EP0933594A1 - Gasturbinenbrennkammer für flüssigen Kraftstoff - Google Patents

Gasturbinenbrennkammer für flüssigen Kraftstoff Download PDF

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Publication number
EP0933594A1
EP0933594A1 EP99400141A EP99400141A EP0933594A1 EP 0933594 A1 EP0933594 A1 EP 0933594A1 EP 99400141 A EP99400141 A EP 99400141A EP 99400141 A EP99400141 A EP 99400141A EP 0933594 A1 EP0933594 A1 EP 0933594A1
Authority
EP
European Patent Office
Prior art keywords
air
combustion chamber
fuel
enclosure
chamber according
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
EP99400141A
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English (en)
French (fr)
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EP0933594B1 (de
Inventor
Jean-Hervé Le Gal
Patrick Flament
Gérard Martin
Guy Grienche
Gérard Schott
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.)
IFP Energies Nouvelles IFPEN
Original Assignee
IFP Energies Nouvelles IFPEN
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Publication of EP0933594A1 publication Critical patent/EP0933594A1/de
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Publication of EP0933594B1 publication Critical patent/EP0933594B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
    • 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
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/58—Cyclone or vortex type combustion chambers

Definitions

  • the present invention relates to the field of combustion of gas turbines powered by liquid fuel.
  • Such gas turbines can be illustrated by the system shown in Figure 3.
  • This assembly includes a compressor (20) the outlet of which is connected to the inlet of the combustion chamber (1) where a liquid fuel (fuel oil or kerosene) is injected.
  • a liquid fuel fuel oil or kerosene
  • the gases burned in this chamber are then expanded in a turbine (30) which thereby provides the desired power to the main shaft which itself drives the compressor (20).
  • thermodynamic cycle of the machine In gas turbine combustion chambers, combustion at flame level is usually performed around stoichiometry as this ensures good flame stability. Wealth however global imposed by the conditions of the thermodynamic cycle of the machine is very low, on the order of 0.15 to 0.3, depending on the conditions of operation. Operating locally in or around rich conditions stoichiometry, with air preheated by the compressor, leads to locally very high temperatures in the room (around 2000 to 2500 K). The measurements showed that under these conditions, the majority of the nitrogen oxide formed was "thermal NO".
  • the so-called dry processes generally aim to achieve combustion a lean premix of air and fuel produced beforehand.
  • the Patent application EP-A2-0 769 657 illustrates a system of this type.
  • the stability of combustion and ignition of the main premix are ensured by a pilot flame of small power whose role is also to ensure the machine running at idle speed.
  • the wealth in the chamber being fixed by the respective proportions of air and fuel premixed, it is possible to limit the flame temperatures and therefore thermal nitrogen oxide.
  • premixed combustion technologies do not not give satisfactory results with liquid fuel.
  • this technique requires the implementation of a pilot burner allowing to ensure the stability of the flame, especially in poor conditions.
  • This burner ensuring the operation of the machine during the phases of idling, it passes a fuel flow of up to almost a third of the total flow. For some applications, it works under conditions operating close to stoichiometry so under conditions unfavorable procedures from the point of view of oxide production nitrogen.
  • the present invention makes it possible in particular to resolve all of the problems discussed above. It is an alternative solution to combustion chambers operating in premix or in processes damp as mentioned above.
  • the present invention aims to achieve a diffusion flame by combining certain conditions of injection of air and liquid fuel.
  • the present invention relates to a combustion chamber of gas turbine operating on liquid fuel, comprising an enclosure tubular having at least one air inlet, a means for injecting liquid fuel located on or near the longitudinal axis of the enclosure tubular, one outlet to the turbine, at least two types of air inlets under pressure located close to each other: the first introducing air helically around the longitudinal axis of the combustion chamber, the second inlet introduces air tangentially to the enclosure to create around the fuel jets counter-rotating flows intended for improve the mixture between said fuel and air.
  • the first air inlet allows the introduction of 30% to 70% of the total amount of pressurized air entering the combustion chamber, the rest being injected through the second inlets pressurized air.
  • said injection means has between 5 and 12 orifices intended for the injection of liquid fuel, preferably between 6 and 10 ports.
  • the injection means comprises a central disc located on the longitudinal axis of the tubular enclosure, around which is arranged a ring pierced with said orifices, the surface of the ring being a truncated cone.
  • the tangential entry includes a set of inserts distributed around the periphery of the enclosure, which direct the air tangentially to the enclosure wall with a direction of rotation opposite to that of flow main.
  • the air inlets can be dimensioned so that the air speed inside the combustion chamber is between 20 and 120 m / s.
  • the angle at the top of the injection cone is preferably between 35 ° and 45 °.
  • the combustion chamber according to the invention illustrated schematically in Figure 1, includes a tubular outer casing 1 and an inner enclosure 2 coaxial with the casing 1.
  • envelopes 1 and 2 are closed at one end where they delimit a functional space 3.
  • envelopes 1 and 2 define between they an annular space 4 for the circulation of pressurized air before to enter the combustion chamber proper.
  • the actual combustion chamber, 5, is defined by the interior volume of the enclosure 2.
  • a means for injecting fuel 6 which preferably comprises a central disc 61 located on or in the immediate vicinity of the longitudinal axis XX 'of the enclosure 2.
  • the injection means 6 comprises a set of orifices 62 arranged on a truncated cone ring.
  • from 5 to 12 jets can be created; preferably between 6 and 10. These jets are separated from each other from others and located along the generatrices of a corner cone at the top a between 30 ° and 60 °, preferably between 35 ° and 45 °.
  • the injection means 6 can operate with assistance additional air; we then obtain medium diameter droplets less than 50 micrometers.
  • the number of jets is also important. If this one is too important, there is an effect of blocking the flow by the jets of combustible. This results in an air-depleted area behind the jets, which leads to rich combustion conditions, therefore at high temperature. Yes there are too few jets, the interactions between jets decrease and we found in the case of n independent axial flames.
  • the first type introduces air helically into enclosure 2, around the longitudinal axis of the enclosure.
  • This entry 7 is here a ring around the injection means 6.
  • Fins 71 can be arranged in the ring to print to this air a quantity of tangential movement.
  • the second type of air intake includes peripheral inlets 8 which allow the air to be injected tangentially to the wall of the enclosure 2. A this effect of the inserts 81 as shown in FIG. 2 can be planned.
  • the inserts 81 direct the air tangentially and in the opposite direction to the first type of flow. This increases the shear between the two flows and therefore accelerate the mixing between the air and the fuel droplets.
  • the air flow at inlet 7 is between 30 and 70% air used for combustion, preferably between 40 and 50%.
  • Well heard the air flow passing through the tangential inlets 8 is the 100% complement.
  • Dilution air is introduced if necessary downstream of the combustion zone 5, through orifices made in the enclosure 2.
  • the means injection 6 advantageously comprises a central disc 61.
  • the latter allows, in combination with the rotation of the flow, generate a small internal recirculation according to the arrows A in Figure 1, at level of the injector nose 6.
  • the zone 10 delimited by this recirculation is rather rich in fuel and it partly ensures the stability of the combustion.
  • the majority of the fuel is burned in poor conditions since the overall wealth in the combustion chamber 5 is between 0.4 and 0.8.
  • a separate flame burner operates around stoichiometry or with a slight excess of air.
  • thermodynamic cycle of this imposes operation under pressure which can vary from approximately 2 to approximately 30 bars.
  • the residence times in the combustion chamber 5 according to the invention are commonly less than 50 milliseconds, which leads to heating densities of between 50 and 200 MW / m 3 .
  • the heating densities in the field of boiler burners are rather less than 1 MW / m 3 , with residence times of the order of a second.
  • the figure 3 shows in longitudinal section a turbo-compressor assembly likely to implement the invention; this figure was commented on in description head.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP99400141A 1998-01-28 1999-01-21 Verfahren zum Betreiben einer Gasturbinenbrennkammer für flüssigen Kraftstoff Expired - Lifetime EP0933594B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9800932A FR2774152B1 (fr) 1998-01-28 1998-01-28 Chambre de combustion de turbine a gaz fonctionnant au carburant liquide
FR9800932 1998-01-28

Publications (2)

Publication Number Publication Date
EP0933594A1 true EP0933594A1 (de) 1999-08-04
EP0933594B1 EP0933594B1 (de) 2004-12-15

Family

ID=9522281

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99400141A Expired - Lifetime EP0933594B1 (de) 1998-01-28 1999-01-21 Verfahren zum Betreiben einer Gasturbinenbrennkammer für flüssigen Kraftstoff

Country Status (5)

Country Link
US (1) US6378310B1 (de)
EP (1) EP0933594B1 (de)
JP (1) JPH11270852A (de)
DE (1) DE69922559T2 (de)
FR (1) FR2774152B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10040791A1 (de) * 2000-08-21 2002-03-14 Siemens Ag Verfahren und Vorrichtung zur Bestimmung und Kompensation der Verkippung des Spektrums in einer Lichtleitfaser einer Datenübertragungsstrecke
EP2072899A1 (de) * 2007-12-19 2009-06-24 ALSTOM Technology Ltd Kraftstoffeinspritzsystem
NL2005381C2 (en) * 2010-09-21 2012-03-28 Micro Turbine Technology B V Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine.

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6543235B1 (en) * 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
CN100559080C (zh) * 2004-10-18 2009-11-11 阿尔斯通技术有限公司 燃气轮机用的燃烧器
US20060218932A1 (en) * 2004-11-10 2006-10-05 Pfefferle William C Fuel injector
DE102005036889A1 (de) * 2005-08-05 2007-02-15 Gerhard Wohlfarth Verfahren und Vorrichtung zur Einleitung, Förderung und Beschleunigung physikalischer Prozesse bzw. Reaktionen an flüssigen, gasförmigen Stoffen, Stoffgemischen, Lösungen und im besonderen ein Verfahren und Vorrichtung zur Steigerung des Wirkungsgrades bei Verbrennungsvorgängen in Ölfeuerungsanlagen
US8062027B2 (en) * 2005-08-11 2011-11-22 Elster Gmbh Industrial burner and method for operating an industrial burner
US7614211B2 (en) * 2005-12-15 2009-11-10 General Electric Company Swirling flows and swirler to enhance pulse detonation engine operation
FR2903173B1 (fr) * 2006-06-29 2008-08-29 Snecma Sa Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
US9062563B2 (en) 2008-04-09 2015-06-23 General Electric Company Surface treatments for preventing hydrocarbon thermal degradation deposits on articles
US8701383B2 (en) * 2009-01-07 2014-04-22 General Electric Company Late lean injection system configuration
US8112216B2 (en) * 2009-01-07 2012-02-07 General Electric Company Late lean injection with adjustable air splits
US8707707B2 (en) * 2009-01-07 2014-04-29 General Electric Company Late lean injection fuel staging configurations
US8701382B2 (en) * 2009-01-07 2014-04-22 General Electric Company Late lean injection with expanded fuel flexibility
US8683808B2 (en) * 2009-01-07 2014-04-01 General Electric Company Late lean injection control strategy
US8701418B2 (en) * 2009-01-07 2014-04-22 General Electric Company Late lean injection for fuel flexibility
US20120210717A1 (en) * 2011-02-21 2012-08-23 General Electric Company Apparatus for injecting fluid into a combustion chamber of a combustor
DE102011013950A1 (de) * 2011-03-14 2012-09-20 Air Liquide Deutschland Gmbh Brenner und Verfahren zum Betreiben eines Brenners
US8893500B2 (en) 2011-05-18 2014-11-25 Solar Turbines Inc. Lean direct fuel injector
US8919132B2 (en) 2011-05-18 2014-12-30 Solar Turbines Inc. Method of operating a gas turbine engine
US9182124B2 (en) 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same
US20160053681A1 (en) * 2014-08-20 2016-02-25 General Electric Company Liquid fuel combustor having an oxygen-depleted gas (odg) injection system for a gas turbomachine
CN110397935A (zh) * 2018-04-25 2019-11-01 中国科学院工程热物理研究所 旋风熔融炉及其使用方法

Citations (10)

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GB387049A (en) * 1930-10-23 1933-02-02 Hubert Jezler Improvements in or relating to the firing of boilers and the like
GB870988A (en) * 1956-09-01 1961-06-21 Gio Batta Sommariva Improvements in or relating to a liquid fuel atomiser
US4006589A (en) * 1975-04-14 1977-02-08 Phillips Petroleum Company Low emission combustor with fuel flow controlled primary air flow and circumferentially directed secondary air flows
US4702073A (en) * 1986-03-10 1987-10-27 Melconian Jerry O Variable residence time vortex combustor
US4842509A (en) * 1983-03-30 1989-06-27 Shell Oil Company Process for fuel combustion with low NOx soot and particulates emission
FR2656676A1 (fr) 1989-12-28 1991-07-05 Inst Francais Du Petrole Bruleur industriel a combustible liquide a faible emission d'oxyde d'azote, ledit bruleur generant plusieurs flammes elementaires et son utilisation.
US5562437A (en) 1993-06-22 1996-10-08 Enterprise Generale De Chauffage Industriel Pillard (Societe Anonyme) Liquid or gaseous fuel burner with very low emission of nitrogen oxides
EP0769657A2 (de) 1995-10-19 1997-04-23 General Electric Company Vormischbrenner für eine Gasturbinenbrennkammer mit niedriger Schadstoffemission
FR2741424A1 (fr) 1995-11-17 1997-05-23 Schlumberger Services Petrol Bruleur a faible pollution, pour essais de puits petroliers
US5680766A (en) * 1996-01-02 1997-10-28 General Electric Company Dual fuel mixer for gas turbine combustor

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US2638745A (en) * 1943-04-01 1953-05-19 Power Jets Res & Dev Ltd Gas turbine combustor having tangential air inlets for primary and secondary air
JPS4931059Y1 (de) * 1970-11-30 1974-08-22
US4271675A (en) * 1977-10-21 1981-06-09 Rolls-Royce Limited Combustion apparatus for gas turbine engines
US4226083A (en) * 1978-01-19 1980-10-07 United Technologies Corporation Method and apparatus for reducing nitrous oxide emissions from combustors
US4928481A (en) * 1988-07-13 1990-05-29 Prutech Ii Staged low NOx premix gas turbine combustor
US5628184A (en) * 1993-02-03 1997-05-13 Santos; Rolando R. Apparatus for reducing the production of NOx in a gas turbine
US5479781A (en) * 1993-09-02 1996-01-02 General Electric Company Low emission combustor having tangential lean direct injection
US5488829A (en) * 1994-05-25 1996-02-06 Westinghouse Electric Corporation Method and apparatus for reducing noise generated by combustion

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB387049A (en) * 1930-10-23 1933-02-02 Hubert Jezler Improvements in or relating to the firing of boilers and the like
GB870988A (en) * 1956-09-01 1961-06-21 Gio Batta Sommariva Improvements in or relating to a liquid fuel atomiser
US4006589A (en) * 1975-04-14 1977-02-08 Phillips Petroleum Company Low emission combustor with fuel flow controlled primary air flow and circumferentially directed secondary air flows
US4842509A (en) * 1983-03-30 1989-06-27 Shell Oil Company Process for fuel combustion with low NOx soot and particulates emission
US4702073A (en) * 1986-03-10 1987-10-27 Melconian Jerry O Variable residence time vortex combustor
FR2656676A1 (fr) 1989-12-28 1991-07-05 Inst Francais Du Petrole Bruleur industriel a combustible liquide a faible emission d'oxyde d'azote, ledit bruleur generant plusieurs flammes elementaires et son utilisation.
US5562437A (en) 1993-06-22 1996-10-08 Enterprise Generale De Chauffage Industriel Pillard (Societe Anonyme) Liquid or gaseous fuel burner with very low emission of nitrogen oxides
EP0769657A2 (de) 1995-10-19 1997-04-23 General Electric Company Vormischbrenner für eine Gasturbinenbrennkammer mit niedriger Schadstoffemission
FR2741424A1 (fr) 1995-11-17 1997-05-23 Schlumberger Services Petrol Bruleur a faible pollution, pour essais de puits petroliers
US5680766A (en) * 1996-01-02 1997-10-28 General Electric Company Dual fuel mixer for gas turbine combustor

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10040791A1 (de) * 2000-08-21 2002-03-14 Siemens Ag Verfahren und Vorrichtung zur Bestimmung und Kompensation der Verkippung des Spektrums in einer Lichtleitfaser einer Datenübertragungsstrecke
EP2072899A1 (de) * 2007-12-19 2009-06-24 ALSTOM Technology Ltd Kraftstoffeinspritzsystem
WO2009080600A1 (en) * 2007-12-19 2009-07-02 Alstom Technology Ltd Fuel injection method
US8621870B2 (en) 2007-12-19 2014-01-07 Alstom Technology Ltd. Fuel injection method
NL2005381C2 (en) * 2010-09-21 2012-03-28 Micro Turbine Technology B V Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine.
WO2012039611A1 (en) * 2010-09-21 2012-03-29 Micro Turbine Technology Bv Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine

Also Published As

Publication number Publication date
EP0933594B1 (de) 2004-12-15
US6378310B1 (en) 2002-04-30
JPH11270852A (ja) 1999-10-05
FR2774152A1 (fr) 1999-07-30
DE69922559D1 (de) 2005-01-20
DE69922559T2 (de) 2005-05-12
US20020050139A1 (en) 2002-05-02
FR2774152B1 (fr) 2000-03-24

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