WO2010136300A2 - Brenner und verfahren zur verringerung von selbstinduzierten flammenschwingungen in einem brenner - Google Patents
Brenner und verfahren zur verringerung von selbstinduzierten flammenschwingungen in einem brenner Download PDFInfo
- Publication number
- WO2010136300A2 WO2010136300A2 PCT/EP2010/055827 EP2010055827W WO2010136300A2 WO 2010136300 A2 WO2010136300 A2 WO 2010136300A2 EP 2010055827 W EP2010055827 W EP 2010055827W WO 2010136300 A2 WO2010136300 A2 WO 2010136300A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- burner
- fuel
- flow body
- jet pipe
- mixture
- Prior art date
Links
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. An increased Supply of pilot gas, however, 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 raise the level of the speed 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.
- 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.
- 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, by means of at least one strut with the fuel jet tube.
- 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 has a mixture-forming zone, a burner outlet and between the mixture-forming zone and comprises the burner output arranged acceleration zone.
- 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 losses generated as a result of the acceleration can be reduced.
- the pressure of the fuel-air mixture can in particular by means of a diffuser, which for example a
- Opening angle in the range of greater than 0 degrees to about 10 degrees may be increased.
- 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. This will in addition to the acoustic partial decoupling in the exit area of the burner also in the
- the speed of fuel flowing through the fuel feed may be in the
- Fuel acceleration zone for example, be increased by the fact that the fuel is conducted past a flow body.
- the velocity of fuel flowing through the fuel supply may be further increased in the fuel acceleration zone by passing the fuel through a fuel acceleration zone configured as a nozzle having a tapered cross-section.
- 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 shows schematically a gas turbine.
- Fig. 2 shows schematically the emergence of self-induced flame oscillations or the emergence of Brennschbrummens.
- Fig. 3 shows schematically a burner according to the invention.
- Fig. 4 shows schematically a fuel supply according to the invention.
- Fig. 5 shows schematically an alternative fuel supply according to the invention.
- FIG. 1 shows schematically 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. As seen in the flow direction of a working medium follows in the hot gas duct of a guide vane row 117 a
- Blades 115 formed series.
- 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.
- Combustion system 151 out and mixed there with a fuel. The mixture is then using the jet burner 1 burned to form the working medium in the combustion system 151. From there, the working medium flows past the guide vanes 117 and the rotor blades 115 along the hot gas channel. At the rotor blades 115, the working medium expands in a pulse-transmitting manner, so that the rotor blades 115 drive the rotor and this drives the working machine coupled thereto or a generator (not shown).
- FIG. 2 schematically shows the occurrence of self-induced flame oscillations or combustion chamber hum.
- 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 position and shape of 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.
- FIG. 3 shows schematically 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 central axis 4 of the burner 1 also represents the central axis of the fuel feed 5 and the jet pipe 8. At the same time, however, the supply of the fuel can also be carried out differently.
- the fuel feed 5 is configured as a fuel jet tube and comprises an output 18, through which a fuel 6 is injected into an air stream 7 surrounding the fuel feed 5. Immediately before the output 18 of the fuel supply 5 thus forms a
- the resulting fuel-air mixture then flows into the jet pipe 8.
- the jet pipe 8 comprises a
- the flow body 10 and designed as a diffuser region 12.
- 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 illustrated by arrows 17
- 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 illustrated by arrows 16 in FIG.
- 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 marked as acceleration zone 9 in FIG. Subsequently, 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.
- secondary air 16, 17 into the jet pipe 8 in the region of the flow body 10 facing the burner exit 2 or into the region 12 designed as a diffuser, an at least partial absorption of the sound waves is obtained, which move from the combustion chamber in the direction of the burner.
- FIG. 4 schematically shows a fuel feed 5a according to the invention, which differs from the fuel feed 5 shown in FIG. 3 in that it comprises a flow body 29.
- the flow body 29, the shape of the flow body 10th may correspond in the jet pipe 8, is arranged in the interior of the fuel supply 5a in the region of the central axis 19 of the fuel supply 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 feed 5b according to the invention, which differs from the fuel feed 5 illustrated in FIG. 3 in that it comprises a region 33 designed as a venturi nozzle with a tapering cross section. This area acts as a fuel acceleration zone 30. At this area, in the direction of the outlet 18 of the fuel feed 5b, a region 31 adjoins, in which the cross section of the fuel feed 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.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE112010002095T DE112010002095A5 (de) | 2009-05-28 | 2010-04-29 | Brenner und verfahren zur verringerung von selbstinduzierten flammenschwingungen in einem brenner |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09161318.2 | 2009-05-28 | ||
EP09161318A EP2261566A1 (de) | 2009-05-28 | 2009-05-28 | Brenner und Verfahren zur Verringerung von selbstinduzierten Flammenschwingungen in einem Brenner |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2010136300A2 true WO2010136300A2 (de) | 2010-12-02 |
WO2010136300A3 WO2010136300A3 (de) | 2011-01-27 |
Family
ID=41343308
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2010/055827 WO2010136300A2 (de) | 2009-05-28 | 2010-04-29 | Brenner und verfahren zur verringerung von selbstinduzierten flammenschwingungen in einem brenner |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP2261566A1 (de) |
DE (1) | DE112010002095A5 (de) |
WO (1) | WO2010136300A2 (de) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140134551A1 (en) * | 2012-04-12 | 2014-05-15 | Massachusetts Institute Of Technology | Combustion Instability Suppression System Using Heat Insulating Flameholding Material |
Family Cites Families (4)
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 |
EP0623786B1 (de) * | 1993-04-08 | 1997-05-21 | Asea Brown Boveri Ag | Brennkammer |
DE4417538A1 (de) * | 1994-05-19 | 1995-11-23 | Abb Management Ag | Brennkammer mit Selbstzündung |
-
2009
- 2009-05-28 EP EP09161318A patent/EP2261566A1/de not_active Withdrawn
-
2010
- 2010-04-29 DE DE112010002095T patent/DE112010002095A5/de not_active Withdrawn
- 2010-04-29 WO PCT/EP2010/055827 patent/WO2010136300A2/de active Application Filing
Non-Patent Citations (1)
Title |
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None |
Also Published As
Publication number | Publication date |
---|---|
WO2010136300A3 (de) | 2011-01-27 |
EP2261566A1 (de) | 2010-12-15 |
DE112010002095A5 (de) | 2012-10-25 |
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