing in segmented air feedway region embodiment illustrated in fig. 2.
Detailed description of the invention
Fig. 1 schematically illustrates the sectional view of the gas turbine 1 by prior art.Gas turbine 1 has in inside around the rotationally supported rotor 3 of rotation 2 and axle 4, and rotor is also referred to as turbine rotor.What follow one another along rotor 3 is inlet casing 6, compressor 8, the combustion system 9 having some combustion chambers 10, turbine 14 and exit casing 15, and combustion chamber 10 comprises a burner apparatus 11 and a combustion box 12 respectively.
Combustion system 9 is connected with the high-temperature fuel gas passage of such as annular.The stage of turbine of multiple tandem forms turbine 14 there.Each stage of turbine is made up of some blade rings.The flow direction along working medium is seen, in high temperature channel after the vane group be made up of guide vane 17, arranges the vane group be made up of working-blade 18.Wherein guide vane 17 is fixed on the interior casing of stator 19, and one group of working-blade 18 is such as arranged on rotor 3 by the turbine disk.What be connected with rotor 3 is such as generator (not shown).
During gas turbine operation, compressor 8 sucks air by inlet casing 6 and compresses.Combustion system 9 is directed at the compressed air that the end of turbine side provides by compressor 8, and there in the region of burner apparatus 11 and fuel mix.Then mixture burns in combustion system 9 by burner apparatus 11, forms working air current.Set out therefrom, working air current flows through guide vane 17 and working-blade 18 along high-temperature fuel gas passage.Working air current expands and transmission pulse at working-blade 18 place, so working-blade 18 drives rotor 3, and rotor 3 drives again the generator (not shown) be connected with it.
Fig. 2 represents the Local map of the gas-turbine combustion chamber 20 by an embodiment of the present invention.Combustion chamber 20 combuster casing 21, it is designed to around axis 22 Rotational Symmetry.First combustion zone 23 and the second combustion zone 24 are in combustion box 21, and with regard to main flow direction 26, wherein the second combustion zone 24 is in downstream after the first combustion zone 23.Combustion chamber 20 comprises the first burner apparatus (not shown) and the second burner apparatus 28, and the latter is used at second combustion zone 24 combust fuel/air mixture.Second burner apparatus 28 comprises the pre-mixing passages 29 that imports the second combustion zone 24, for the preparation of fuel/air mixture, the air feeder 32 be included in the second burner apparatus 28 and fuel supply system 33 is imported in pre-mixing passages 29, wherein air feeder 32 sectional design, thus can give outlet 34 that segmented air feedway 32 imports pre-mixing passages 29 different time delay.
Therefore the second burner apparatus 28 is arranged in the region of axial second stage.Second burner apparatus 28 is included in the fuel that outer peripheral arranges around combustion box 21 and distributes ring 36 and multiple pre-mixing passages 29, wherein its one end 37 imports in the second combustion zone 24 by pre-mixing passages 29 in combustion box 21, and it is corresponding with distributing ring 36 fuel supply system 33 along separate routes from fuel respectively, here, the outlet 34 of a segmented air feedway 32 is set along one of them pre-mixing passages 29 with distributing.
By a kind of favourable expansion design of illustrated embodiment of the present invention, each pre-mixing passages 29 of the second burner apparatus 28 can have a segmented air feedway.
Spray into the fuel in pre-mixing passages 29 by fuel supply system 33, mix with the air being entered pre-mixing passages 29 by outlet 34, so fuel/air mixture streamwise 39 in pre-mixing passages flows.The volume of air of discharging from outlet 34 and fuel mix, here, from the position of outlet 34, need a perdurabgility to arrive in combustion zone 24.Described perdurabgility is called time delay, and its is determined according to entering flowing element in pre-mixing passages for the time of arriving at required for combustion zone.Along the outlet 34 that pre-mixing passages 29 is arranged, arrange, so corresponding from different time delay based on their differences in pre-mixing passages 29.Can give in pre-mixing passages 29 that each exports different time delay thus.
Fig. 3 represents the combustion chamber by an embodiment of the present invention shown in Fig. 2, the detail drawing in the second burner apparatus region of axial second stage.A part of combustion box 21 is illustrated in figure, it is around the first combustion zone 23 (illustrating a part in figure) and the second combustion zone 24 (illustrating a part in figure) being connected to its downstream, wherein, to be included in the second burner apparatus, to import in the second combustion zone 24 for the preparation of the pre-mixing passages 29 of fuel/air mixture.In the pre-mixing passages 29 of hose-like design, import and be used in pre-mixing passages 29, spray into the fuel supply system 33 of fuel 35 and the air feeder 32 of sectional design.The air feeder 32 of sectional design comprises outlet 34a, 34b, 34c for input air 40 of importing in pre-mixing passages 29, can give the delay time T that outlet 34a, 34b, 34c are different here
1, τ
2, τ
3.Such as, the volume of air of discharging from outlet 34a mixes with the fuel 35 that feedway 33 sprays into by burning flow through, and here, from the position exporting 34a, in order to arrive in the second combustion zone 24 need one perdurabgility τ
1.In order to decay or blanketing frequency f chamber pressure fluctuation, outlet 34a, 34b and 34c position can advantageously be chosen as, make τ
1-τ
3> 1/f.Fluctuated, when fuel/air mixture is lighted in the second combustion zone 24, based on different delay time T by the fluctuate atmospheric density that causes in exit of the chamber pressure of frequency f
1, τ
2, τ
3, can be superposed to and these density fluctuations are cancelled each other substantially.For this reason, can correspondingly select to export 34a, 34b, 34c layout along pre-mixing passages 29.Frequency f chamber pressure fluctuation can relate to a kind of design based on combustion chamber can preferential excitation chamber pressure fluctuation.It also can be called preferential chamber pressure fluctuation.The one expansion design of illustrated embodiment can also specify, the same sectional design (not illustrating here) of fuel supply system 33.
Claims (6)
1. the combustion chamber for gas turbine (1) (10,20), comprises
-at least one combustion zone (23,24), and
-at least one is for the burner apparatus (11,28) at combustion zone (23,24) combust fuel/air mixture,
-wherein, burner apparatus (11,28) comprises the pre-mixing passages for the preparation of fuel/air mixture (29) at least one remittance combustion zone (23,24), and in pre-mixing passages (29), import one be included in air feeder (32) in burner apparatus (11,28) and at least one fuel supply system (33)
It is characterized by: air feeder (32) sectional design, thus outlet in the remittance pre-mixing passages (29) of described segmented air feedway (34,34a, 34b, 34c) can be given with different (τ time delay
1, τ
2, τ
3), wherein, described time delay according to the air entered in pre-mixing passages for the time of arriving at required for combustion zone is determined, the minimum delay time τ of described segmented air feedway
minwith maximum delay time τ
maxthe relation fluctuated with the chamber pressure of the frequency f that will suppress, applicable elements: τ
max-τ
min> 1/f, and outlet in the remittance pre-mixing passages (29) of described segmented air feedway (32) (34,34a, 34b, 34c) is arranged as, make by least one frequency f ' preferential chamber pressure fluctuate, density fluctuation by causing in outlet (34a, 34b, 34c) fluid that inputs in pre-mixing passages (29), based on give (the τ different time delay of outlet (34,34a, 34b, 34c)
1, τ
2, τ
3), and be superposed to these density fluctuations are cancelled each other substantially.
2. according to combustion chamber according to claim 1 (10,20), it is characterized by, except the air feeder (32) of described sectional design, same sectional design one imports the fuel supply system that also can add fuel gas in pre-mixing passages (29).
3. according to the combustion chamber (10,20) one of all claims in prostatitis Suo Shu, it is characterized by, the pre-mixing passages (29) of burner apparatus (28) imports in second combustion zone (24), wherein, first combustion zone (23) with the first burner apparatus (11) is set in the upstream of this second combustion zone (24).
4. according to combustion chamber (10 according to claim 3, 20), it is characterized by, described burner apparatus (28) comprises one in outside around combustion box (12, 21) fuel arranged distributes ring (36) and multiple pre-mixing passages (29), wherein, pre-mixing passages (29) by its one end at combustion box (12, 21) import in combustion zone (24), and along separate routes fuel supply system (33) is out corresponding to distribute ring (36) with at least one from fuel, the outlet (34 of segmented air feedway (32) is at least set along one of them pre-mixing passages (29) with distributing, 34a, 34b, 34c).
5. one kind has the gas turbine (1) of at least one combustion chamber (10,20), it is characterized by: design at least one according to the combustion chamber (20) one of Claims 1-4 Suo Shu.
6. the burner apparatus for gas turbine (1) (28), is characterized by: it is the part according to the described combustion chamber of one of Claims 1-4 (20).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP11187285.9A EP2587158A1 (en) | 2011-10-31 | 2011-10-31 | Combustion chamber for a gas turbine and burner assembly |
| EP11187285.9 | 2011-10-31 | ||
| PCT/EP2012/070783 WO2013064383A1 (en) | 2011-10-31 | 2012-10-19 | Combustion chamber for a gas turbine and burner arrangement |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104024737A CN104024737A (en) | 2014-09-03 |
| CN104024737B true CN104024737B (en) | 2016-04-06 |
Family
ID=47115871
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201280065621.7A Expired - Fee Related CN104024737B (en) | 2011-10-31 | 2012-10-19 | For combustion chamber and the burner apparatus of gas turbine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20140260265A1 (en) |
| EP (2) | EP2587158A1 (en) |
| CN (1) | CN104024737B (en) |
| WO (1) | WO2013064383A1 (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150159877A1 (en) * | 2013-12-06 | 2015-06-11 | General Electric Company | Late lean injection manifold mixing system |
| US9803555B2 (en) * | 2014-04-23 | 2017-10-31 | General Electric Company | Fuel delivery system with moveably attached fuel tube |
| CN105650678B (en) * | 2016-01-11 | 2018-04-10 | 清华大学 | The combustion chamber charge structure of Turbine piston hybrid power system |
| US20170260866A1 (en) * | 2016-03-10 | 2017-09-14 | Siemens Energy, Inc. | Ducting arrangement in a combustion system of a gas turbine engine |
| JP2018004138A (en) * | 2016-06-30 | 2018-01-11 | 川崎重工業株式会社 | Gas turbine combustor |
| US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
| US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005003634A1 (en) * | 2003-07-04 | 2005-01-13 | Siemens Aktiengesellschaft | Burner unit for a gas turbine, and gas turbine |
| WO2010106034A2 (en) * | 2009-03-17 | 2010-09-23 | Siemens Aktiengesellschaft | Method for operating a burner and burner, in particular for a gas turbine |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB9929601D0 (en) * | 1999-12-16 | 2000-02-09 | Rolls Royce Plc | A combustion chamber |
| US6427446B1 (en) * | 2000-09-19 | 2002-08-06 | Power Systems Mfg., Llc | Low NOx emission combustion liner with circumferentially angled film cooling holes |
| GB2390150A (en) * | 2002-06-26 | 2003-12-31 | Alstom | Reheat combustion system for a gas turbine including an accoustic screen |
| EP2078898A1 (en) * | 2008-01-11 | 2009-07-15 | Siemens Aktiengesellschaft | Burner and method for reducing self-induced flame oscillations |
| US9032737B2 (en) * | 2009-12-30 | 2015-05-19 | Rolls-Royce North American Technologies, Inc. | Combustor added to a gas turbine engine to increase thrust |
-
2011
- 2011-10-31 EP EP11187285.9A patent/EP2587158A1/en not_active Withdrawn
-
2012
- 2012-10-19 US US14/355,467 patent/US20140260265A1/en not_active Abandoned
- 2012-10-19 EP EP12780155.3A patent/EP2773907A1/en not_active Withdrawn
- 2012-10-19 CN CN201280065621.7A patent/CN104024737B/en not_active Expired - Fee Related
- 2012-10-19 WO PCT/EP2012/070783 patent/WO2013064383A1/en active Application Filing
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005003634A1 (en) * | 2003-07-04 | 2005-01-13 | Siemens Aktiengesellschaft | Burner unit for a gas turbine, and gas turbine |
| WO2010106034A2 (en) * | 2009-03-17 | 2010-09-23 | Siemens Aktiengesellschaft | Method for operating a burner and burner, in particular for a gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| US20140260265A1 (en) | 2014-09-18 |
| CN104024737A (en) | 2014-09-03 |
| EP2773907A1 (en) | 2014-09-10 |
| EP2587158A1 (en) | 2013-05-01 |
| WO2013064383A1 (en) | 2013-05-10 |
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