EP1710502A2 - Gasbrenneranordnung für eine Gasturbine - Google Patents

Gasbrenneranordnung für eine Gasturbine Download PDF

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Publication number
EP1710502A2
EP1710502A2 EP06111895A EP06111895A EP1710502A2 EP 1710502 A2 EP1710502 A2 EP 1710502A2 EP 06111895 A EP06111895 A EP 06111895A EP 06111895 A EP06111895 A EP 06111895A EP 1710502 A2 EP1710502 A2 EP 1710502A2
Authority
EP
European Patent Office
Prior art keywords
holes
burner
assembly
gaps
feed line
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
Application number
EP06111895A
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English (en)
French (fr)
Other versions
EP1710502B1 (de
EP1710502A3 (de
Inventor
Federico Bonzani
Giacomo Pollarolo
Vittorio Corona
Carlo Piana
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia SpA
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Publication date
Application filed by Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Publication of EP1710502A2 publication Critical patent/EP1710502A2/de
Publication of EP1710502A3 publication Critical patent/EP1710502A3/de
Application granted granted Critical
Publication of EP1710502B1 publication Critical patent/EP1710502B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/286—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
    • F23R3/02—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
    • F23R3/34—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
    • 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
    • F23R2900/00016—Retrofitting in general, e.g. to respect new regulations on pollution
    • 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
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • the present invention relates to a gas burner assembly for a gas turbine.
  • Gas turbine combustors comprising a combustion chamber, and a burner assembly ( Figure 6) in turn comprising a peripheral burner (5) and a central burner (4).
  • the peripheral burner has swirl or turbulence vanes (6), commonly known as a "diagonal swirler", at the outlet, and is a so-called “premix” burner, i.e. conducts a stream of fuel gas and an air stream, which are mixed, with a high surplus of air with respect to the stoichiometric ratio, at the "diagonal" swirler, upstream from the flame area.
  • the central burner has a substantially axial swirler (16a), conducts a stream of combustion air through the swirler, and comprises two separate gas feed lines.
  • a first line (36a) generates a diffusion flame, i.e. injects a stream of fuel gas, in a practically stoichiometric ratio to the combustion air, by means of a number of nozzles (38a) on an inner cone (17a) of the axial swirler, so that combustion takes place inside the combustion chamber with substantially no premixing of the reactants.
  • the first feed line is mainly used for ignition and when starting or bringing the turbine up to speed. Once the turbine reaches an appropriate speed, and before it reaches nominal speed (3000 rpm), the peripheral premix burner is also activated : albeit for a short period of time, the turbine is therefore supplied simultaneously with gas burnt by the diffusion flame of the central burner and gas burnt by the premix flame of the peripheral burner ("mixed combustion").
  • a changeover is then made to "full-premix" mode, i.e. fuel gas is fed through the central burner from the second feed line (52a), and gas supply from the first line (36a) is cut off, so as to produce a pilot flame for ensuring stable combustion of the peripheral burner premix flame.
  • the second gas feed line terminates with four pipes (60) located inside respective gaps between the vanes of the axial swirler (16a); and the fuel gas supplied by the pipes (about 10% of the gas flowing through the burner assembly as a whole) is injected parallel to the burner axis to produce a diffusion-type, and therefore highly stable, pilot flame.
  • a premix flame burns at a lower temperature (1500°C as compared with 2000°C typical of a diffusion flame) and so produces fewer nitric oxide emissions.
  • a gas burner assembly for a gas turbine having an axis and comprising:
  • Number 1 in Figure 1 indicates a fuel gas burner assembly for a gas turbine (not shown).
  • Assembly 1 extends along an axis 2, generates, in use, combustion inside a chamber 3 (shown partly), and comprises a central burner 4, and a peripheral "premix" burner 5 coaxial with and surrounding burner 4.
  • Burner 5 has a swirl or turbulence generating device 6 known as a "swirler” and comprising a number of vanes 7 defining respective gaps 8. Gaps 8 conduct so-called “diagonally” into chamber 3 a stream of combustion air from an inlet 9 defined radially inwards by an externally conical, axially hollow body 11, and radially outwards by an annular, substantially conical wall 12.
  • Burner 5 comprises a fuel gas feed line 13 which terminates with an annular header 14 formed in body 11 and communicating with gaps 8 via passages 15 formed in vanes 7. More specifically, the fuel gas and combustion air mixture formed in gaps 8, with more air than the theoretical stoichiometric ratio, is swirled sufficiently by device 6 to produce a premix flame.
  • Burner 4 has another swirl or turbulence generating device (“swirler”) indicated 16 and comprising an inner cone 17, and an outer cone 18 which extends axially to form an extension of body 11 towards chamber 3.
  • swirl or turbulence generating device indicated 16 and comprising an inner cone 17, and an outer cone 18 which extends axially to form an extension of body 11 towards chamber 3.
  • cones 17, 18 have, respectively, an outer conical surface 19 and an inner conical surface 20, which are positioned facing each other to guide a stream of combustion air, and house between them ten vanes 21 defining respective gaps 22.
  • Vanes 21 have respective pressure faces; respective low-pressure faces; respective outer surfaces 23 resting on surface 20; and respective inner surfaces 24 resting on surface 19 and having respective fastening appendixes 26, which project along respective axes 27 converging at axis 2, and engage respective seats 28 formed in surface 19.
  • burner 4 comprises an axial tubular body 34 which extends to form an axial extension of cone 17, is connected integrally to cone 17, and houses a gas oil or fuel oil burner 35 projecting axially from cone 17 towards chamber 3.
  • Body 34 and burner 35 define radially, between them, an annular channel 36 for a first stream of fuel gas for producing a diffusion flame in chamber 3.
  • Channel 36 has a lateral inlet 37 formed in body 34; and an outlet defined by a number of nozzles 38 ( Figure 2) formed through cone 17 and debouching inside gaps 22 into which the combustion air also flows.
  • the combustion air comes from an annular channel 40 which is located upstream from device 16, is coaxial with channel 36, and houses a known ignition electrode 41 for producing an ignition spark inside gaps 22, and which is powered by a known electric line 42 located alongside body 34 and not described in detail.
  • Channel 40 is defined radially outwards by body 11 and radially inwards by a cylindrical outer surface 45 of body 34.
  • body 34 has four passages 46 (Figure 3), parallel to axis 2, for a second stream of fuel gas for producing a pilot flame in chamber 3.
  • Passages 46 debouch, at one end, inside an annular inlet header 47 and, at the opposite end, inside an annular header 48 bounded axially by a rear portion 49 of cone 17 and separated radially from channel 40 by a cylindrical wall portion 48a, which is therefore swept externally by the combustion air stream flowing into device 16. More specifically, portion 49 is joined, e.g. welded, in fluidtight manner to the axial end of body 34 and to wall portion 48a, i.e. on opposite radial sides of header 48.
  • Header 48 communicates with gaps 22 via seats 28 and cavities 29. More specifically, with reference to Figure 2, seats 28 communicate with header 48 via respective holes 50 formed through portion 49 in directions substantially parallel to surface 19, and each cavity 29 communicates with gaps 22 via six relatively small-diameter holes 51, of which three are formed on the low-pressure face, and three on the pressure face.
  • Holes 51 define respective nozzles having axes substantially perpendicular to the air flow direction, and for producing a premix pilot flame with a large surplus of air with respect to the stoichiometric ratio.
  • Nozzles 38 on the other hand, as stated, produce a diffusion flame with a practically stoichiometric fuel gas-combustion air ratio.
  • Device 16 simultaneously performs two functions : generating an appropriate amount of turbulence in the air stream; injecting the gaseous fuel by means of an appropriate number of holes (nozzles 51) in vanes 21. As such, the reactants are premixed completely before reaching the flame area. Best mixing is achieved by so contouring gaps 22 as to reduce losses caused by separation of the boundary layer.
  • the air flow into device 16 is set, at the start of the working life of device 16, to achieve an optimum compromise between stable combustion and sufficiently low nitric oxide emissions.
  • the above setting is made by means of a constriction or choke with a calibrated or predetermined cross section, and which is defined by a ring or annular plate 55 ( Figure 3) housed in fluidtight manner in channel 40, fixed, e.g. welded, to surface 45, and having a number of holes 56 spaced angularly about axis 2.
  • the number and diameter of holes 56 are such as to achieve a satisfactory predetermined combustion air flow value, in terms of nitric oxide emissions and flame stability, over a wide operating range of the turbine.
  • the air flow value is calibrated and improved as a function of the specific operating range of the turbine, and the emission range to be complied with, by further reducing and fine setting the flow section of holes 56, e.g. by inserting plugs or calibrated bushes (not shown), without impairing combustion stability.
  • Figure 4 shows a variation of ring 55 indicated 55a.
  • Ring 55a has two sets of calibrated circular holes 56a and 56b for the same function as holes 56 described above. Holes 56a, 56b alternate about axis 2, at least along part of the circumference of ring 55a, and are equally spaced 15° apart about axis 2. Holes 56b are twelve in number and of the same diameter; and holes 56a are twelve in number and of the same diameter larger than that of holes 56b.
  • Two diametrically opposite holes 57, forming part of holes 56a, may be used for the passage of a thermocouple; and two holes 58, also forming part of holes 56a, have a less than circular contour - more specifically, are U-shaped - for the passage of electrodes 41 and/or line 42.
  • air flow through ring 55a can be fine set and improved as a function of the specific operating range of the turbine, and the emission range to be complied with, by reducing the air flow section, e.g. by inserting plugs 59 ( Figure 4) or calibrated bushes (not shown) inside some of holes 56b equally spaced about axis 2, or inside all of holes 56b.
  • the gas from nozzles 38 may be used for ignition and when starting or bringing the turbine up to speed. Once an appropriate turbine speed or load is reached, premix burner 5 is also activated, and a changeover is made to full-premix mode, i.e. fuel gas is fed through nozzles 51, and gas supply from nozzles 38 is cut off, so as to produce a premix pilot flame.
  • Device 16 is compact, and permits ignition of burner 4 directly by the gas from nozzles 51, with no need for a dedicated gas stream from nozzles 38, on account of electrode 41 producing a spark at nozzles 51.
  • Burner 4 can therefore be ignited, and the turbine subsequently started or brought up to speed, directly by the premix gas feed line - i.e. the line (indicated 52 in Figure 1) comprising passages 46, header 48, holes 50, and cavities 29, and terminating with nozzles 51 - with no need for a diffusion flame, thus affording advantages in terms of reducing vibration.
  • gas flow from nozzles 51 is reduced to simply produce the pilot flame to keep the premix flame of burner 5 stable.
  • the feed line terminating with channel 36 and with nozzles 38 need not be used, thus eliminating the need for gas control and feed devices, such as regulating valves, sensors, piping, etc..., and so reducing cost and making additional space available for other components; alternatively, nozzles 38 may be closed, and channel 36 also used to feed gas (in known manner not shown) to nozzles 51 in parallel with passages 46, to increase the maximum gas flow from nozzles 51, thus enhancing the operating range and versatility of assembly 1.
  • assembly 1 has a single, completely premix type, pilot flame, thus reducing nitric oxide emissions, while still ensuring flame stability throughout the operating range.
  • nitric oxide emissions may be reduced to 30 mg/Nm3 (in low-load operating conditions) without compromising stability of the combustion process.
  • nitric oxide emissions of below 9 ppm with 15% oxygen in the fumes are obtainable.
  • Device 16 with ring 55 or 55a may be used to update a standard-production burner, or to adapt an already operating standard burner, to obtain a premix as opposed to diffusion pilot flame.
  • a known burner assembly (such as the one shown in Figure 6) can be converted to assembly 1 by substituting device 16 for the existing swirler and assembling ring 55, 55a inside channel 40.
  • the premix pilot flame configuration involves no alterations to the standard burner, and tests show the reduction in air flow produced by ring 55 in no way affects stability of the diffusion flame.
  • Device 16 requires no shielding or particular or additional heat protection along the gas feed line to nozzles 51, on account of the combustion air flow into device 16 flowing directly over the outside of wall portion 48a of header 48.
  • Calibrating air flow by means of holes arranged about axis 2, and in particular by means of the specific hole solutions shown and described in connection with rings 55, 55a, provides for achieving optimum fluid-dynamic performance as regards effective premixing of the premix pilot flame combustion air.
  • FIG. 5 shows a different swirl or turbulence generating device (“swirler”) 16b, which is obtained by simply modifying, as opposed to replacing, a “swirler” 16a of a known assembly 1a ( Figure 6) to obtain a premix flame.
  • swirl or turbulence generating device (swirler) 16b, which is obtained by simply modifying, as opposed to replacing, a “swirler” 16a of a known assembly 1a ( Figure 6) to obtain a premix flame.
  • the geometry and structure of the known swirler 16a differ from devices 16, 16b by being configured to generate:
  • device 16b produces the premix pilot flame in burner 4 by means of gas from holes 51a formed through cone 17a in lieu of holes 38a.
  • the device 16b embodiment therefore has the advantage of dispensing with perforated vanes 21 to inject the fuel gas, and employing the same standard vanes 21a and cones 17a, 18a of swirler 16a, thus minimizing the alterations required to known assembly 1a to add a premix pilot flame to an existing diffusion pilot flame.
  • the fuel gas generating the premix flame is supplied by line 36a, while line 52a remains unchanged and is again used to produce a diffusion pilot flame.
  • the Figure 5 solution calls for altering the geometry of the gas outlet of line 36a.
  • the number of holes 51a for each gap 22a and the diameter of the holes may differ from those indicated above, depending on the composition of the fuel gas. More specifically, the slope of axes 62 with respect to axis 2, the diameter and, hence, penetration of the gas jet, and the location of holes 51a are the parameters which define the degree of premixing with no risk of flashback, and may differ from those indicated above by way of example.
  • the gas from holes 51a is used for ignition, by virtue of electrode 41 generating a spark at one of the four gaps 22a in which holes 51a are formed.
  • the line defined by passages 15 is also used in parallel to feed fuel gas to burner 5 until the turbine reaches a speed corresponding to a no-load operating condition.
  • line 52a is also activated, so that gas is supplied simultaneously along three lines, to commence powering the electric machine. Once line 52a is activated, gas flow from holes 51a is cut off, and the premix flame of burner 5 is stabilized solely by the diffusion pilot flame.
  • pilot combustion is switched from the diffusion flame to the premix flame, i.e. fuel gas supply is switched from line 52a to line 36a.
  • the Figure 5 solution also provides for more flexible operation as compared with the Figure 1 solution.
  • the Figure 1 solution in fact, does not permit use of a diffusion pilot line, whereas the Figure 5 solution allows a choice between using as a pilot :
EP06111895.6A 2005-03-30 2006-03-29 Gasbrenneranordnung für eine Gasturbine Not-in-force EP1710502B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ITTO20050208 ITTO20050208A1 (it) 2005-03-30 2005-03-30 Gruppo bruciatore a gas per una turbina a gas

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EP1710502A2 true EP1710502A2 (de) 2006-10-11
EP1710502A3 EP1710502A3 (de) 2007-03-14
EP1710502B1 EP1710502B1 (de) 2016-05-11

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2169312A1 (de) * 2008-09-25 2010-03-31 Siemens Aktiengesellschaft Abgestufter Wirbler zur dynamischen Steuerung
ITMI20090556A1 (it) * 2009-04-07 2010-10-08 Ansaldo Energia Spa Metodo per operare un impianto a turbina a gas
EP2244015A1 (de) * 2009-04-23 2010-10-27 Siemens Aktiengesellschaft Vormischbrenner
ITMI20110808A1 (it) * 2011-05-10 2012-11-11 Ansaldo Energia Spa Gruppo bruciatore per una turbina a gas e metodo per alimentare combustibile a una camera di combustione di una turbina a gas
ITMI20111943A1 (it) * 2011-10-26 2013-04-27 Ansaldo Energia Spa Metodo per modificare un gruppo bruciatore di una turbina a gas
CN103154496A (zh) * 2010-10-21 2013-06-12 伍德沃德公司 半管形叶片式空气旋流器
WO2015090993A1 (en) * 2013-12-17 2015-06-25 Siemens Aktiengesellschaft Method of calibrating the air flow of a swirler of a gas turbine burner
CN106247408A (zh) * 2016-07-27 2016-12-21 中国科学院工程热物理研究所 一种拓宽回火裕度的喷嘴、喷嘴阵列和燃烧器

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2444640C2 (ru) * 2007-08-01 2012-03-10 Ансальдо Энергия С.П.А. Устройство и способ регулирования температуры выхлопа газовой турбины

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2280022A (en) * 1993-06-28 1995-01-18 Toshiba Kk Gas turbine combustor
WO1999004196A1 (de) * 1997-07-17 1999-01-28 Siemens Aktiengesellschaft Brenneranordnung für eine feuerungsanlage, insbesondere eine gasturbinenbrennkammer
WO2000012933A1 (de) * 1998-08-26 2000-03-09 Siemens Aktiengesellschaft Hybridbrenner und verfahren zum betrieb eines hybridbrenners
EP1193449A2 (de) * 2000-09-29 2002-04-03 General Electric Company Ringverwirbelungsanordnung
DE10104695A1 (de) * 2001-02-02 2002-08-08 Alstom Switzerland Ltd Vormischbrenner sowie Verfahren zum Betrieb eines derartigen Vormischbrenners
EP1400754A1 (de) * 2002-09-23 2004-03-24 Siemens Westinghouse Power Corporation Vormischender Pilotbrenner für eine Gasturbine
US20040144094A1 (en) * 1999-12-15 2004-07-29 Koji Moriya Fluid distributor, burner apparatus, gas turbine engine and co-generation system
EP1645805A1 (de) * 2004-10-11 2006-04-12 Siemens Aktiengesellschaft Brenner für fluidische Brennstoffe und Verfahren zum Betreiben eines derartigen Brenners

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1614967B1 (de) * 2004-07-09 2016-03-16 Siemens Aktiengesellschaft Verfahren und Vormischverbrennungssystem

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2280022A (en) * 1993-06-28 1995-01-18 Toshiba Kk Gas turbine combustor
WO1999004196A1 (de) * 1997-07-17 1999-01-28 Siemens Aktiengesellschaft Brenneranordnung für eine feuerungsanlage, insbesondere eine gasturbinenbrennkammer
WO2000012933A1 (de) * 1998-08-26 2000-03-09 Siemens Aktiengesellschaft Hybridbrenner und verfahren zum betrieb eines hybridbrenners
US20040144094A1 (en) * 1999-12-15 2004-07-29 Koji Moriya Fluid distributor, burner apparatus, gas turbine engine and co-generation system
EP1193449A2 (de) * 2000-09-29 2002-04-03 General Electric Company Ringverwirbelungsanordnung
DE10104695A1 (de) * 2001-02-02 2002-08-08 Alstom Switzerland Ltd Vormischbrenner sowie Verfahren zum Betrieb eines derartigen Vormischbrenners
EP1400754A1 (de) * 2002-09-23 2004-03-24 Siemens Westinghouse Power Corporation Vormischender Pilotbrenner für eine Gasturbine
EP1645805A1 (de) * 2004-10-11 2006-04-12 Siemens Aktiengesellschaft Brenner für fluidische Brennstoffe und Verfahren zum Betreiben eines derartigen Brenners

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
MAGHON H ET AL: "PROGRESS IN NOX AND CO EMISSION REDUCTION OF GAS TURBINES" AMERICAN SOCIETY OF MECHANICAL ENGINEERS SYMPOSIA SERIES, NEW YORK,NY, US, 21 October 1990 (1990-10-21), pages 1-7, XP000648263 *

Cited By (17)

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US8678301B2 (en) 2008-09-25 2014-03-25 Siemens Aktiengesellschaft Stepped swirler for dynamic control
WO2010034558A1 (en) * 2008-09-25 2010-04-01 Siemens Aktiengesellschaft Stepped swirler for dynamic control
EP2169312A1 (de) * 2008-09-25 2010-03-31 Siemens Aktiengesellschaft Abgestufter Wirbler zur dynamischen Steuerung
ITMI20090556A1 (it) * 2009-04-07 2010-10-08 Ansaldo Energia Spa Metodo per operare un impianto a turbina a gas
RU2551462C2 (ru) * 2009-04-23 2015-05-27 Сименс Акциенгезелльшафт Горелка предварительного смешения
CN102414514A (zh) * 2009-04-23 2012-04-11 西门子公司 预混合燃烧器
WO2010121845A1 (de) * 2009-04-23 2010-10-28 Siemens Aktiengesellschaft Vormischbrenner
CN102414514B (zh) * 2009-04-23 2014-08-20 西门子公司 预混合燃烧器
EP2244015A1 (de) * 2009-04-23 2010-10-27 Siemens Aktiengesellschaft Vormischbrenner
CN103154496A (zh) * 2010-10-21 2013-06-12 伍德沃德公司 半管形叶片式空气旋流器
CN103154496B (zh) * 2010-10-21 2015-07-22 伍德沃德公司 半管形叶片式空气旋流器
ITMI20110808A1 (it) * 2011-05-10 2012-11-11 Ansaldo Energia Spa Gruppo bruciatore per una turbina a gas e metodo per alimentare combustibile a una camera di combustione di una turbina a gas
ITMI20111943A1 (it) * 2011-10-26 2013-04-27 Ansaldo Energia Spa Metodo per modificare un gruppo bruciatore di una turbina a gas
WO2013061303A1 (en) * 2011-10-26 2013-05-02 Ansaldo Energia S.P.A. Method for modifying a gas turbine burner assembly
WO2015090993A1 (en) * 2013-12-17 2015-06-25 Siemens Aktiengesellschaft Method of calibrating the air flow of a swirler of a gas turbine burner
CN106247408A (zh) * 2016-07-27 2016-12-21 中国科学院工程热物理研究所 一种拓宽回火裕度的喷嘴、喷嘴阵列和燃烧器
CN106247408B (zh) * 2016-07-27 2019-01-18 中国科学院工程热物理研究所 一种拓宽回火裕度的喷嘴、喷嘴阵列和燃烧器

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Publication number Publication date
ITTO20050208A1 (it) 2006-09-30
EP1710502B1 (de) 2016-05-11
EP1710502A3 (de) 2007-03-14

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