EP1992878A1 - Distributeur de combustible - Google Patents

Distributeur de combustible Download PDF

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Publication number
EP1992878A1
EP1992878A1 EP07009960A EP07009960A EP1992878A1 EP 1992878 A1 EP1992878 A1 EP 1992878A1 EP 07009960 A EP07009960 A EP 07009960A EP 07009960 A EP07009960 A EP 07009960A EP 1992878 A1 EP1992878 A1 EP 1992878A1
Authority
EP
European Patent Office
Prior art keywords
swirler
fuel
opening
openings
flow
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.)
Withdrawn
Application number
EP07009960A
Other languages
German (de)
English (en)
Inventor
Paul Headland
Richard Noden
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.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP07009960A priority Critical patent/EP1992878A1/fr
Priority to PCT/EP2008/055762 priority patent/WO2008141955A1/fr
Priority to CN2008800165789A priority patent/CN101688669B/zh
Priority to RU2009147021/06A priority patent/RU2470228C2/ru
Priority to AT08750236T priority patent/ATE549582T1/de
Priority to EP08750236A priority patent/EP2147256B1/fr
Publication of EP1992878A1 publication Critical patent/EP1992878A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/02—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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • 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
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air

Definitions

  • the invention relates to a fuel distributor, in particular for a burner and a swirler.
  • the main purpose of the burner is to mix fuel and air together to obtain stable and efficient combustion with good flame stability and the smallest possible amount of NOx emissions. Therefore, the burner design must ensure that the proper amounts of fuel and air are introduced in the right locations within the burner and that these amounts of fuel and air are thoroughly mixed, so that complete combustion takes place with a minimum amount of excess air in order to achieve optimum overall efficiency.
  • the two burner principles which could be combined to use their respective advantages, are the premix combustion burner and the diffusion flame burner.
  • the air required for combustion, is mixed with the burner fuel before delivery to the combustion zone.
  • the fuel is not mixed with the air ahead of the combustion zone, but delivered as pure fuel in the immediate vicinity of the combustion zone.
  • Diffusion flame burners provide good flame stability. The NOx production is relatively high.
  • Low emission gas turbine engines often use a combustor with two operating modes including a pilot nozzle that forms a diffusion flame and a plurality of main nozzles for discharging a fuel/air mixture to form premixed flames as the main combustion around the diffusion flame.
  • the US 5,901,555 describes a conventional gas turbine with the main burners divided into a plurality of groups in accordance with the load. The flow rate of the pilot fuel is increased when the gas turbine load is low, to achieve stable combustion. When the gas turbine load is high, the ratio of the pilot fuel is decreased, to decrease the amount of NOx.
  • Separately controllable fuel lines, valves, pipe work and a control logic are required to achieve the appropriate fuel flows to the pilot and main nozzles, increasing the cost of the engine.
  • An object of the invention is to provide an improved fuel distributor.
  • An inventive fuel distributor uses the pressure gradient across the combustion system to control the proportion of fuel provided to different areas of the combustion system. These areas could provide pilot fuel at low loads, or better mixing of the fuel and air at high loads.
  • the system comprises a cavity with an inlet opening and at least two fuel injection openings.
  • the fuel distributor relies on having a larger injection opening arranged in the cavity of the fuel distributor in an upstream section, relative to the flow of compressor air, and a smaller injection opening arranged in the cavity in a downstream section, relative to the flow of compressor air, and serving as feed near combustor pressure.
  • a restrictor is arranged at the inlet opening to balance between the fuel flows through the at least one smaller outlet opening and the at least one larger third opening, respectively.
  • the restrictor is adjustable to adapt the pressure for different fuel types.
  • the third opening with a larger cross-sectional area and exposed to higher external air pressure as main fuel injection opening.
  • the principle of the fuel distributor is applied to a diffusion flame burner, where the fuel distributor has a tubular form with the outlet opening at the end of the tube facing the combustion chamber and with third openings arranged upstream the tube, relative to the flow of the fuel. At low fuel flows, the majority of the fuel will enter the combustion chamber through the outlet opening. Compressor air can enter the fuel distributor through the third openings and give some premixing of the fuel and the air. As the fuel flow increases, the pressure in the cavity increases and fuel will spill out through the third openings and will mix with compressor air and enter the combustion chamber.
  • the principle of the fuel distributor is applied to a swirler.
  • the cavity of the fuel distributor is arranged in the base plate of the swirler.
  • the fuel openings and the third openings are arranged in the mixing ducts, that is, in the passages of the swirler.
  • the openings may be arranged in the base plate of the swirler or in the swirler vanes. If arranged in the swirler vanes, the arrangement could be at different heights to improve the fuel distribution over the swirler vane height. Smaller fuel outlet openings would be closer to the swirler exit hole with lower pressure. Larger third openings would rather be in an upstream part of the swirler passages relative to the flow of compressor air, with higher pressure.
  • the fuel outlet openings would serve as pilot and the third openings as main fuel injection openings.
  • the pressure drop of the air between an outlet opening and a third opening in a mixing duct or a swirler passage is controlled by making the mixing duct or swirler passage convergent or divergent.
  • the inventive fuel distributor provides an increasing level of premix as the fuel flow increases.
  • the inventive fuel distributor even provides some premixing of fuel and air at low flows, thus further reducing NOx emissions.
  • the fuel/air mixing within a premix duct like e.g. a swirler passage can be varied as the fuel flow changes without the use of control valves, thus reducing costs and increasing reliability.
  • FIG. 1 shows the scheme of the inventive fuel distributor 1 applied in a diffusion flame burner 2.
  • the fuel distributor 1 comprises a distribution element 18 defining a cavity 3 with an inlet opening 4, an outlet opening 5, opposing the inlet opening 4, and two third openings 6.
  • the third openings 6 are larger than the outlet opening 5.
  • a restrictor 7 is arranged upstream the inlet opening 4 relative to the fuel flow 8, and sized to give the correct pressure to balance the fuel flows 8 between the outlet opening 5 and the third openings 6.
  • Pressure P1 at the third openings 6 is greater than pressure P2 at the outlet opening 5.
  • the majority of the fuel 8 will enter the combustion chamber 9 through the outlet opening 5.
  • air 10 may enter the cavity 3 through third openings 6 and give some premixing of the fuel 8 and air 10.
  • the pressure in the cavity 3 increases.
  • P1 fuel 8 will spill out of the third openings 6, as shown in Figure 2 , and mix with air 10.
  • the fuel/air premix will then enter the combustion chamber 9.
  • the swirler 11 for a gas turbine engine is shown.
  • the swirler 11 comprises swirler vanes 12 arranged on a swirler vane support 13.
  • the swirler vanes 12 can be fixed to a burner head (not shown) with their sides showing away from the swirler vane support 13.
  • swirler passages 14 are formed between a swirler passage inlet opening 15 and a swirler passage outlet opening 16.
  • the swirler passages 14 are delimited by opposing side faces 16 of swirler vanes 12, by the surface of the swirler vane support 13 which shows to the burner head (not shown) and by a surface of the burner head to which the swirler vanes 12 are fixed.
  • Outlet openings 5 and third openings 6 are arranged in the swirler passages 14 in the swirler vane support 13.
  • FIG. 4 a cross-sectional view of an inventive fuel distributor 1 arranged in a swirler vane support 13 is shown.
  • the outlet opening 5 and the third opening 6 open out into a swirler passage 14.
  • Compressor air 10 is entering the swirler passage 14 from the left by the swirler passage inlet opening 15, where the pressure P1 exceeds the pressure P2 at the swirler passage outlet opening 16.
  • Figure 4 shows the fuel distributor at low loads.
  • Fuel 8 enters the cavity 3 of the fuel distributor 1 by the inlet opening 4 through the restrictor 7.
  • a predominant proportion of the fuel 8 enters the swirler passage 14 through the outlet opening 5. Only a small amount of fuel 8 enters the swirler passage 14 through the third opening 6. This is beneficial for providing pilot fuel to the outlet opening 5.
  • At very low load a part of the compressor air 10 entering the swirler passage 14 flows into the cavity 3 through the third opening 6, leading to some premixing in the cavity 3.
  • Figures 6 and 7 show an alternative arrangement where the distribution of the fuel flow 8 across the height of the swirler passage 14 could be varied.
  • the cavity 3 of the fuel distributor 1 is again arranged in the swirler vane support 13.
  • the outlet opening 5 and the third opening 6 are arranged at different heights of the swirler vane 12 in the swirler passage 14.
  • the outlet opening 5 has a smaller cross-sectional area and is arranged close to the swirler passage outlet opening 16, where the pressure is low
  • the third opening 6 has a larger cross-sectional area and is arranged close to the swirler passage inlet opening 15, where the pressure is higher than at the swirler passage outlet opening 16.
  • Figure 9 shows a further embodiment of the inventive fuel distributor 1.
  • the general layout is similar to the embodiment described in Figure 6 .
  • the pressure drop of the air 10 in the swirler passage 14 between the outlet opening 5 and the third opening 6 is varied by making the swirler passage 14 convergent (as shown in Figure 9 ) or divergent (not shown).

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP07009960A 2007-05-18 2007-05-18 Distributeur de combustible Withdrawn EP1992878A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP07009960A EP1992878A1 (fr) 2007-05-18 2007-05-18 Distributeur de combustible
PCT/EP2008/055762 WO2008141955A1 (fr) 2007-05-18 2008-05-09 Distributeur de combustible
CN2008800165789A CN101688669B (zh) 2007-05-18 2008-05-09 燃料分配器
RU2009147021/06A RU2470228C2 (ru) 2007-05-18 2008-05-09 Распределитель топлива
AT08750236T ATE549582T1 (de) 2007-05-18 2008-05-09 Brennstoffverteiler
EP08750236A EP2147256B1 (fr) 2007-05-18 2008-05-09 Distributeur de combustible

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07009960A EP1992878A1 (fr) 2007-05-18 2007-05-18 Distributeur de combustible

Publications (1)

Publication Number Publication Date
EP1992878A1 true EP1992878A1 (fr) 2008-11-19

Family

ID=38573478

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07009960A Withdrawn EP1992878A1 (fr) 2007-05-18 2007-05-18 Distributeur de combustible
EP08750236A Not-in-force EP2147256B1 (fr) 2007-05-18 2008-05-09 Distributeur de combustible

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08750236A Not-in-force EP2147256B1 (fr) 2007-05-18 2008-05-09 Distributeur de combustible

Country Status (5)

Country Link
EP (2) EP1992878A1 (fr)
CN (1) CN101688669B (fr)
AT (1) ATE549582T1 (fr)
RU (1) RU2470228C2 (fr)
WO (1) WO2008141955A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2239501A1 (fr) * 2009-04-06 2010-10-13 Siemens Aktiengesellschaft Tourbillonnement, chambre à combustion, et turbine à gaz avec tourbillon amélioré
EP2942563A1 (fr) * 2014-05-09 2015-11-11 Siemens Aktiengesellschaft Élément de tourbillonnement d'un brûleur de moteur de turbine à gaz, brûleur de moteur de turbine à gaz et moteur de turbine à gaz

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2246617B1 (fr) 2009-04-29 2017-04-19 Siemens Aktiengesellschaft Brûleur pour moteur de turbine à gaz
DE102009045950A1 (de) 2009-10-23 2011-04-28 Man Diesel & Turbo Se Drallerzeuger

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0870989A2 (fr) * 1997-04-10 1998-10-14 European Gas Turbines Limited Disposition d'injection de carburant pour une chambre de combustion de turbine à gaz
EP0936406A2 (fr) * 1998-02-10 1999-08-18 General Electric Company Brûleur à prémélange combustible/air uniforme pour une combustion à faibles émissions
EP1394471A1 (fr) * 2002-09-02 2004-03-03 Siemens Aktiengesellschaft Brûleur
EP1507119A1 (fr) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Brûleur et méthode de fonctionnement d'une turbine à gaz

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2122684C1 (ru) * 1994-09-29 1998-11-27 Акционерное общество открытого типа "Экотеплогаз" Способ сжигания органического топлива в камере сгорания газотурбинных установок и других топливных устройствах
FR2753779B1 (fr) * 1996-09-26 1998-10-16 Systeme d'injection aerodynamique d'un melange air carburant
RU2260747C2 (ru) * 2003-11-18 2005-09-20 Открытое акционерное общество "Авиадвигатель" Камера сгорания газотурбинной установки

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0870989A2 (fr) * 1997-04-10 1998-10-14 European Gas Turbines Limited Disposition d'injection de carburant pour une chambre de combustion de turbine à gaz
EP0936406A2 (fr) * 1998-02-10 1999-08-18 General Electric Company Brûleur à prémélange combustible/air uniforme pour une combustion à faibles émissions
EP1394471A1 (fr) * 2002-09-02 2004-03-03 Siemens Aktiengesellschaft Brûleur
EP1507119A1 (fr) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Brûleur et méthode de fonctionnement d'une turbine à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2239501A1 (fr) * 2009-04-06 2010-10-13 Siemens Aktiengesellschaft Tourbillonnement, chambre à combustion, et turbine à gaz avec tourbillon amélioré
WO2010115648A1 (fr) * 2009-04-06 2010-10-14 Siemens Aktiengesellschaft Générateur de turbulence, chambre de combustion et turbine à gaz à tourbillonnement amélioré
US9222666B2 (en) 2009-04-06 2015-12-29 Siemens Aktiengesellschaft Swirler, combustion chamber, and gas turbine with improved swirl
EP2942563A1 (fr) * 2014-05-09 2015-11-11 Siemens Aktiengesellschaft Élément de tourbillonnement d'un brûleur de moteur de turbine à gaz, brûleur de moteur de turbine à gaz et moteur de turbine à gaz
WO2015169930A1 (fr) * 2014-05-09 2015-11-12 Siemens Aktiengesellschaft Coupelle rotative pour brûleur de turbine à gaz, brûleur de turbine à gaz et turbine à gaz

Also Published As

Publication number Publication date
WO2008141955A1 (fr) 2008-11-27
EP2147256A1 (fr) 2010-01-27
CN101688669A (zh) 2010-03-31
RU2470228C2 (ru) 2012-12-20
RU2009147021A (ru) 2011-06-27
ATE549582T1 (de) 2012-03-15
CN101688669B (zh) 2011-06-08
EP2147256B1 (fr) 2012-03-14

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