EP1892472A1 - 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
EP1892472A1
EP1892472A1 EP06016932A EP06016932A EP1892472A1 EP 1892472 A1 EP1892472 A1 EP 1892472A1 EP 06016932 A EP06016932 A EP 06016932A EP 06016932 A EP06016932 A EP 06016932A EP 1892472 A1 EP1892472 A1 EP 1892472A1
Authority
EP
European Patent Office
Prior art keywords
nozzle
burner
nozzle tube
opening
outlet opening
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
EP06016932A
Other languages
German (de)
English (en)
Other versions
EP1892472B1 (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
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 ES06016932T priority Critical patent/ES2356924T3/es
Priority to AT06016932T priority patent/ATE493615T1/de
Priority to EP06016932A priority patent/EP1892472B1/fr
Priority to DE502006008611T priority patent/DE502006008611D1/de
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
Anticipated expiration legal-status Critical

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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, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; 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, e.g. noise reduction means
    • 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.
  • 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 intensifies the entrainment of the combustion exhaust gases. As a consequence, the stability of the flame is increased.
  • the protruding elements are provided by a nozzle tube section having a corrugated inner circumferential surface extending up to the nozzle outlet opening educated.
  • This realization leads to an enlargement of the surface of the jet emerging from the nozzle opening.
  • the enhancement of vortex formation is essentially due to the increased radiation surface.
  • the corrugated inner peripheral surface at the nozzle outlet opening may in particular be designed such that it has a maximum deflection A about a mean opening radius R of the nozzle outlet opening and the ratio of the deflection to the mean opening radius through the relationship 0 . 03 ⁇ / A R ⁇ 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 circumferential 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 ⁇ / L T 2 ⁇ A ⁇ 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.
  • the protruding elements are formed by vanes arranged in the region of the nozzle outlet opening on the inner circumferential surface of the nozzle tube, which wings may in particular be delta wings.
  • Delta wings are triangular in shape and have a relatively low profile thickness relative to their length and depth.
  • the wings, in particular the delta wings lead to an increased vortex formation in the area of the wing edges.
  • the increased vortex formation is not first induced by the enlarged radiation surface, but is already present at the exit of the jet from the nozzle outlet opening.
  • the blades protrude at the nozzle exit port via the distance S from the inner circumferential surface, which is formed at the nozzle orifice in a circular shape with an opening diameter D, into the nozzle orifice.
  • the ratio of the distance S to the opening diameter D is determined by the relationship 0 . 03 ⁇ / S D ⁇ 0 . 2 given. The conditions which satisfy the given relationship lead to particularly good results in stabilizing the jet flame.
  • the wings are inclined at an angle ⁇ with respect to the radial direction of the nozzle outlet opening.
  • the angle ⁇ can in this case be in the range 65 ° ⁇ ⁇ 85 °, in particular.
  • the inclined wings in particular those with angles of inclination in the specified range, lead to a particularly advantageous vortex formation in the surface region the exiting from the nozzle outlet opening fluid jet. This leads in particular to good results for the flame stability, if the ratio of the distance S to the opening diameter D of the nozzle outlet opening satisfies the relationship given above.
  • a combustion system with a combustion chamber and a burner 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 region 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 may in particular be a burner according to the invention.
  • FIG. 1 An embodiment of a combustion system according to the invention is shown in a highly schematic representation in Fig. 1.
  • 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 premixed air / fuel mixture is injected into the combustion chamber 3 to form the jet flame 5.
  • 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 deflected radially inner region of 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 area, in the amplitude decreases from its maximum value A to zero, in the axial direction of the nozzle tube 7 has a length L T.
  • the ratio of the length L T of the transition region to the maximum amplitude A is defined by the relationship 1 ⁇ / L T 2 ⁇ A ⁇ 5 given.
  • the surface of the jet emerging from the nozzle outlet opening 15 of air / fuel mixture is increased in comparison to a jet of air / fuel mixture emerging from a nozzle outlet opening with a round cross section and the radius R.
  • 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 ⁇ / A R ⁇ 0 . 2 given is.
  • Fig. 2 is merely exemplary and schematic of the shape of the corrugation.
  • the number of wave crests and troughs may also be smaller or larger than shown in FIG.
  • Fig. 3 shows a second embodiment of the nozzle tube of the burner according to the invention.
  • the figure shows the nozzle tube 107 according to the second variant in a schematic section along its central longitudinal axis.
  • the nozzle tube 107 of the second embodiment in the region of the nozzle outlet opening 115 no corrugation. Instead are arranged in the region of the inner peripheral surface of the nozzle outlet opening 115 delta wing 119.
  • the delta wings 119 protrude beyond the distance S into the nozzle outlet opening 115.
  • the ratio of the distance S to the diameter D of the nozzle outlet opening 115 is in this case in particular by the relationship 0 . 03 ⁇ / S D ⁇ 0 . 2 given.
  • the delta wings 119 are inclined in the present embodiment by an angle ⁇ in the range between 65 ° and 85 ° against the radial direction in the nozzle tube 107. But there are also embodiments without inclination possible.
  • FIG. 1 A further exemplary embodiment of the combustion system according to the invention is shown in FIG.
  • 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 mentioned at this point, however, that the burner also in the second embodiment of the combustion system can be equipped with a corrugation or with delta wings in the region of its nozzle outlet opening 215.
  • the nozzle tube 207 projects into the combustion chamber 203 by the distance L.
  • the distance L, by which the nozzle tube 207 protrudes into the combustion chamber 203, is with the opening diameter D of the nozzle outlet opening preferably in a relationship by 0 . 3 ⁇ / L D ⁇ 3 given is. 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)
  • Gas Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Spray-Type Burners (AREA)
  • Control Of Turbines (AREA)
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
ES06016932T ES2356924T3 (es) 2006-08-14 2006-08-14 Sistemas de combustión, en especial para una turbina de gas.
AT06016932T ATE493615T1 (de) 2006-08-14 2006-08-14 Verbrennungssystem insbesondere für eine gasturbine
EP06016932A EP1892472B1 (fr) 2006-08-14 2006-08-14 Système de combustion en particulier pour une turbine à gaz
DE502006008611T DE502006008611D1 (de) 2006-08-14 2006-08-14 Verbrennungssystem insbesondere für eine Gasturbine
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 true EP1892472A1 (fr) 2008-02-27
EP1892472B1 EP1892472B1 (fr) 2010-12-29

Family

ID=37575196

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)

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

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2169308A1 (fr) * 2008-09-29 2010-03-31 Siemens Aktiengesellschaft Alimentation en carburant et procédé d'injection du carburant
EP2169307A1 (fr) * 2008-09-29 2010-03-31 Siemens Aktiengesellschaft Buse à combustible
WO2010034819A1 (fr) * 2008-09-29 2010-04-01 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
CN110822479A (zh) * 2019-11-22 2020-02-21 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

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1502459A (en) * 1974-08-30 1978-03-01 Ofr Spa Burner assembly for use in a fuel oil burner
DE3636787A1 (de) * 1986-10-29 1988-05-19 Man Technologie Gmbh Brenner mit einer oelzerstaeubervorrichtung
DE9310257U1 (de) * 1993-07-09 1993-09-02 Viessmann Werke Gmbh & Co, 35108 Allendorf Gebläsebrenner
US5323614A (en) * 1992-01-13 1994-06-28 Hitachi, Ltd. Combustor for gas turbine
US6026644A (en) * 1993-04-07 2000-02-22 Hitachi, Ltd. Stabilizer for gas turbine combustors and gas turbine combustor equipped with the stabilizer
EP1342956A2 (fr) * 2002-03-08 2003-09-10 National Aerospace Laboratory of Japan Chambre de combustion de turbine à gaz

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1502459A (en) * 1974-08-30 1978-03-01 Ofr Spa Burner assembly for use in a fuel oil burner
DE3636787A1 (de) * 1986-10-29 1988-05-19 Man Technologie Gmbh Brenner mit einer oelzerstaeubervorrichtung
US5323614A (en) * 1992-01-13 1994-06-28 Hitachi, Ltd. Combustor for gas turbine
US6026644A (en) * 1993-04-07 2000-02-22 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
EP1342956A2 (fr) * 2002-03-08 2003-09-10 National Aerospace Laboratory of Japan Chambre de combustion de turbine à gaz

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2169308A1 (fr) * 2008-09-29 2010-03-31 Siemens Aktiengesellschaft Alimentation en carburant et procédé d'injection du carburant
EP2169307A1 (fr) * 2008-09-29 2010-03-31 Siemens Aktiengesellschaft Buse à combustible
WO2010034819A1 (fr) * 2008-09-29 2010-04-01 Siemens Aktiengesellschaft Buse à combustible
CN102165258A (zh) * 2008-09-29 2011-08-24 西门子公司 燃料喷嘴
CN102165258B (zh) * 2008-09-29 2014-01-22 西门子公司 燃料喷嘴
RU2506497C2 (ru) * 2008-09-29 2014-02-10 Сименс Акциенгезелльшафт Топливная форсунка
US8959922B2 (en) 2008-09-29 2015-02-24 Siemens Aktiengesellschaft Fuel nozzle with flower shaped nozzle tube
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
CN110822479A (zh) * 2019-11-22 2020-02-21 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

Also Published As

Publication number Publication date
EP2052184A1 (fr) 2009-04-29
ES2356924T3 (es) 2011-04-14
WO2008019969A1 (fr) 2008-02-21
DE502006008611D1 (de) 2011-02-10
ATE493615T1 (de) 2011-01-15
EP1892472B1 (fr) 2010-12-29

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