CN1133421A - Method and apparatus for starting a gas turbine combustor - Google Patents
Method and apparatus for starting a gas turbine combustor Download PDFInfo
- Publication number
- CN1133421A CN1133421A CN 95104374 CN95104374A CN1133421A CN 1133421 A CN1133421 A CN 1133421A CN 95104374 CN95104374 CN 95104374 CN 95104374 A CN95104374 A CN 95104374A CN 1133421 A CN1133421 A CN 1133421A
- Authority
- CN
- China
- Prior art keywords
- burner
- combustion chamber
- main
- ignition
- main burner
- 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
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000002485 combustion reaction Methods 0.000 claims abstract description 57
- 239000000446 fuel Substances 0.000 claims abstract description 27
- 239000007788 liquid Substances 0.000 claims abstract description 9
- 230000007935 neutral effect Effects 0.000 claims description 3
- 239000000203 mixture Substances 0.000 abstract description 12
- 238000004519 manufacturing process Methods 0.000 abstract 2
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 14
- 239000007789 gas Substances 0.000 description 12
- GQPLMRYTRLFLPF-UHFFFAOYSA-N Nitrous Oxide Chemical compound [O-][N+]#N GQPLMRYTRLFLPF-UHFFFAOYSA-N 0.000 description 8
- 239000002737 fuel gas Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000003134 recirculating effect Effects 0.000 description 3
- 241001672694 Citrus reticulata Species 0.000 description 2
- 238000001574 biopsy Methods 0.000 description 2
- 239000003550 marker Substances 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000001154 acute effect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000002459 sustained effect Effects 0.000 description 1
Images
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
- F23R3/34—Feeding into different combustion zones
-
- 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
- F23D14/26—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid with provision for a retention flame
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
- F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D23/00—Assemblies of two or more burners
-
- 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
-
- 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
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
-
- 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
- F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The object of the invention is to propose a method and a device for starting a combustion chamber in order to increase the efficiency of a gas turbine and to reduce the emission of NOx. According to the invention, the method for the production of a premix burner with a main burner and a pilot burner and the operation of these premix burners with gaseous and liquid fuels is achieved in such a way that the main burner (3) acts exclusively as a mixer for the production of the fuel and air mixture (25 ', 28'). The main burner (3) is ignited by a pilot burner (2) in a known manner. During operation of the combustion chamber (1, 29), the flame front (27') of the main burner (3) is stabilized continuously by the flame front (27) of the pilot burner (2).
Description
The present invention relates to a kind of method and apparatus of starting combustion chamber of gas turbine.
By the known a kind of bipyramid formula premix burner of EP-B1-0321809, it is made up of the part cone that two center lines stagger mutually.Be designed to the tangential admission seam in the both sides of burner, the fuel of the liquid state gaseous state that radially enters or that enter vertically mixes therein with the combustion air that comes from compressor stream.When the fuel-air mixture with very high peripheral speed separates, when promptly so-called vortex separates, form a kind of uniform fuel concentration of the best in the fuel device inlet region.
By these two part cones that radially relatively move, can increase the air inlet seam that between them, constitutes, and thereby changed the peripheral speed of fuel and air mixture form the optimum condition that vortex separates so that can create all the time according to service condition.
Known in gas-turbine combustion chamber by EP-A1-0387532, be provided with a plurality of such bipyramid formula burners at its end that becomes a mandarin.According to the combustion-supporting air quantity that flows through them, they or play ignition burner, or play main burner.These two kinds of burners alternately are arranged in a row in the combustion chamber.Thereby can make less ignition burner when full load, be operated in desirable admixture, when localised load, also therefore can accomplish less nitrogen oxide (NO
x) discharge capacity.
But, still have a sustained task that further reduces nitrogen oxide emission, yet can not accomplish this point with these known combustion chambers from the viewpoint of environmental protection.Proved already that the shortcoming of this class combustion chamber was that the bipyramid burner pressure loss is bigger.Its consequence is to have improved Fuel Consumption, has reduced power, thereby has reduced the efficient of gas turbine.
The present invention attempts to overcome all these shortcomings.The objective of the invention is to propose a kind of method and apparatus of starting chamber, with this discharge capacity that improves the efficient of gas turbine and reduce nitrogen oxide.
Achieving the above object by the present invention is to adopt the described method of claim 1 preamble, makes main burner only play the blender of preparation fuel and air mixture, and they are lighted in the known manner by ignition burner.When working in the combustion chamber, the flame front of main burner makes it stable by the flame front of ignition burner constantly.For this reason, what enter main burner is the combustion air with low swirl ratio, and what enter ignition burner is the combustion air with higher swirl ratio.
Advantage of the present invention is almost completely to have eliminated the discharged nitrous oxides that is caused by main burner so far.But have only when the residence time of fuel and air mixture in main burner more in short-term, could realize this burning that does not almost have nitrogen oxide.Therefore flow into the swirl ratio of the combustion air in the main burner, should be reduced to and no longer can form the degree that vortex separates.The main burner thereby the unstable blender that also only plays a part that becomes.
As everyone knows, the swirl ratio limiting value that causes vortex to separate is 0.7, so its swirl ratio of combustion air that enters main burner is at this below limiting value, and enters the combustion air of ignition burner, and its swirl ratio is on this limiting value.Therefore, do not have ignition burner, main burner can not can not be lighted when sub-load is worked when full load.By contrast, be to move by the main burner of known method so far low-levelly, so they can not stop working, and when working, sub-load can obtain the support of ignition burner when full-load operation.
The swirl ratio of desired minimizing main burner preferably reaches like this, promptly should make the ratio of air inlet seam and main burner discharge area, is designed to bigger than this corresponding ratio in the ignition burner.For this reason, or the air inlet seam of increase main burner, or reduce its discharge area.Reduce the subtended angle of main burner, also can reach same purpose.
Another advantage of the present invention program is to stitch owing to enlarged the air inlet of main burner, so reduced the pressure loss.Therefore, no matter be that power or its efficient of gas turbine can both be improved.
Because it is main burner and ignition burner are lined up the two neutral gear places of arranging and being located at each other at least, can improve the igniting of combustion chamber, make work more reliable, more reasonable when the Temperature Distribution ratio during sub-load has only row's burner.When every row only was provided with the identical bipyramid burner of structure, ignition burner guaranteed good horizontal igniting.Otherwise, in each row, alternately arrange main burner and ignition burner, can control main burner better, and more uniform radial temperature profile can be arranged in the combustion chamber.
Power is produced by the main burner that does not almost have nitrogen oxide, and the flame temperature of ignition burner only brought up to guarantee the stable degree of various duty lower combustion chamber.
In another kind of version of the present invention, Combustion chamber design is a toroidal combustion chamber, and the bipyramid burner is lined up three rows, and lines up circle in known manner in a public vertical plane.In this case, row's ignition burner is set between two row's main burners.Adopt this structure to obtain relation between a kind of particularly advantageous ignition burner and the main burner, at this moment, because the negligible amounts of ignition burner, so can further reduce the discharge capacity of nitrogen oxide.In addition, can be together or connect respectively and cut off if two row's main burners are arranged to, then can on purpose influence radial temperature profile, thereby higher load can be arranged at the blade tip of turbine.
Improve the flame temperature in the ignition burner, can advantageously improve the flame-out characteristic of combustion chamber, meanwhile can not increase the discharging of nitrogen oxide significantly.
Accompanying drawing has been represented various embodiments of the present invention by means of a kind of circle or toroidal combustion chamber and single burner.Wherein:
Fig. 1 is equipped with the gas turbine circular chamber of different bipyramid burners to overlook signal
Figure;
Fig. 2 is designed to the ignition burner side view of bipyramid burner, biopsy cavity marker devices and perspective
Expression;
Fig. 3 is designed to the main burner side view of bipyramid burner, biopsy cavity marker devices and perspective table
Show;
The rough schematic view of the IV-IV section of Fig. 4 Fig. 2;
The rough schematic view of the V-V section of Fig. 5 Fig. 3;
Fig. 6 is equipped with the bowing of gas turbine toroidal combustion chamber fragment of different bipyramid burners
Look schematic diagram;
The another kind of version of Fig. 7 is corresponding to the schematic diagram of Fig. 6;
The another kind of version of Fig. 8 is corresponding to the schematic diagram of Fig. 6;
Only represented among the figure that those are the member of understanding necessity of the present invention.Except that combustion chamber and burner, other member of gas turbine is expression not.The flow direction of working media is represented with arrow in the drawings.
In the circular chamber 1 of gas turbine, in a common plane, arranging a plurality of bipyramid formula burners circlewise as ignition burner 2 or main burner 3.Wherein, alternately then be row's ignition burner 2 (Fig. 1) from outside to inside behind row's main burner 3.
The ignition burner 2 that is designed to traditional bipyramid formula burner is made up of two 1/2nd hollow cones 4,5, and they stagger mutually and folded mutually (Fig. 2) each other along side direction.The center line 6,7 of part cone 4,5 thereby also along side direction stagger each other (Fig. 4).In the both sides of ignition burner 2, become mirrorimage structures ground respectively to cause a tangential air inlet seam 8,9 in this way.Combustion air 10 flows into the inner chamber of ignition burner 2 by these air inlet seams 8,9, that is flows in the conical cavity 11 (Fig. 2).
These two part cones 4,5 respectively have a cylindrical The initial segment 12,13, and similar with part cone 4,5, they stagger equally each other.Therefore, the side that becomes a mandarin of tangential admission seam 8,9 is designed to along the total length of ignition burner 2.Do not have nozzle 14 in cylindrical The initial segment 12,13, its fuel nozzle ports 15 is located at the narrowest cross-section of the conical cavity that is made of two part cones 4,5 11.Certainly, ignition burner 2 also can be designed to not have the simple taper of cylindrical The initial segment 12,13.
On two part cones 4,5 and in the outer end of tangential admission seam 8,9, be equipped with cartridge 16,17.Be shaped on some holes 18 on the cartridge 16,17, fuel gas 19 enters in the conical cavity 11 of ignition burner 2 by these holes 18.These fuel gas 19 and combustion air 10 blending of flowing through tangential admission seam 8,9.Blending is carried out in the location of tangential admission seam 8,9.These two part cones 4,5 have a less subtended angle 20.The combustion chamber end 21 of ignition burner 2 has the end plate 22 of standing part cone 4,5 usefulness.
Spray into conical cavity 11 through nozzle 14 flowing liquid fuel 23 by an acute angle, so in the plane of the exit face 24 of ignition burner 2, have fuel cone as far as possible uniformly.The rotary combustion-supporting air 10 that the liquid fuel section 25 of this taper is tangentially flowed into is surrounded.The concentration of liquid fuel 23 reduces gradually owing to constantly mix combustion air 10 vertically.Along the entire cross section optimum and uniformly fuel concentration is to separate (Vortex-Breakdown) to distinguish at vortex, promptly in the recirculating zone 26.Igniting 26 top is carried out in the recirculating zone.Only could set up stable fire and strive forward 27 in this position.Burnt if be blended into the fuel gas 19 that goes in the combustion air 10, formed fuel and air mixture 28 so there equally in tangential admission seam 8,9 outer ends.
In the circular chamber 1 of gas turbine, have the combustion air 10 of low swirl ratio ' enter main burner 3, the combustion air 10 with higher swirl ratio enters ignition burner 2.So stable flame front of having introduced above in ignition burner 2, can forming 27.The fuel and air mixture 25 of main burner 3 ', 28 ' light by adjacent ignition burner 2.In circular chamber's 1 course of work, the flame front 27 of main burner 3 ' flame front 27 by ignition burner 2 makes it stable (Fig. 1 to 3) constantly.
In second kind of embodiment, the Combustion chamber design of gas turbine circularizes combustion chamber 29, and has been equipped with two row's bipyramid burners, and they circularly all are arranged in the public vertical plane.Each row has only the identical bipyramid burner of structure, and wherein, that row of ignition burner 2 is outer, and that row of main burner 3 is located at the inside (Fig. 6).The ordering of this two rows burner also can be conversely.Equally also can in every row's bipyramid burner, main burner 3 also be arranged existing ignition burner 2, their arrangements alternate with each other in this row this moment, and be located at neutral position (Fig. 7) with respect to adjacent row.
In another kind of embodiment, the toroidal combustion chamber 29 of gas turbine is equipped with three row's bipyramid formula burners, and they are arranged in the public vertical plane circularly, and wherein, row's ignition burner 2 is located between two row's main burners 3 (Fig. 8).
Symbol table
1 figure combustion chamber, 22 end plates, 2 ignition burners, 23 liquid fuel 3 main burners, 24 exit faces (amassing), 4 part cones, 25 liquid fuel sections, fuel and air mixture 5 part cones 26 recirculating zones 6 center lines, 27 flame fronts, 7 center lines, 28 fuel and air mixtures, 8 tangential admissions stitch 29 toroidal combustion chambers, 9 tangential admissions seams, 4 ' part cone, 10 combustion airs, 5 ' part cone, 11 conical cavities, 6 ' center line, 12 cylindrical the initial segment 7 ' center line 13 cylindrical the initial segment 8 ' tangential admissions and stitch 14 nozzles, 9 ' tangential admission and stitch 15 fuel nozzle ports, 10 ' combustion air, 16 cartridges, 19 ' fuel gas, 17 cartridges, 20 ' subtended angle, 18 holes, 24 ' exit faces (amassing), 19 fuel gas, 25 ' fuel and air mixture, 20 subtended angles, 27 ' flame front, 21 combustion chambers, 28 ' fuel and air mixture
Claims (15)
1. the method for starting combustion chamber of gas turbine, the method has the premix burner that is designed to main burner and ignition burner, and their is characterized by with gaseous state and liquid fuel work:
A) main burner (3) only plays blender, is used for preparing fuel and air and mixes
Thing (25 ', 28 ');
B) main burner (3) is lighted by ignition burner (2) in known manner, and
C) in the course of work of combustion chamber (1,29), the flame front of main burner (3)
(27 ') make it steady by the flame front (27) of ignition burner (2) constantly
Fixed.
2. in accordance with the method for claim 1, it is characterized by: the combustion air (10 ') with low swirl ratio enters in the main burner (3), and the combustion air (10) with higher swirl ratio enters in the ignition burner (2).
3. according to claim 1 and 2 described methods, it is characterized by: the swirl ratio of the combustion air (10 ') of main burner (3) is lower, and the swirl ratio of the combustion air (10) of ignition burner (2) is greater than 0.7.
4. according to the described method of claim 1 to 3, it is characterized by: the major part of gaseous state and liquid fuel (19,23) is by main burner (3) burning, and the flame temperature of ignition burner (2) is only brought up to and can be guaranteed the stable degree in combustion chamber (1,29).
5. according to the described method of claim 1 to 4, it is characterized by: have the adjacent bipyramid burner co-operation of two rows at least.
6. according to the described method of claim 1 to 3, it is characterized by: main burning (3) co-operation that row's ignition burner (2) is adjacent with two rows, this two row's main burner (3) can switch on and off together or respectively.
7. it is characterized by in accordance with the method for claim 6: main burner (3) carries out work with the flow that will lack than ignition burner (2) to 1/2nd at most.
8. implement gas-turbine combustion chamber according to the described method of claim 1, wherein be provided with a plurality of bipyramid burners by the EP-B10321809 design, they or play ignition burner, or play main burner, it is characterized by: the ratio of the air inlet of main burner (3) seam (8 ', 9 ') and discharge area (24 ') is designed to this corresponding ratio greater than ignition burner (2).
9. according to the described combustion chamber of claim 8, it is characterized by: the air inlet of main burner (3) seam (8 ', 9 ') is designed to bigger than the air inlet seam of ignition burner (2).
10. according to the described combustion chamber of claim 8, it is characterized by: the discharge area (24 ') of main burner (3) is designed to littler than the discharge area of ignition burner (2).
11. according to the described combustion chamber of claim 8, it is characterized by: the subtended angle (20 ') of main burner (3) is designed to littler than the subtended angle (20) of ignition burner (2).
12. according to the described combustion chamber of claim 8 to 11, it is characterized by: main burner (3) and ignition burner (2) are arranged in two rows at least, and are located at neutral gear place each other.
13., it is characterized by: in each row, only be provided with the identical bipyramid burner of structure according to the described combustion chamber of claim 12.
14., it is characterized by according to the described combustion chamber of claim 12: existing main burner (3) in each row's bipyramid burner, ignition burner (2) is also arranged, they are alternately arranged in a row.
15. according to the described combustion chamber of claim 8 to 12, it is characterized by: the combustion chamber is designed to toroidal combustion chamber (29), the bipyramid burner is lined up three rows, they are arranged in the public vertical plane in known manner circularly, wherein, row's ignition burner (2) comes between two row's main burners (3).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19944412315 DE4412315B4 (en) | 1994-04-11 | 1994-04-11 | Method and device for operating the combustion chamber of a gas turbine |
| DEP4412315.9 | 1994-04-11 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1133421A true CN1133421A (en) | 1996-10-16 |
| CN1088172C CN1088172C (en) | 2002-07-24 |
Family
ID=6515035
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 95104374 Expired - Fee Related CN1088172C (en) | 1994-04-11 | 1995-04-10 | Method and apparatus for starting a gas turbine combustor |
Country Status (3)
| Country | Link |
|---|---|
| JP (1) | JP4106098B2 (en) |
| CN (1) | CN1088172C (en) |
| DE (1) | DE4412315B4 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101297156B (en) * | 2005-09-05 | 2010-10-20 | 西门子公司 | Burner arrangement for a combustion chamber, associated combustion chamber and method for combusting fuel |
| US8448445B2 (en) | 2008-02-04 | 2013-05-28 | Nuovo Pignone S.P.A. | Method for the start-up of a gas turbine |
| CN113028449A (en) * | 2021-02-26 | 2021-06-25 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Streamline fuel flow distribution disc of fuel gas generator |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19547914A1 (en) * | 1995-12-21 | 1997-06-26 | Abb Research Ltd | Premix burner for a heat generator |
| EP0979972A1 (en) * | 1998-08-12 | 2000-02-16 | Asea Brown Boveri AG | Burner arrangement with a main and a pilot burner and pilot burner for such an arrangement |
| GB2398863B (en) | 2003-01-31 | 2007-10-17 | Alstom | Combustion Chamber |
| US6968699B2 (en) * | 2003-05-08 | 2005-11-29 | General Electric Company | Sector staging combustor |
| EP1531305A1 (en) * | 2003-11-12 | 2005-05-18 | United Technologies Corporation | Multi-point fuel injector |
| WO2006094939A1 (en) | 2005-03-09 | 2006-09-14 | Alstom Technology Ltd | Burner comprising a premix for combustion chamber |
| US8479521B2 (en) | 2011-01-24 | 2013-07-09 | United Technologies Corporation | Gas turbine combustor with liner air admission holes associated with interspersed main and pilot swirler assemblies |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4194358A (en) * | 1977-12-15 | 1980-03-25 | General Electric Company | Double annular combustor configuration |
| DE3361535D1 (en) * | 1982-05-28 | 1986-01-30 | Bbc Brown Boveri & Cie | Gas turbine combustion chamber and method of operating it |
| CH674561A5 (en) * | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
| CH678757A5 (en) * | 1989-03-15 | 1991-10-31 | Asea Brown Boveri | |
| JPH02147610U (en) * | 1989-05-11 | 1990-12-14 | ||
| CH680084A5 (en) * | 1989-06-06 | 1992-06-15 | Asea Brown Boveri | |
| US5247797A (en) * | 1991-12-23 | 1993-09-28 | General Electric Company | Head start partial premixing for reducing oxides of nitrogen emissions in gas turbine combustors |
| US5289685A (en) * | 1992-11-16 | 1994-03-01 | General Electric Company | Fuel supply system for a gas turbine engine |
| DE4411623A1 (en) * | 1994-04-02 | 1995-10-05 | Abb Management Ag | Premix burner |
-
1994
- 1994-04-11 DE DE19944412315 patent/DE4412315B4/en not_active Expired - Fee Related
-
1995
- 1995-04-10 CN CN 95104374 patent/CN1088172C/en not_active Expired - Fee Related
- 1995-04-11 JP JP08580495A patent/JP4106098B2/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101297156B (en) * | 2005-09-05 | 2010-10-20 | 西门子公司 | Burner arrangement for a combustion chamber, associated combustion chamber and method for combusting fuel |
| US8448445B2 (en) | 2008-02-04 | 2013-05-28 | Nuovo Pignone S.P.A. | Method for the start-up of a gas turbine |
| CN101503977B (en) * | 2008-02-04 | 2015-02-25 | 诺沃皮尼奥内有限公司 | Method for the start-up of a gas turbine |
| CN113028449A (en) * | 2021-02-26 | 2021-06-25 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Streamline fuel flow distribution disc of fuel gas generator |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH07293886A (en) | 1995-11-10 |
| DE4412315A1 (en) | 1995-10-12 |
| DE4412315B4 (en) | 2005-12-15 |
| JP4106098B2 (en) | 2008-06-25 |
| CN1088172C (en) | 2002-07-24 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C53 | Correction of patent of invention or patent application | ||
| CB02 | Change of applicant information |
Address after: Baden, Switzerland Applicant after: Asea Brown Boveri AG Applicant before: Asea Brown Boveri AG |
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