EP1892472B1 - Système de combustion en particulier pour une turbine à gaz - Google Patents

Système de combustion en particulier pour une turbine à gaz Download PDF

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Publication number
EP1892472B1
EP1892472B1 EP06016932A EP06016932A EP1892472B1 EP 1892472 B1 EP1892472 B1 EP 1892472B1 EP 06016932 A EP06016932 A EP 06016932A EP 06016932 A EP06016932 A EP 06016932A EP 1892472 B1 EP1892472 B1 EP 1892472B1
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EP
European Patent Office
Prior art keywords
nozzle
tube
orifice
burner
combustion chamber
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.)
Not-in-force
Application number
EP06016932A
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German (de)
English (en)
Other versions
EP1892472A1 (fr
Inventor
Werner Dr. Krebs
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP06016932A priority Critical patent/EP1892472B1/fr
Priority to AT06016932T priority patent/ATE493615T1/de
Priority to DE502006008611T priority patent/DE502006008611D1/de
Priority to ES06016932T priority patent/ES2356924T3/es
Priority to EP07788256A priority patent/EP2052184A1/fr
Priority to PCT/EP2007/058144 priority patent/WO2008019969A1/fr
Publication of EP1892472A1 publication Critical patent/EP1892472A1/fr
Application granted granted Critical
Publication of EP1892472B1 publication Critical patent/EP1892472B1/fr
Not-in-force legal-status Critical Current
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Classifications

    • 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 
    • F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
    • F23C9/006—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber the recirculation taking place in the combustion chamber
    • 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
    • F23D11/40—Mixing tubes; Burner heads
    • F23D11/406—Flame stabilising means, e.g. flame holders
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F23D14/70—Baffles or like flow-disturbing 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
    • F23R3/28—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
    • 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
    • F23C2900/09002—Specific devices inducing or forcing flue gas recirculation
    • 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
    • F23D2900/11401—Flame intercepting baffles forming part of burner head
    • 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
    • F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation

Definitions

  • the present invention relates to a combustion system, in particular a combustion system for a gas turbine with a combustion chamber and at least one nozzle tube, which opens into the combustion chamber with a nozzle outlet opening.
  • Jet flames are discussed as an alternative to swirl flames in combustion systems for gas turbine plants.
  • a fuel fluid or a mixture of fuel fluid and air is introduced by means of a nozzle tube as a jet into the combustion chamber.
  • Jet flames enable emissions of nitrogen oxides (NO x) emissions, which are as low as in premixed flames swirl, while at the same time allow the distribution of heat release over a greater compared to the premixed swirl flame region in the combustor.
  • NO x nitrogen oxides
  • jet flames open up a potential for reducing thermoacoustically induced vibrations.
  • jet flames enable the burning of very different fuel fluids, which ensures a high flexibility of the combustion system. High flexibility is one of the main goals of modern combustion systems.
  • jet flames are mainly stabilized by the entrainment of hot reaction gases from an outer recirculation zone of the combustion chamber.
  • the entrainment of the hot reaction gases has been improved by increasing the jet velocity and adjusting the geometry of the combustion assembly.
  • the adjustment of the geometry is usually carried out by establishing a specific ratio between the diameter of the combustion chamber and the diameter of the nozzle opening into the combustion chamber of the nozzle tube.
  • a technical solution that leads to flame stabilization and noise reduction, is from the DE 93102547 U known.
  • the Flame stability may still be unsatisfactory, in particular with regard to different operating points of gas turbine plants or when using fuels with a high hydrogen content, which lead to a high combustion speed.
  • a burner according to the invention which in particular can be designed as a burner for a gas turbine, comprises at least one nozzle tube and a fuel fluid supply line communicating with the nozzle tube for supplying a fuel fluid into the nozzle tube and optionally additionally an air supply line communicating with the nozzle tube for supplying Combustion air in the nozzle tube.
  • the nozzle tube has a nozzle outlet opening and is designed to inject a jet of fuel fluid or of a mixture of air and fuel fluid into a combustion chamber.
  • the nozzle tube has in the region of the nozzle outlet opening to the center of the opening projecting elements.
  • the elements projecting towards the center of the opening thus lead to an increase in the turbulent fluctuations in the region of the boundary surface between the jet and the recirculated combustion exhaust gases in the well-worn jet, which in turn increases the entrainment of the combustion exhaust gases. As a consequence, the stability of the flame is increased.
  • the projecting elements are formed by a nozzle tube section having a corrugated inner circumferential surface extending up to the nozzle outlet opening. This leads to an enlargement of the surface of the jet emerging from the nozzle opening. Since the number of turbulent fluctuations depends on the size of the interface between the jet and the hot reaction gases, ie the combustion gases, in the recirculation zone, in this implementation, the enhancement of vortex formation is essentially due to the increased radiant surface area.
  • the corrugated inner peripheral surface at the nozzle exit port is configured to have a maximum deflection A about a mean opening radius R of the nozzle exit port, and the ratio of the deflection to the mean port radius through the relationship 0 . 03 ⁇ / R A ⁇ 0 . 2 given is.
  • the corrugated inner peripheral surface may in particular have the shape of a sine wave extending over the circumference of the nozzle outlet opening. But other in the broadest sense corrugated forms, such as sawtooth shapes, are possible.
  • the nozzle tube has a nozzle tube section remote from the nozzle opening and a transition section.
  • the transition section represents a transition from the nozzle tube section with a circular opening cross-section to the nozzle tube section with the corrugated inner circumferential surface.
  • the maximum amplitude of the corrugated inner peripheral surface is reached directly at the nozzle outlet opening.
  • the ratio of the length L T of the transition region to the maximum amplitude A is given by the formula 1 ⁇ / 2 ⁇ A L T ⁇ 5 given. In the given by the formula ratio of the length of the transition region to the maximum amplitude can be achieved particularly advantageous results for flame stability.
  • a combustion system with a combustion chamber and a burner according to the invention comprises at least one nozzle tube and a fuel fluid supply line communicating with the nozzle tube for supplying a fuel fluid into the nozzle tube and optionally additionally an air supply line communicating with the nozzle tube for supplying combustion air into the nozzle tube.
  • the nozzle tube has a nozzle outlet opening into the combustion chamber and is designed to inject a jet of fuel fluid or a mixture of air and fuel fluid into the combustion chamber.
  • the nozzle tube projects into the combustion chamber.
  • the nozzle tube may have an opening diameter D and project over a length L in the combustion chamber, wherein the ratio of the length L to the opening diameter D by the relationship 0 .
  • the nozzle tube projecting into the combustion chamber can be equipped, in particular in the area of the nozzle outlet opening, with elements projecting towards the center of the opening, as have been described with reference to the burner according to the invention.
  • the burner is a burner according to the invention.
  • FIG Fig. 1 An exemplary embodiment of a combustion system according to the invention is shown in a highly schematic representation in FIG Fig. 1 shown.
  • the figure shows a section through the longitudinal axis of the combustion system and shows a burner 1 and a combustion chamber. 3
  • the burner is designed to generate a jet flame 5. It comprises a nozzle tube 7, which in the present embodiment is in communication with a fuel supply line 9 and an air supply line 11.
  • the fuel fluid supplied via the fuel supply line 9, for example, gas (such as natural gas) or oil (such as fuel oil) is mixed in a mixer 13 and supplied to the nozzle tube 7.
  • gas such as natural gas
  • oil such as fuel oil
  • the premixed air / fuel mixture is injected into the combustion chamber 3 to form the jet flame 5.
  • the diameter of the nozzle outlet opening with the dimension of the combustion chamber opening W in the ratio 1 ⁇ W / D ⁇ 4.
  • a recirculation zone 6 in which hot combustion gases flow back in the radially outer region of the combustion chamber 3 in the direction of the burner 7 and in the upstream region of the combustion chamber 3 in its direction of movement in the direction of the radially inner area be distracted the combustion chamber.
  • shear forces occur, which entrain the recirculated exhaust gas 17 in the flow direction F of the air / fuel mixture. Due to this entrainment effect, the jet flame 5 is stabilized in the combustion chamber 3. For the entrainment effect, primarily turbulent fluctuations in the peripheral surface of the jet flame 5 are responsible.
  • the nozzle tube 7 of the burner 1 has a corrugated tube wall 19 in the region of the nozzle outlet opening 15.
  • the corrugation is realized in that the tube wall 19 has the shape of a standing sine wave oscillating about an average tube radius R with an amplitude A.
  • the corrugation can also be implemented in its inner wall by incorporating a sinusoidal contour in the circumferential direction of the nozzle tube. The curl does not necessarily have sinusoidal form. Other shapes, such as sawtooth shapes, are possible.
  • the amplitude A of the corrugation has its maximum value at the nozzle outlet opening 15. It decreases towards upstream pipe sections until finally reaching a pipe section 21 in which the pipe has a circular cross-section.
  • the transition region in which the amplitude decreases from its maximum value A to zero, has a length L T in the axial direction of the nozzle tube 7.
  • the ratio of the length L T of the transition region to the maximum amplitude A is defined by the relationship 1 ⁇ / 2 ⁇ A L T ⁇ 5 given.
  • the surface of the nozzle outlet opening 15 emerging jet of air / fuel mixture in comparison to a emerging from a nozzle outlet opening with a round cross-section and the radius R jet of air / fuel mixture increases.
  • the enlargement of the surface of the jet leads to more turbulent fluctuations and thus to an amplification of the described entrainment effect.
  • the entrainment effect can be enhanced if the ratio of the deflection A of the corrugation to the mean radius R of the nozzle outlet opening is enhanced by the relationship 0 . 03 ⁇ / R A ⁇ 0 . 2 given is.
  • Fig. 2 merely exemplary and schematically represents the shape of the corrugation.
  • the number of wave crests and troughs can also be smaller or larger than that in Fig. 2 is shown.
  • FIG. 3 A further embodiment of the combustion system according to the invention is in Fig. 3 shown.
  • the figure shows the combustion system in a section along its longitudinal axis and shows a burner 201 and a combustion chamber 203.
  • the burner comprises a nozzle tube 207, a fuel supply line 209 and an air supply line 211 and a mixer 213, which is connected upstream of the nozzle tube 207 and into which the fuel supply line 209 and the air supply line 211 open.
  • the nozzle tube 207 has neither a corrugation nor delta wings in the region of its nozzle outlet opening 215. It should be noted at this point, however, that the burner can be equipped in the second embodiment of the combustion system with a corrugation or with delta wings in the region of its nozzle outlet opening 215.
  • the nozzle exit opening 215 Due to the entry into the combustion chamber 203, the nozzle exit opening 215 can be brought closer to the recirculation zone in the combustion chamber, so that shortly after the exit of the jet 205 from the nozzle exit opening 215 the entrainment effect occurs. The entrainment effect can therefore stabilize the jet flame 205 largely over its entire length.
  • the entrainment effect for the hot gases in the outer recirculation zone is increased.
  • the increased turbulent fluctuations ensure uniform combustion with low acoustic amplitudes, thus suppressing the occurrence of combustion oscillations.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Control Of Turbines (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Spray-Type Burners (AREA)
  • Gas Burners (AREA)

Claims (6)

  1. Brûleur ( 1, 101 ), notamment pour une turbine à gaz, comprenant au moins un tube ( 7, 107 ) formant buse ainsi qu'un conduit ( 9 ) d'apport de fluide combustible communiquant avec le tube ( 7, 107 ) formant buse pour l'apport d'un fluide combustible au tube ( 7, 107 ) formant buse, le tube ( 7, 107 ) formant buse ayant une ouverture ( 15, 115 ) de sortie de buse et étant conformé pour l'injection d'un jet ( 5 ) de fluide combustible ou d'un mélange d'air et de fluide combustible dans une chambre de combustion ( 3 ), dans lequel le tube ( 7, 107 ) formant buse a dans la zone de l'ouverture ( 15, 115 ) de sortie de la buse des éléments ( 19, 119 ) en saillie vers le milieu de l'ouverture, les éléments en saillie étant formés par un tronçon du tube formant buse qui va jusqu'à l'ouverture ( 15 ) de sortie de la buse et qui a une surface périphérique intérieure ondulée, caractérisé en ce que la surface ( 19 ) périphérique intérieure ondulée a à l'ouverture ( 15 ) de sortie de la buse une excursion A maximum autour d'un rayon R du moyen d'ouverture de l'ouverture ( 15 ) de sortie de la buse et le rapport de l'excursion au rayon moyen d'ouverture est donné par la relation 0 , 03 < / R A < 0 , 2
    Figure imgb0013
  2. Brûleur ( 1 ) suivant la revendication 1, caractérisé en ce que la surface ( 19 ) périphérique intérieure ondulée a la forme d'une onde sinusoïdale.
  3. Brûleur ( 1 ) suivant la revendication 1, caractérisé en ce que la surface ( 19 ) périphérique intérieure ondulée a une forme en dents de scie.
  4. Brûleur ( 1 ) suivant l'une des revendications 1 à 3, caractérisé en ce que le tube ( 7 ) formant buse a un tronçon ( 21 ) éloigné de l'ouverture ( 15 ) formant buse ayant une section transversale d'ouverture circulaire et un tronçon de transition allant du tronçon ( 21 ) de tube formant buse ayant la section transversale d'ouverture circulaire à la section du tube formant buse ayant la surface ( 19 ) périphérique intérieure ondulée, l'amplitude A maximum de la surface ( 19 ) périphérique intérieure ondulée étant atteinte à l'ouverture ( 15 ) de sortie de la buse et le rapport de la longueur LT de la partie de transition à l'amplitude A maximum étant donné par la relation 1 < / 2 ⁢ A L T < 5
    Figure imgb0014
  5. Système de combustion, notamment pour une turbine à gaz, comprenant une chambre de combustion ( 203 ) et un brûleur suivant l'une des revendications précédentes, caractérisé en ce que le tube ( 207 ) formant buse fait saillie dans la chambre de combustion.
  6. Système de combustion suivant la revendication 5, caractérisé en ce que le tube ( 207 ) formant buse a un diamètre D d'ouverture et fait saillie dans la chambre de combustion ( 203 ) sur une longueur L, le rapport du diamètre D de l'ouverture à la longueur L étant donné par la relation 0 , 3 < / D L < 3
    Figure imgb0015
EP06016932A 2006-08-14 2006-08-14 Système de combustion en particulier pour une turbine à gaz Not-in-force EP1892472B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP06016932A EP1892472B1 (fr) 2006-08-14 2006-08-14 Système de combustion en particulier pour une turbine à gaz
AT06016932T ATE493615T1 (de) 2006-08-14 2006-08-14 Verbrennungssystem insbesondere für eine gasturbine
DE502006008611T DE502006008611D1 (de) 2006-08-14 2006-08-14 Verbrennungssystem insbesondere für eine Gasturbine
ES06016932T ES2356924T3 (es) 2006-08-14 2006-08-14 Sistemas de combustión, en especial para una turbina de gas.
EP07788256A EP2052184A1 (fr) 2006-08-14 2007-08-06 Système de combustion, en particulier pour une turbine à gaz
PCT/EP2007/058144 WO2008019969A1 (fr) 2006-08-14 2007-08-06 Système de combustion, en particulier pour une turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06016932A EP1892472B1 (fr) 2006-08-14 2006-08-14 Système de combustion en particulier pour une turbine à gaz

Publications (2)

Publication Number Publication Date
EP1892472A1 EP1892472A1 (fr) 2008-02-27
EP1892472B1 true EP1892472B1 (fr) 2010-12-29

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP06016932A Not-in-force EP1892472B1 (fr) 2006-08-14 2006-08-14 Système de combustion en particulier pour une turbine à gaz
EP07788256A Withdrawn EP2052184A1 (fr) 2006-08-14 2007-08-06 Système de combustion, en particulier pour une turbine à gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP07788256A Withdrawn EP2052184A1 (fr) 2006-08-14 2007-08-06 Système de combustion, en particulier pour une turbine à gaz

Country Status (5)

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EP (2) EP1892472B1 (fr)
AT (1) ATE493615T1 (fr)
DE (1) DE502006008611D1 (fr)
ES (1) ES2356924T3 (fr)
WO (1) WO2008019969A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2169307A1 (fr) * 2008-09-29 2010-03-31 Siemens Aktiengesellschaft Buse à combustible
EP2169308A1 (fr) * 2008-09-29 2010-03-31 Siemens Aktiengesellschaft Alimentation en carburant et procédé d'injection du carburant
EP2329189B1 (fr) * 2008-09-29 2016-01-13 Siemens Aktiengesellschaft Buse à combustible
WO2016068922A1 (fr) * 2014-10-30 2016-05-06 Siemens Aktiengesellschaft Veilleuse et procédé pour la stabilisation d'une flamme de veilleuse dans une chambre de combustion soumise à une dynamique de combustion
CN106016358B (zh) * 2016-05-30 2019-04-30 中国科学院工程热物理研究所 一种兼具旋流、喷射与掺混作用的旋流器
CN110822479B (zh) * 2019-11-22 2020-09-29 四川航天中天动力装备有限责任公司 一种高燃油调节比的加力燃烧室喷油装置

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI1974U21844U1 (it) * 1974-08-30 1976-03-01 O F R Officine Flii Riello S P A Testa di combustione con elica accorciatrice di fiamma per bruciatori di gasolio
DE3636787A1 (de) * 1986-10-29 1988-05-19 Man Technologie Gmbh Brenner mit einer oelzerstaeubervorrichtung
JPH05203148A (ja) * 1992-01-13 1993-08-10 Hitachi Ltd ガスタービン燃焼装置及びその制御方法
US5575153A (en) * 1993-04-07 1996-11-19 Hitachi, Ltd. Stabilizer for gas turbine combustors and gas turbine combustor equipped with the stabilizer
DE9310257U1 (de) * 1993-07-09 1993-09-02 Viessmann Werke Gmbh & Co, 35108 Allendorf Gebläsebrenner
JP4134311B2 (ja) * 2002-03-08 2008-08-20 独立行政法人 宇宙航空研究開発機構 ガスタービン燃焼器

Also Published As

Publication number Publication date
ATE493615T1 (de) 2011-01-15
EP1892472A1 (fr) 2008-02-27
EP2052184A1 (fr) 2009-04-29
DE502006008611D1 (de) 2011-02-10
ES2356924T3 (es) 2011-04-14
WO2008019969A1 (fr) 2008-02-21

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