EP2261566A1 - Brûleur et procédé de réduction d'oscillations de flammes à auto-induction dans un brûleur - Google Patents

Brûleur et procédé de réduction d'oscillations de flammes à auto-induction dans un brûleur Download PDF

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Publication number
EP2261566A1
EP2261566A1 EP09161318A EP09161318A EP2261566A1 EP 2261566 A1 EP2261566 A1 EP 2261566A1 EP 09161318 A EP09161318 A EP 09161318A EP 09161318 A EP09161318 A EP 09161318A EP 2261566 A1 EP2261566 A1 EP 2261566A1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
flow body
jet pipe
zone
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Withdrawn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
EP09161318A
Other languages
German (de)
English (en)
Inventor
Olaf Hein
Jaap Van Kampen
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 EP09161318A priority Critical patent/EP2261566A1/fr
Priority to PCT/EP2010/055827 priority patent/WO2010136300A2/fr
Priority to DE112010002095T priority patent/DE112010002095A5/de
Publication of EP2261566A1 publication Critical patent/EP2261566A1/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Withdrawn legal-status Critical Current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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • 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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention relates to a burner, in particular for a gas turbine, and to a method for reducing self-induced flame oscillations in a burner.
  • combustion chamber vibrations are an undesirable side effect of the combustion process, since they cause an increased mechanical and thermal loading of the burner components and the combustion chamber components.
  • combustion chamber hum caused an increased noise in the environment of the respective combustion chamber.
  • a reduction in the combustion chamber humming or a minimization of self-induced flame vibrations has hitherto been achieved in part with the aid of Helmholtz resonators.
  • Another possibility is to supply the burner used an increased pilot gas quantity. Pilot gas or pilot fuel is usually used to stabilize the flame. However, an increased supply of pilot gas can also lead to increased NO x emissions.
  • the first object is achieved by a burner according to claim 1.
  • the second object is achieved by a gas turbine according to claim 10.
  • the third object is achieved by a method according to claim 11.
  • the burner according to the invention comprises a mixture forming zone for forming a fuel-air mixture and a burner outlet. Between the mixture-forming zone and the burner outlet, an acceleration zone for increasing the speed of the fuel-air mixture is arranged.
  • the acceleration zone comprises at least one flow body.
  • the flow body is flowed around by the fuel-air mixture during operation of the burner in the output region of the burner.
  • the purpose of the flow body is to seal off or at least mitigate pressure waves which propagate from the combustion chamber in the direction of the mixture formation zone.
  • an acoustic partial decoupling is effected between a combustion chamber adjoining the burner outlet and the mixture-forming zone.
  • this partial decoupling can be achieved by measures which, at a suitable point between the mixture-forming zone and the combustion chamber, markedly increase the level of the velocity of the fuel-air mixture, in particular with the aid of a flow body.
  • a velocity level based on the speed of sound should be set here between 0.35 Ma and 0.45 Ma.
  • the acceleration zone can be arranged, for example, in a jet pipe.
  • the jet pipe can also comprise a central axis and the flow body can be arranged in the region of the central axis.
  • the flow body by means of at least one strut connected to the jet pipe, in particular fixed.
  • a diffuser can be arranged between the acceleration zone and the burner outlet.
  • the pressure losses generated as a result of the acceleration of the fuel-air mixture can be minimized and the greatest possible pressure recovery can be effected.
  • the diffuser can be designed so that a free flow in the diffuser is ensured at each operating point. In this way, possible flashbacks are effectively prevented.
  • the flow body may comprise a region facing the burner exit. In this region, which faces the burner outlet, the flow body may comprise at least one opening for blowing air and / or fuel into the jet pipe.
  • the jet pipe may include a central axis and at least one opening for blowing air and / or fuel into the jet pipe.
  • the opening in the jet pipe is arranged in an axial region with respect to the central axis, which corresponds to the position of the area of the flow body facing the burner outlet. In this way, secondary air can be injected into the jet pipe in the rear region of the flow body, that is to say toward the burner outlet. This causes at least partial absorption of the sound waves, which, starting from the combustion chamber, move in the direction of the burner.
  • the burner may include a fuel supply with a fuel acceleration zone.
  • the fuel acceleration zone may be configured as a nozzle having a tapered cross section.
  • the fuel acceleration zone may comprise at least one flow body.
  • the fuel supply may include an output. Between the fuel acceleration zone and the outlet, a diffuser may be arranged.
  • the fuel acceleration zone can be designed as a fuel jet tube.
  • the fuel jet tube may comprise a central axis and the flow body may be arranged in the region of the central axis.
  • the flow body can be connected, in particular fastened, to the fuel jet pipe by means of at least one strut.
  • the burner can basically be designed as a jet burner, preferably as a spin-free jet burner.
  • the gas turbine according to the invention comprises a burner according to the invention, as described in the preceding sections.
  • the gas turbine according to the invention has in particular the same advantages as the burner according to the invention.
  • the method according to the invention for reducing self-induced flame vibrations relates to a burner which comprises a mixture-forming zone, a burner outlet and an acceleration zone arranged between the mixture-forming zone and the burner outlet.
  • a fuel-air mixture is formed in the mixture-forming zone.
  • the acceleration zone the speed of the fuel-air mixture is increased.
  • the fuel-air mixture is conducted past a flow body in the acceleration zone. This causes a partial acoustic decoupling between the mixture forming zone and a combustion chamber adjoining the burner outlet.
  • the velocity of the fuel-air mixture is preferably increased to a value between 0.35 Ma and 0.45 Ma when passing by the flow body.
  • the pressure of the fuel-air mixture can be increased.
  • the pressure of the fuel-air mixture can be increased, in particular with the aid of a diffuser, which, for example, can have an opening angle in the range from greater than 0 degrees to approximately 10 degrees.
  • the acceleration zone can be designed as a jet pipe.
  • the flow body may comprise a region facing the burner exit. In the region of the flow body facing the burner outlet, air can be blown into the jet pipe. This causes at least partial absorption of the sound waves, which, starting from the combustion chamber, move in the direction of the burner.
  • the burner may include a fuel supply with a fuel acceleration zone.
  • the velocity of fuel flowing through the fuel supply may be increased in the fuel acceleration zone.
  • the speed of fuel flowing through the fuel supply can be increased in the fuel acceleration zone, for example, by passing the fuel past a flow body.
  • the velocity of fuel flowing through the fuel supply may continue to flow therethrough in the fuel acceleration zone be increased, that the fuel is passed through a designed as a nozzle with a tapered cross section fuel acceleration zone.
  • the partial acoustic decoupling between the combustion chamber and the mixture formation zone which is achieved in the context of the invention by raising the speed of the fuel-air mixture, reduces the formation of self-induced flame oscillations and combustion chamber hum.
  • FIG. 1 schematically shows a gas turbine.
  • a gas turbine has inside a rotor rotatably mounted about a rotation axis with a shaft 107, which is also referred to as a turbine runner.
  • a turbine runner Along the rotor follow one another an intake housing 109, a compressor 101, a combustion system 151 with a number of jet burners 1, a turbine 105 and the exhaust housing 190.
  • the combustion system 151 communicates with a, for example, annular hot gas channel.
  • a plurality of successively connected turbine stages form the turbine 105.
  • Each turbine stage is formed of blade rings.
  • the guide vanes 117 are fastened to an inner housing of a stator, whereas the moving blades 115 of a row are attached to the rotor, for example by means of a turbine disk. Coupled to the rotor is a generator or a work machine.
  • FIG. 2 schematically shows the occurrence of self-induced flame oscillations or Brennschbrummens.
  • the starting point is the occurrence of initially small pressure fluctuations 20 in the combustion chamber. These pressure fluctuations 20 lead to changes in the air mass flow 21 in the burner channels. These changes in the air mass flow in the burner channels 21 in turn cause a change in the flow rate 22 and / or a change in the mixture composition 23. The change in the mixture composition 23 in turn leads to a change in the flame speed or auto-ignition 24th
  • the change in the flow rate 22 and / or the change in the flame speed or the autoignition 24 cause / causes a change in position and shape of the ignition position or the flame front 25.
  • the position and shape change the ignition position or the flame front 25 leads to a change in the heat release and the Heat transfer 26, which in turn has a local pressure and temperature change 27 result.
  • the local pressure and temperature change 27 induces a pressure pulse 28, which in turn amplifies the pressure fluctuations in the combustion chamber 20.
  • the FIG. 3 schematically shows a burner according to the invention.
  • the burner 1 comprises a burner outlet 2 leading to a combustion chamber, a flow channel 8 designed as a jet pipe, and a fuel feed 5.
  • the center axis of the burner 1 is identified by the reference numeral 4.
  • the center axis 4 of the burner 1 also represents the central axis of the fuel feed 5 and of the jet pipe 8. In principle, however, the feed of the fuel can also be effected differently.
  • the fuel supply 5 is configured as a fuel jet tube and comprises an output 18, through which a fuel 6 is injected into an air flow 7 surrounding the fuel feed 5. Immediately before the exit 18 of the Fuel supply 5 thus forms a mixture forming zone 3, in which the fuel 6 is mixed with the air 7.
  • the resulting fuel-air mixture then flows into the jet pipe 8.
  • the jet pipe 8 comprises a flow body 10 and a region 12 configured as a diffuser.
  • the flow body 10 has an oval shape with an axis of symmetry about which the oval is rotationally symmetrical. It is arranged in the region of the central axis 4 and fastened by means of a strut 13 on the jet pipe 8.
  • the symmetry axis of the oval coincides with the central axis 4 of the jet pipe 8.
  • the flow body 10 comprises an obtuse region 15 facing the fuel feed 5 and a tapering region 14 facing the burner exit 2.
  • the blunt region 15 of the flow body 10 leads to a reduction of the flow cross section in the flow direction of the fluid flowing through the jet tube 8.
  • the pointed region 14 of the flow body leads to an enlargement of the flow cross-section, which is available to the flowing fluid.
  • the burner outlet 2 facing tapered region 14 of the flow body 10 includes openings through which secondary air and / or fuel is injected into the leading to the burner outlet 2 region of the jet pipe 8 or can be blown. This is indicated by arrows 17 in FIG FIG. 3 shown.
  • the jet pipe 8 is configured in a region 12, which extends from the flow body to the burner exit 2, with a cross section enlarging towards the burner outlet 2 and thus as a diffuser 12.
  • the jet pipe 8 or the diffuser comprises openings through which secondary air and / or fuel is blown or blown into the area of the jet pipe 8 leading to the burner exit 2. This is indicated by arrows 16 in FIG FIG. 3 shown.
  • the flow direction of the fuel-air mixture generated in the mixture-forming zone 3 in the jet pipe 8 is indicated by the reference numeral 11.
  • the fuel-air mixture flows around the flow body 10 and is initially accelerated. This area is called the acceleration zone 9 in the FIG. 3 characterized.
  • the fuel-air mixture flows through the configured as a diffuser 12 region of the jet pipe 8, wherein the pressure of the fuel-air mixture increases.
  • FIG. 4 schematically shows a fuel supply 5a according to the invention, which differs from that in the FIG. 3 shown fuel supply 5 differs in that it comprises a flow body 29.
  • the flow body 29, which may correspond in shape to the flow body 10 in the jet pipe 8, is arranged in the interior of the fuel feed 5a in the region of the central axis 19 of the fuel feed 5a.
  • the flow body 29 is attached by means of a strut 32 to the fuel supply 5a.
  • the fuel 6 flows around the flow body 29.
  • the fuel 6 is first accelerated in a fuel acceleration zone 30 characterized by a flow cross section decreasing in the flow direction.
  • the pressure of the fuel 6 is increased in a zone 31 of the fuel feed 5a which is characterized by a flow cross section increasing in the flow direction. In this way, any flow fluctuations in the fuel supply 5a are reduced.
  • FIG. 5 schematically shows an alternative fuel supply 5b according to the invention, which differs from that in the FIG. 3 5 differs in that it comprises a Venturi nozzle designed as a tapered cross-section 33 area.
  • This area acts as a fuel acceleration zone 30.
  • a region 31 adjoins, in which the cross section of the fuel supply 5b increases. As it flows through this region 31, the pressure of the fuel 6 is increased. In this way, any flow fluctuations in the fuel supply 5b are reduced.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP09161318A 2009-05-28 2009-05-28 Brûleur et procédé de réduction d'oscillations de flammes à auto-induction dans un brûleur Withdrawn EP2261566A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP09161318A EP2261566A1 (fr) 2009-05-28 2009-05-28 Brûleur et procédé de réduction d'oscillations de flammes à auto-induction dans un brûleur
PCT/EP2010/055827 WO2010136300A2 (fr) 2009-05-28 2010-04-29 Brûleur et procédé pour réduire des oscillations de flammes auto-induites dans un brûleur
DE112010002095T DE112010002095A5 (de) 2009-05-28 2010-04-29 Brenner und verfahren zur verringerung von selbstinduzierten flammenschwingungen in einem brenner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09161318A EP2261566A1 (fr) 2009-05-28 2009-05-28 Brûleur et procédé de réduction d'oscillations de flammes à auto-induction dans un brûleur

Publications (1)

Publication Number Publication Date
EP2261566A1 true EP2261566A1 (fr) 2010-12-15

Family

ID=41343308

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09161318A Withdrawn EP2261566A1 (fr) 2009-05-28 2009-05-28 Brûleur et procédé de réduction d'oscillations de flammes à auto-induction dans un brûleur

Country Status (3)

Country Link
EP (1) EP2261566A1 (fr)
DE (1) DE112010002095A5 (fr)
WO (1) WO2010136300A2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013155363A1 (fr) * 2012-04-12 2013-10-17 Massachusetts Institute Of Technology Système de suppression de l'instabilité de la combustion en utilisant un matériau de maintien de flamme isolant thermique

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2632300A (en) * 1949-08-03 1953-03-24 Thermal Res & Engineering Corp Combustion stabilization means having igniter grill heated by pilotburner
US2927423A (en) * 1956-02-09 1960-03-08 Henryk U Wisniowski Prevention of screeching combustion in jet engines
EP0623786A1 (fr) * 1993-04-08 1994-11-09 ABB Management AG Chambre de combustion
DE4417538A1 (de) * 1994-05-19 1995-11-23 Abb Management Ag Brennkammer mit Selbstzündung

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2632300A (en) * 1949-08-03 1953-03-24 Thermal Res & Engineering Corp Combustion stabilization means having igniter grill heated by pilotburner
US2927423A (en) * 1956-02-09 1960-03-08 Henryk U Wisniowski Prevention of screeching combustion in jet engines
EP0623786A1 (fr) * 1993-04-08 1994-11-09 ABB Management AG Chambre de combustion
DE4417538A1 (de) * 1994-05-19 1995-11-23 Abb Management Ag Brennkammer mit Selbstzündung

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013155363A1 (fr) * 2012-04-12 2013-10-17 Massachusetts Institute Of Technology Système de suppression de l'instabilité de la combustion en utilisant un matériau de maintien de flamme isolant thermique

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Publication number Publication date
WO2010136300A2 (fr) 2010-12-02
WO2010136300A3 (fr) 2011-01-27
DE112010002095A5 (de) 2012-10-25

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