CN1403745A - Gas turbine combustion chamber - Google Patents
Gas turbine combustion chamber Download PDFInfo
- Publication number
- CN1403745A CN1403745A CN02126826.6A CN02126826A CN1403745A CN 1403745 A CN1403745 A CN 1403745A CN 02126826 A CN02126826 A CN 02126826A CN 1403745 A CN1403745 A CN 1403745A
- Authority
- CN
- China
- Prior art keywords
- combustion chamber
- cylindrical member
- mix
- gas
- diameter
- 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.)
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Classifications
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- 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
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/78—Cooling burner parts
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- 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
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/74—Preventing flame lift-off
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- 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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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- 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
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- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
A gas turbine combustor is improved to enhance a cooling effect and a flame holding ability to thereby reduce NOx generation. A combustor 13 comprises a double structure of an inner cylindrical member 13a and an enlarged outer cylindrical member 13b to thereby enlarge a diameter of a combustion zone. A pre-mixing nozzle 11 comprises an outer sleeve 23 of which front end is projected beyond a base plate 17 and a pre-mixing nozzle portion 21 of the inner side. Air flows between the outer sleeve 23 and the pre-mixing nozzle portion 21 for enhancing the cooling effect of the pre-mixing nozzle 11. High temperature gas inner and outer circulating flows 15, 16 are formed in the combustion zone to enhance the flame holding ability. Pilot fuel quantity, as so far necessitated for flame holding, is reduced and NOx quantity generated of the pilot fuel is reduced. The base plate 17 exposed to the high temperature gas is prevented from being overheated by the projected front portion of the pre-mixing nozzle 11.
Description
Technical field
The present invention relates to a kind of gas-turbine combustion chamber of realizing low NOx combustion.
Background technology
Fig. 4 (a) and (b) schematically represent the gas-turbine combustion chamber of prior art, wherein Fig. 4 (a) is a longitudinal section, the inside of combustion chamber is shown, and Fig. 4 (b) is the front view of combustion chamber one side of something.At Fig. 4 (a) with (b), main fuel 40 flows in eight pre-mix nozzles 31 arranging around its axis in combustion chamber body 36, closes with air pre-mixing then, and is as mentioned below, forms main premix with in the combustion zone that is supplied to combustion chamber 33.With feed-in combustion chamber 33, the inner rim space segment of the combustion chamber body 36 of flowing through is shown in the arrow 50 of Fig. 4 (a) by compressor (not shown) supply air.On the other hand, auxiliary fuel 41 flows to the pilot jet 32 that is arranged on combustion chamber body 36 axis, thereby lights to burn at this with main premix to spray into combustion chamber 33. auxiliary fuels 41.On pilot jet 32, be provided with a flame and keep cone 34, and keep the flame that high temperature circulation air-flow 35 that cone 34 forms is kept auxiliary fuel 41 by flame.This combustion chamber has pre-mix nozzle and aforesaid formation, is commonly referred to as the low NOx combustion chamber.
In the premixed flame type low NOx combustion chamber of above-mentioned prior art, the flame of pilot jet 32 is kept by the flame of diffusion, in other words, keep the high temperature circulation air-flow 35 that cone 34 forms by flame and keep, thereby reduced the amount of the NOx that produces by pre-mix nozzle 31.Yet the NOx amount that is produced by the diffusion flame of pilot jet 32 can not be suppressed, and can make to realize that on the whole low NOx produces the restriction that is subjected to this value.
Summary of the invention
Therefore, an object of the present invention is to provide a kind of gas-turbine combustion chamber, this gas-turbine combustion chamber is configured, and both improves flame by the high-temperature fuel gas circular flow and keeps ability, thereby the cooling that improves pre-mix nozzle again is to reduce auxiliary fuel consumption, reduces the NOx amount that auxiliary fuel produces simultaneously.
In order to reach described purpose, the invention provides the measure of following (1) to (4) item:
(1) gas-turbine combustion chamber, be included in pilot jet and a plurality of pre-mix nozzle of arranging around described pilot jet arranged on the axis of described combustion chamber, it is characterized in that, the diameter of the combustion zone of described combustion chamber is to set like this, make the area that on the sagittal plane of combustion chamber, presents, area in the outside of the inboard of combustion zone and centring ring, centring ring is defined as the circle of whole central axis of arranging a plurality of pre-mix nozzles thereon, less than the area that presents by a plurality of pre-mix nozzles in the outside of centring ring, be all a plurality of pre-mix nozzles area half or more than.
(2) gas-turbine combustion chamber described in above measure (1), it is characterized in that the outstanding distance that each of a plurality of pre-mix nozzles has outstanding substrate that surpasses this pre-mix nozzle of supporting of its front end and a this outstanding front end is set at more than 1/3rd or 1/3rd of external diameter of pre-mix nozzle.
(3) gas-turbine combustion chamber described in above measure (1), it is characterized in that, the double structure with inner member and external member is made in the front portion of each of a plurality of pre-mix nozzles, keeps predetermined gap between this inner member and external member, and air flows in the crack during this time.
(4) gas-turbine combustion chamber described in above measure (1), it is characterized in that, the combustion chamber body is as the shell of combustion chamber, cylindrical member and Outer cylindrical member in comprising therein, interior cylindrical member is arranged to such an extent that hold a plurality of pre-mix nozzles, and the internal diameter of Outer cylindrical member is done greater than the external diameter of interior cylindrical member, and arrange hold in cylindrical member leading section and extend in the downstream of cylindrical member, to cover the combustion zone, can must surpass the enlarged-diameter of combustion zone the internal diameter of interior cylindrical member with this.
In measure of the present invention (1), the diameter that produces the combustion zone of high-temperature fuel gas is to set like this, make the sectional area of the sectional area in the inboard and centring ring outside, combustion zone less than the pre-mix nozzle in the centring ring outside, be all in advance the sectional area of mix nozzles half or more than.With this structure, the neighboring spatial portion of combustion zone is extended, and forms the gas stagnant area in this spatial portion, promptly in the neighboring spatial portion before pre-mix nozzle.The outside high-temperature gas circular flow that produces by the premix burning from pre-mix nozzle is formed on this gas stagnant area.In addition, the internal high temperature gas circulation stream of auxiliary fuel generation is formed on the central space portion that flame is kept the preceding combustion zone of the other pilot jet of cone.Like this, by inside and outside high-temperature gas circular flow, can improve the flame of combustion chamber widely and keep ability.Thereby, can reduce the amount of keeping requisite auxiliary fuel so far for flame, can reduce the Nox value that the auxiliary fuel burning produces, realize that on the whole low-down NOx produces.
In measure of the present invention (2), each of a plurality of pre-mix nozzles has the outstanding substrate that surpasses of front end, makes substrate can not directly be exposed to the high-temperature gas circular flow.Thereby prevented that substrate is overheated, and can realize the effect of measure of the present invention (1) more reliably.
In measure of the present invention (3), each of a plurality of pre-mix nozzles has its front portion and makes the double structure with inner member and external member, keep predetermined gap between this inner member and external member, air flows in the crack during this time, is used to cool off pre-mix nozzle.Thereby prevented that pre-mix nozzle is overheated, and can realize the effect of measure of the present invention (1) more reliably.
In measure of the present invention (4), the combustion chamber body comprises interior cylindrical member and Outer cylindrical member therein as the shell of combustion chamber.The internal diameter of Outer cylindrical member is done greater than the external diameter of interior cylindrical member.Thereby the diameter of combustion zone is outwards enlarged, make to be easy in the neighboring spatial portion of the pre-preceding combustion zone of mix nozzle, form the gas stagnant area.The outside high-temperature combustion gas circular flow that produces by the premix burning from pre-mix nozzle is formed on this gas stagnant area, and has improved flame and kept ability.Therefore can further guarantee to realize the effect that low NOx produces by measure of the present invention (1).
Description of drawings
Fig. 1 (a) and (b) schematically represent gas-turbine combustion chamber according to an embodiment of the invention, wherein Fig. 1 (a) is a longitudinal section, the inside of combustion chamber is shown, and Fig. 1 (b) is the front view of combustion chamber one side of something.
Fig. 2 is the longitudinal section of the amplification of one of pre-mix nozzle.
Fig. 3 is and identical view shown in Fig. 1 (a) wherein to have increased the part of hatching.
Fig. 4 (a) and (b) schematically represent the gas-turbine combustion chamber of prior art, wherein Fig. 4 (a) is a longitudinal section, the inside of combustion chamber is shown, and Fig. 4 (b) is the front view of combustion chamber one side of something.
The specific embodiment
Below, accompanying drawings is according to one embodiment of present invention.
Fig. 1 (a) and (b) schematically represent the gas-turbine combustion chamber of this embodiment, wherein Fig. 1 (a) is a longitudinal section, the inside of combustion chamber is shown, and Fig. 1 (b) is the front view of combustion chamber one side of something.At Fig. 1 (a) with (b), label 10 expression combustion chamber bodies, as the shell of combustion chamber, eight pre-mix nozzles 11 are located at wherein, and the axis that centers on combustion chamber body 10 interconnects.Pre-mix nozzle 11 structures are able to the outstanding substrate 17 that surpasses of its front end, and this will be in hereinafter explanation.Label 11 expression pilot jets, this pilot jet is arranged on the axis of combustion chamber body 10.Label 13 expression combustion chambers, this combustion chamber comprises combustion chamber body 10 and the miscellaneous part that is arranged in wherein.Cylindrical member 13a and Outer cylindrical member 13b in combustion chamber body 10 comprises therein.The internal diameter of Outer cylindrical member 13b is done both greater than the external diameter of interior cylindrical member 13a, again greater than the external diameter of the cylindrical member of the combustion chamber of prior art.Outer cylindrical member 13b arranges to such an extent that hold the leading section of interior cylindrical member 13a and the downstream of extending interior cylindrical member 13a, to cover the combustion zone of combustion chamber 13.Label 14 expression flames are kept cone, and this flame is kept cone and cancelled its leading section, and the flame that makes it to be shorter than prior art is kept cone.Label 17 expression substrates, this is the lip-deep member of inner peripheral wall of cylindrical member 13a in eight pre-mix nozzles 11 are supported to.
Fig. 2 is the longitudinal section of the amplification of one of pre-mix nozzle 11.The double structure of the outer sleeve 23 with inboard premix spray nozzle part 21 and outside is made in the front portion of this pre-mix nozzle 11.Omitted in the drawings, a plurality of ribs member supportings of outer sleeve 23 processes are on premix spray nozzle part 21.The pre-mix nozzle of prior art cuts off in substrate position at its front end, and is further not outstanding, and pre-mix nozzle 11 of the present invention is in the outstanding substrate 17 that surpasses of its front end.In other words, the outstanding forward position that surpasses substrate 17 of the front end of outer sleeve 23.Label 14 expression flames are kept cone, and this cone leading section is by the projection brachymemma of outer sleeve 23.Swirler blade of label 22 expressions, its structure is identical with prior art.
In the above combustion chamber of describing that sees figures.1.and.2, main fuel 40 flow in eight pre-mix nozzles 11 and with air pre-mixing to form premix, be used in the combustion chamber 13 combustion zone and burn.Air is by the inner rim spatial portion of compressor (not shown) supply with the combustion chamber body 10 of flowing through in the feed-in combustion chamber 13, shown in arrow 50 among Fig. 1 (a), flow through the then neighboring spatial portion of the premix spray nozzle part 21 and the premix spray nozzle part 21 of flowing through is shown in the arrow among Fig. 2 51.On the other hand, auxiliary fuel 41 infeeds in the combustion chamber 13 through the pilot jet 12 of center, combustion chamber, and burns with premix in this chamber.
Preceding central space portion in that the flame of pilot jet 12 is kept cone 14 produces circular flow 15 in the high-temperature gas by auxiliary fuel.In addition, the inner rim spatial portion at the Outer cylindrical member 13b of pre-mix nozzle 11 fronts produces high-temperature gas outer circulation stream 16 by the premix that enters from pre-mix nozzle 11.Thereby, carry out flame reliably and keep by these two circulating currents 15,16.Because the structure of combustion chamber 13, be cylindrical member 13a and Outer cylindrical member 13b in combustion chamber 13 comprises, and do the internal diameter of Outer cylindrical member 13b greatlyyer, thereby in the inner rim spatial portion of the front Outer cylindrical member 13b of pre-mix nozzle 11, form the gas stagnant area.Like this, the high-temperature combustion gas that produces along with the burning of main premix circulates, and forms high-temperature gas outer circulation stream 16 in this gas stagnant area.
Keep the flame that circular flow causes in the high-temperature gas that cone 14 produces and keep along with increasing flame, because the structure of circulating current and outer circulation air- flow 15,16 in the high-temperature gas has been strengthened flame widely and kept ability.Thereby, keep needed auxiliary fuel consumption for flame so far and can reduce, thereby can reduce the NOx that auxiliary fuel produces, realize the burning of very low NOx.
As the explanation that reference Fig. 2 is done, pre-mix nozzle 11 comprises swirler blade 22, premix spray nozzle part 21 and outer sleeve 23.The premix spray nozzle part 21 that outer sleeve 23 is arranged inboardly with it keeps predetermined gap, and shown in arrow among Fig. 2 51, air flows into this gap, thereby can cool off mix nozzle portion 21 and the outer sleeve 23 that is subjected to the high-temperature gas heating effectively.
And, the front end of the pre-mix nozzle 11 that forms by the front end of outer sleeve 23, the outstanding substrate 17 that surpasses.Owing to the part of this projection, prevent from directly to be exposed to substrate 17 superheated of high-temperature gas outer circulation stream 16.Among Fig. 2, L is the outstanding distance of jut, the just front side surface of substrate 17 and the distance between mix nozzle 11 front ends in advance, and D is the external diameter of pre-mix nozzle 11, the external diameter of outer sleeve 23 just, if L is set to D/3 or above (L 〉=D/3) just can improve the effect that prevents that substrate 17 is overheated.
Fig. 3 is and the identical view of Fig. 1 (a), has wherein increased hatched part.In Fig. 3, alphabetical P is defined as and is centring ring, and this is a circle of arranging all pre-mix nozzles 11 thereon.Internal diameter corresponding to the Outer cylindrical member 13b of the diameter of combustion zone in the combustion chamber is to set like this, make the area that presents on the sagittal plane, combustion chamber, outside cylindrical member 13b inboard and at the area in the outside of centring ring P less than the shared area of the pre-mix nozzle 11 in the outside of centring ring P, that is to say, among Fig. 3 the shared area of dashed area be all pre-mix nozzles 11 area half or more than.By the diameter in such selective combustion Indoor Combustion district, in the preceding outer space portion of pre-mix nozzle 11, form the above-mentioned gas stagnant area effectively, keep ability thereby can improve flame widely.
According to the gas-turbine combustion chamber of above-mentioned formation, can be reduced the effect of NOx significantly.For example, the amount of NOx can be reduced to 10PPM or following by the 25PPM of prior art.
Although described the preferred embodiments of the present invention in the above, should be appreciated that to the invention is not restricted to concrete structure and arrangement illustrated and that describe here, but comprise its modification that falls in claims scope.
Claims (4)
1. gas-turbine combustion chamber, be included in pilot jet and a plurality of pre-mix nozzle of arranging around described pilot jet arranged on the axis of described combustion chamber, the diameter of the combustion zone of wherein said combustion chamber is to set like this, make the area that on the sagittal plane of described combustion chamber, presents, area in the outside of the inboard of described combustion zone and centring ring, centring ring is defined as the circle of whole central axis of arranging described a plurality of pre-mix nozzles thereon, less than the area that presents by the described a plurality of pre-mix nozzles in the outside of described centring ring, be all described a plurality of pre-mix nozzles area half or more than.
2. gas-turbine combustion chamber according to claim 1, it is characterized in that the outstanding distance that each of described a plurality of pre-mix nozzles has outstanding substrate that surpasses the described pre-mix nozzle of supporting of its front end and a this outstanding front end is set at more than 1/3rd or 1/3rd of external diameter of described pre-mix nozzle.
3. gas-turbine combustion chamber according to claim 1, it is characterized in that, the double structure with inner member and external member is made in the front portion of each of described a plurality of pre-mix nozzles, keeps predetermined gap between described inner member and described external member, and air can flow in described gap.
4. gas-turbine combustion chamber according to claim 1, it is characterized in that, the combustion chamber body is as the shell of described combustion chamber, cylindrical member and Outer cylindrical member in comprising therein, cylindrical member is arranged to such an extent that hold described a plurality of pre-mix nozzle in described, and the internal diameter of described Outer cylindrical member is done greater than the external diameter of cylindrical member in described, and arrange hold described in cylindrical member leading section and extend described in the downstream of cylindrical member, to cover described combustion zone, can must surpass the enlarged-diameter of described combustion zone the internal diameter of described interior cylindrical member with this.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001254360A JP2003065537A (en) | 2001-08-24 | 2001-08-24 | Gas turbine combustor |
| JP254360/2001 | 2001-08-24 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1403745A true CN1403745A (en) | 2003-03-19 |
| CN1172116C CN1172116C (en) | 2004-10-20 |
Family
ID=19082534
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB021268266A Expired - Fee Related CN1172116C (en) | 2001-08-24 | 2002-07-22 | Gas turbine combustion chamber |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20030037549A1 (en) |
| EP (1) | EP1288576A3 (en) |
| JP (1) | JP2003065537A (en) |
| CN (1) | CN1172116C (en) |
| CA (1) | CA2394118A1 (en) |
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| CN1704574B (en) * | 2004-06-03 | 2010-05-26 | 通用电气公司 | Fuel nozzle and method for cooling fuel nozzle |
| CN101029742B (en) * | 2006-02-27 | 2010-08-18 | 三菱重工业株式会社 | Combustor |
| CN102168851A (en) * | 2009-10-23 | 2011-08-31 | 通用电气公司 | Fuel flexible combustor system and method |
| CN102444911A (en) * | 2010-10-11 | 2012-05-09 | 通用电气公司 | Combustor with lean pre-nozzle fuel injection system |
| CN101793408B (en) * | 2009-02-04 | 2012-10-03 | 燃气涡轮机效率瑞典公司 | Combustor nozzle |
| CN103210257A (en) * | 2011-03-30 | 2013-07-17 | 三菱重工业株式会社 | Nozzle, gas turbine combustor and gas turbine |
| CN104246371A (en) * | 2012-03-29 | 2014-12-24 | 埃克森美孚上游研究公司 | Turbomachine combustor assembly |
| CN104508381A (en) * | 2012-09-24 | 2015-04-08 | 三菱日立电力系统株式会社 | Gap measurement device for combustor, and gap measurement method |
| CN109654538A (en) * | 2018-12-07 | 2019-04-19 | 中国航发沈阳发动机研究所 | A kind of Venturi tube conducive to reduction Calculating Wall Temperature of Flame Tube |
| CN113739204A (en) * | 2021-08-23 | 2021-12-03 | 四川航天中天动力装备有限责任公司 | Pneumatic centrifugal backflow type fuel nozzle for backflow combustion chamber |
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| JP3986348B2 (en) * | 2001-06-29 | 2007-10-03 | 三菱重工業株式会社 | Fuel supply nozzle of gas turbine combustor, gas turbine combustor, and gas turbine |
| US7370466B2 (en) * | 2004-11-09 | 2008-05-13 | Siemens Power Generation, Inc. | Extended flashback annulus in a gas turbine combustor |
| DE102006051286A1 (en) * | 2006-10-26 | 2008-04-30 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Combustion device, has combustion chamber with combustion space and air injecting device including multiple nozzles arranged on circular line, where nozzles have openings formed as slotted holes in combustion space |
| US20090056336A1 (en) * | 2007-08-28 | 2009-03-05 | General Electric Company | Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine |
| US8733108B2 (en) * | 2010-07-09 | 2014-05-27 | General Electric Company | Combustor and combustor screech mitigation methods |
| CN102425793A (en) * | 2011-10-19 | 2012-04-25 | 中国科学院广州能源研究所 | Self-backheating swirling burner for fuel gas with low heat value |
| US9151502B2 (en) * | 2012-08-21 | 2015-10-06 | General Electric Company | System and method for reducing modal coupling of combustion dynamics |
| US8966909B2 (en) * | 2012-08-21 | 2015-03-03 | General Electric Company | System for reducing combustion dynamics |
| EP2700879B1 (en) * | 2012-08-24 | 2019-03-27 | Ansaldo Energia Switzerland AG | Method for mixing a dilution air in a sequential combustion system of a gas turbine, and sequential combustion system for a gas turbine comprising dilution air injector |
| JP6037736B2 (en) * | 2012-09-11 | 2016-12-07 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor and gas turbine engine equipped with the same |
| US9651259B2 (en) | 2013-03-12 | 2017-05-16 | General Electric Company | Multi-injector micromixing system |
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| US9650959B2 (en) | 2013-03-12 | 2017-05-16 | General Electric Company | Fuel-air mixing system with mixing chambers of various lengths for gas turbine system |
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| CN107726317A (en) * | 2017-11-29 | 2018-02-23 | 上海钜荷热力技术有限公司 | A kind of flat-plate burner with cooling device |
| CN109611891B (en) * | 2018-12-16 | 2020-11-06 | 中国航发沈阳发动机研究所 | Dry low-emission combustor |
| JP7112342B2 (en) * | 2019-01-25 | 2022-08-03 | 三菱重工業株式会社 | gas turbine combustor and gas turbine |
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| EP0193029B1 (en) * | 1985-02-26 | 1988-11-17 | BBC Brown Boveri AG | Gas turbine combustor |
| US4991398A (en) * | 1989-01-12 | 1991-02-12 | United Technologies Corporation | Combustor fuel nozzle arrangement |
| US5235814A (en) * | 1991-08-01 | 1993-08-17 | General Electric Company | Flashback resistant fuel staged premixed combustor |
| US5259184A (en) * | 1992-03-30 | 1993-11-09 | General Electric Company | Dry low NOx single stage dual mode combustor construction for a gas turbine |
| US5274991A (en) * | 1992-03-30 | 1994-01-04 | General Electric Company | Dry low NOx multi-nozzle combustion liner cap assembly |
| JP2954480B2 (en) * | 1994-04-08 | 1999-09-27 | 株式会社日立製作所 | Gas turbine combustor |
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| SE9802707L (en) * | 1998-08-11 | 2000-02-12 | Abb Ab | Burner chamber device and method for reducing the influence of acoustic pressure fluctuations in a burner chamber device |
-
2001
- 2001-08-24 JP JP2001254360A patent/JP2003065537A/en not_active Withdrawn
-
2002
- 2002-07-18 CA CA002394118A patent/CA2394118A1/en not_active Abandoned
- 2002-07-18 EP EP02016027A patent/EP1288576A3/en not_active Withdrawn
- 2002-07-19 US US10/198,368 patent/US20030037549A1/en not_active Abandoned
- 2002-07-22 CN CNB021268266A patent/CN1172116C/en not_active Expired - Fee Related
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1704574B (en) * | 2004-06-03 | 2010-05-26 | 通用电气公司 | Fuel nozzle and method for cooling fuel nozzle |
| CN101029742B (en) * | 2006-02-27 | 2010-08-18 | 三菱重工业株式会社 | Combustor |
| CN101793408B (en) * | 2009-02-04 | 2012-10-03 | 燃气涡轮机效率瑞典公司 | Combustor nozzle |
| CN102168851A (en) * | 2009-10-23 | 2011-08-31 | 通用电气公司 | Fuel flexible combustor system and method |
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| CN103210257B (en) * | 2011-03-30 | 2015-04-08 | 三菱日立电力系统株式会社 | Nozzle, gas turbine combustor and gas turbine |
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| CN104508381A (en) * | 2012-09-24 | 2015-04-08 | 三菱日立电力系统株式会社 | Gap measurement device for combustor, and gap measurement method |
| CN104508381B (en) * | 2012-09-24 | 2016-08-24 | 三菱日立电力系统株式会社 | The gap measuring apparatus of burner and gap measuring method |
| US9618333B2 (en) | 2012-09-24 | 2017-04-11 | Mitsubishi Hitachi Power Systems, Ltd. | Clearance measurement device and clearance measurement method for combustor |
| CN109654538A (en) * | 2018-12-07 | 2019-04-19 | 中国航发沈阳发动机研究所 | A kind of Venturi tube conducive to reduction Calculating Wall Temperature of Flame Tube |
| CN113739204A (en) * | 2021-08-23 | 2021-12-03 | 四川航天中天动力装备有限责任公司 | Pneumatic centrifugal backflow type fuel nozzle for backflow combustion chamber |
| CN113739204B (en) * | 2021-08-23 | 2023-02-03 | 四川航天中天动力装备有限责任公司 | Pneumatic centrifugal backflow type fuel nozzle for backflow combustion chamber |
| CN115325569A (en) * | 2022-09-02 | 2022-11-11 | 华能国际电力股份有限公司 | Combustion chamber, gas turbine and combustion control method |
| CN115325569B (en) * | 2022-09-02 | 2023-05-26 | 华能国际电力股份有限公司 | Combustion chamber, gas turbine and combustion control method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1172116C (en) | 2004-10-20 |
| EP1288576A2 (en) | 2003-03-05 |
| US20030037549A1 (en) | 2003-02-27 |
| JP2003065537A (en) | 2003-03-05 |
| EP1288576A3 (en) | 2004-01-07 |
| CA2394118A1 (en) | 2003-02-24 |
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