CN103717970A - Combustor with bi-directional manifold for dynamics damping - Google Patents

Combustor with bi-directional manifold for dynamics damping Download PDF

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Publication number
CN103717970A
CN103717970A CN201180070864.5A CN201180070864A CN103717970A CN 103717970 A CN103717970 A CN 103717970A CN 201180070864 A CN201180070864 A CN 201180070864A CN 103717970 A CN103717970 A CN 103717970A
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China
Prior art keywords
burner
manifold
stream
burners
oxygen gas
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Application number
CN201180070864.5A
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Chinese (zh)
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CN103717970B (en
Inventor
I.A.斯罗博戴安斯基
D.V.特雷亚科夫
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General Electric Co
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General Electric Co
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    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • 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
    • 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
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

The present application provides a combustor (25) for combusting a flow of air and a flow of fuel. The combuster may include a number of fuel nozzles (110), an air path with the flow of air therein leading to the fuel nozzles, and a manifold (230) positioned in the air path upstream of the fuel nozzles. The manifold may include a number of resonator tubes (250).

Description

For the burner with two-way manifold that power is carried out to damping
Technical field
The present invention relates generally to gas-turbine unit and relates more specifically to a kind of burner with two-way manifold for gas-turbine unit, and wherein said two-way manifold is used as Helmholtz (Helmholtz) type resonator so that the power in damping burner (dynamics).
Background technology
Generally, gas-turbine unit burns to the mixture of compressed air and compressed fuel, to produce hot burning gases.The burning gases of heat can be for providing the mechanical power of use.Burning can occur in a plurality of burners of the longitudinal axis radial location around gas-turbine unit.Due to the turbulent flow character in combustion process be discharged into the large volume strain energy in closed cavities, this type of burner may easily be subject to various patterns and the frequency influence of the transient pressure vibration of the amplitude that burning causes.If the one in frequency band is corresponding with the natural frequency band of part in gas-turbine unit or subsystem, may cause so the damage of this part or whole engine.
Traditionally, for suppressing the known method of these pressure oscillations, concentrate on excitation source and feedback mechanism decoupling aspect.Generally, this type of restraining device is only effective in the limited range of operation of burner.
Therefore, need to improve burner design and operation method.Preferably, these designs and method can limit burner power and its frequency range, to prevent, it are caused damage and guarantee sufficient component life.
Summary of the invention
Therefore the present invention provides a kind of burner for air stream and fuel flow are burnt.Described burner can comprise: a plurality of fuel nozzles; Wherein, with the air path of described air stream, described air path is led to described fuel nozzle; And manifold, described manifold is positioned in the described air path of described fuel nozzle upstream end.Described manifold can comprise a plurality of resonantrons.
The present invention provides a kind of method of burner of controlling gas turbine further.Described method can comprise the following steps: stream of ambient air, reduced oxygen gas stream and fuel flow are burnt; Produce combustion powered; Positioning bidirectional manifold so that its be communicated with described stream of ambient air and described reduced oxygen gas stream; Around described two-way manifold, locate a plurality of resonantrons; And adjust described resonantron size so that combustion powered described in damping.
The present invention provides a kind of stoichiometry (stoichiometric) EGR burner for stream of ambient air, reduced oxygen gas stream and fuel flow are burnt further.Described burner casing comprises: a plurality of fuel nozzles; Wherein, with the surrounding air path of described stream of ambient air, described fuel nozzle is led in described surrounding air path; The hypoxemia recirculation entrance wherein with described reduced oxygen gas stream; And two-way manifold, described two-way manifold is communicated with described stream of ambient air and/or described reduced oxygen gas stream.Described two-way manifold can comprise a plurality of resonantrons.
When in conjunction with some accompanying drawings and appended claims and while reading following detailed description, one of skill in the art can have a clear understanding of these and other features and the advantage of the present invention and corresponding patent.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of gas-turbine unit.
Fig. 2 is with the side cross-sectional, view of the burner of two-way manifold and a plurality of resonantrons as described in this specification.
Fig. 3 is the amplification side cross-sectional, view of a part for burner shown in Fig. 2, two-way manifold shown in it and resonantron.
Fig. 4 is the schematic diagram of the example of Helmholtz resonator.
The specific embodiment
Referring now to accompanying drawing, wherein in some accompanying drawings, similar numeral refers to similar components, and Fig. 1 illustrates the schematic diagram of gas-turbine unit 10 as described in this specification.Gas-turbine unit 10 can include compressor 15.Compressor 15 compressions enter air-flow 20.Compressor 15 is transported to burner 25 by compressed air stream 20.Burner 25 mixes compressed air stream 20 with the fuel flow 30 through pressurization, and some burning mixt is to produce combustion-gas flow 35.Although only single burner 25 is shown, gas-turbine unit 10 also can comprise any amount of burner 25.Then, combustion-gas flow 35 is transported on turbine 40.35 pairs of turbines 40 of combustion-gas flow drive to produce mechanical power.The mechanical power producing in turbine 40 is carried out drive compression machine 15 via axle 45, and drives as the external loading 50 of generator and similar installation.
Gas-turbine unit 10 can use natural gas, various types of synthesis gas and/or other types fuel.Gas-turbine unit 10 can be any of the multiple different gas-turbine unit that provides of the General Electric Co. Limited (General Electric Company) that is arranged in Schenectady, New York and similar company.Gas-turbine unit 10 can have different configurations and can use other types parts.In this manual, also can use the gas-turbine unit of other types.In this manual, also the turbine of a plurality of gas-turbine units, other types and other types generating equipment can be used together.
Fig. 2 illustrates the example of burner 25.In this example, stoichiometry EGR (" SEGR ") burner 100 is illustrated.This description also can be used the burner of other types.Stoichiometry EGR burner 100 can comprise a plurality of fuel nozzles 110, and described fuel nozzle is positioned in end cap 120.Although five (5) fuel nozzles 110 are shown, also can use in this manual any quantity fuel nozzle 110.Fuel nozzle 110 can be communicated with fuel flow 30 via one or more fuel inlets 130.Hypoxemia recirculation entrance 140 also can be around end cap 120 location to be provided to reduced oxygen gas stream 150 on fuel nozzle 110.Reduced oxygen gas stream 150 can send from turbine 40 via stoichiometry waste gas recovery compressor (and not shown) and similar installation.
Stoichiometry EGR burner 100 can also comprise combustion liner 160.Combustion liner 160 can limit combustion zone 170 therein.Fair water sleeves 180 can be around combustion liner 160, and can limit therein environment air path 190 for the stream of ambient air 20 from compressor 15.Housing 200 can be around fair water sleeves 180 and combustion liner 160.Transition piece 210 can be positioned on the downstream part of combustion zone 170.
Bleeding point 220 can be located around housing 200, and can be communicated with in one direction with the surrounding air path 190 of fair water sleeves 180 and be communicated with on other direction with fuel nozzle 110 and hypoxemia recirculation entrance 140.Bleeding point 220 can be communicated with turbine 40 and other devices.In jet mode, enter air-flow 20 and 190 extend along surrounding air path, in described surrounding air path, described in to enter air-flow be in the mixed downstream of fuel nozzle 110 the 170 interior burnings in combustion zone with reduced oxygen gas stream 150 and fuel flow 130.Or a part that enters air-flow 20 can be extracted out via bleeding point 220, remaining stream continues to flow to fuel nozzle 110 simultaneously.Under the pattern of bleeding, a part for reduced oxygen gas stream 150 also can be extracted out via bleeding point 220.In this manual, also can use other to be configured to and miscellaneous part.
End cap 120 also can comprise two-way manifold 230 so that suitable mutually with jet mode and the pattern of bleeding, and holds injection stream and enters in burner 100 or hold the stream of bleeding.Two-way manifold 230 can be large circle in shape, and can comprise circular cavity 240.Two-way manifold 230 also can comprise a plurality of resonantrons 250, and described resonantron extends and extend the fair water sleeves 180 in surrounding air path 190 240 of cavitys.
As shown in Figure 4, two-way manifold 230 is served as Helmholtz resonator 260 to a great extent.Therefore, Helmholtz resonator 260 comprises and serves as the cavity 240 of main body 270 and serve as the resonantron 250 of throat 280.Substantially limit, Helmholtz resonator 260Shi sound chamber (acoustical chamber), it includes pressure fluid to vibrate with concrete frequency.The geometric configuration of Helmholtz resonator 260 is directly determined frequency of oscillation.If fluid pressure fluctuates because of external force impact, so resonator 260 can be tuned to the amplitude of these fluctuations is carried out to damping vibration frequency in the situation that.Helmholtz resonator 260 comprises that main body 270 and diameter are less than the throat 280 of main body 270.The pressure fluid that enters throat 280 is to be collected in main body 270, until the pressure in main body 270 is greater than exterior fluid pressure.Now, the fluid in main body 270 leaves via throat 280, thereby reduces the pressure in main body 270.Lower pressure lures that fluid reenters main body 270 into, and like this, process can repeat.Air circle moves the resonant frequency of setting up Helmholtz resonator 260.
As mentioned above, the resonant frequency of Helmholtz resonator 260 is mainly determined by its geometric configuration.Exactly, columniform Helmholtz resonator 60 can produce resonant frequency " f ", and described resonant frequency is partly based on following equation: f=c/2 Π * √ d 2/ LHD 2.In this equation, " c " is that for example, " d " is the diameter of throat 280 by the velocity of sound in fluid (, air, fuel, diluent etc.), and " L " is the length of throat 280, and " H " is the length of main body 270, and " D " is the length of main body 270.In this example, the configuration of main body 270, be circular cavity 240, through fixing so that resonant frequency can be resonantron 250 by changing the 280(of throat) length and diameter change.Thus, resonantron 250 can be adjusted to size for some frequency range and carry out damping, as to the most serious frequency range of burning hardware and manifold 230 itself.In this manual, can use any amount of resonantron 250 that is any required size, shape or configuration.In this manual, also can with the resonantron 250 of different configurations, carry out damping different frequency scope together.
Therefore the Helmholtz resonator 260 that, two-way manifold 130 forms prevents high cycle fatigue by some frequency range of damping in this manual.In addition, no matter two-way manifold 230 is with jet mode or bleeds mode operation, and Helmholtz resonator 260 all provides this type of protection.Although this description is described stoichiometry EGR burner 100, Helmholtz resonator 260 also can be suitable for burner and the applicable other types device that stands hunting of frequency and analogue of other types.In this manual, can use unidirectional, two-way or multidirectional stream.
Should be understood that, aforementioned content only relates to some embodiment of the present invention and corresponding patent.One of skill in the art can make in this manual multiple variation and modification in the situation that not deviating from overall spirit of the present invention and scope, and wherein overall spirit of the present invention and scope are limited by appended claims and its equivalent.

Claims (20)

1. the burner for air stream and fuel flow are burnt, described burner comprises:
A plurality of fuel nozzles;
The air path wherein with described air stream, described air path is led to described a plurality of fuel nozzle; And
Manifold, described manifold is located in the described air path of described a plurality of fuel nozzle upstream ends;
Wherein said manifold comprises a plurality of resonantrons.
2. burner as claimed in claim 1, it further comprises stoichiometry EGR burner.
3. burner as claimed in claim 1, wherein said manifold is communicated with the hypoxemia recirculation entrance with reduced oxygen gas stream wherein.
4. burner as claimed in claim 3, wherein said manifold comprises two-way manifold, wherein said air stream extends in a first direction and described reduced oxygen gas stream extends upward in second party.
5. burner as claimed in claim 1, wherein said air path is limited between combustion liner and fair water sleeves.
6. burner as claimed in claim 5, wherein said air path comprises bleeding point.
7. burner as claimed in claim 1, it further comprises jet mode and the pattern of bleeding.
8. burner as claimed in claim 1, wherein said manifold comprises circular cavity.
9. burner as claimed in claim 1, wherein said manifold and described a plurality of resonantron comprise Helmholtz resonator.
10. burner as claimed in claim 9, wherein said manifold comprises the main body of described Helmholtz resonator.
11. burners as claimed in claim 9, wherein said a plurality of resonantrons comprise the throat of described Helmholtz resonator.
12. burners as claimed in claim 9, wherein said Helmholtz resonator carries out damping to the vibration from wherein passing through.
13. burners as claimed in claim 1, wherein said a plurality of resonantrons comprise length and diameter separately.
14. burners as claimed in claim 13, wherein said a plurality of resonantrons comprise the predetermined length corresponding with the frequency of described burner and predetermined diameter separately.
15. 1 kinds of methods for the burner of controlling gas turbine, described method comprises:
Stream of ambient air, reduced oxygen gas stream and fuel flow are burnt;
Produce combustion powered;
Two-way manifold is set to be communicated with described stream of ambient air and described reduced oxygen gas stream;
Around described two-way manifold, a plurality of resonantrons are set; And
Adjust described a plurality of resonantron so that combustion powered described in damping.
16. 1 kinds of stoichiometry EGR burners for stream of ambient air, reduced oxygen gas stream and fuel flow are burnt, described stoichiometry EGR burner comprises:
A plurality of fuel nozzles;
The surrounding air path wherein with described stream of ambient air, described a plurality of fuel nozzle is led in described surrounding air path;
Wherein the hypoxemia with described reduced oxygen gas stream recycles entrance; And
Two-way manifold, described two-way manifold is communicated with described stream of ambient air and/or described reduced oxygen gas stream;
Wherein said two-way manifold comprises a plurality of resonantrons.
17. stoichiometry EGR burners as claimed in claim 16, wherein said two-way manifold comprises in a first direction the described stream of ambient air of extending and in the upwardly extending described reduced oxygen gas stream of second party.
18. stoichiometry EGR burners as claimed in claim 16, it further comprises jet mode and the pattern of bleeding.
19. stoichiometry EGR burners as claimed in claim 16, wherein said two-way manifold and described a plurality of resonantron comprise Helmholtz resonator.
20. stoichiometry EGR burners as claimed in claim 16, wherein said a plurality of resonantrons comprise the predetermined length corresponding with the frequency of described burner and predetermined diameter separately.
CN201180070864.5A 2011-05-25 2011-05-25 Combustor with bi-directional manifold for dynamics damping Expired - Fee Related CN103717970B (en)

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CN103717970B CN103717970B (en) 2017-03-22

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1001224A2 (en) * 1998-11-12 2000-05-17 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
US6164058A (en) * 1997-07-15 2000-12-26 Abb Research Ltd. Arrangement for damping combustion-chamber oscillations
EP1568869A1 (en) * 2002-12-02 2005-08-31 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor, and gas turbine with the combustor
US20060059913A1 (en) * 2004-09-21 2006-03-23 Siemens Aktiengesellschaft Combustion chamber for a gas turbine with at least two resonator devices
DE102005062284A1 (en) * 2005-12-24 2008-01-31 Alstom Technology Ltd. Combustion chamber for gas turbine of power plant system, has damping device that is formed as Helmholtz Resonator arrangement with helmholtz-Resonator including resonator area and resonator neck, and is attached to chamber through opening

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8448416B2 (en) * 2009-03-30 2013-05-28 General Electric Company Combustor liner
EP2383514A1 (en) * 2010-04-28 2011-11-02 Siemens Aktiengesellschaft Combustion system and method for dampening such a combustion system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6164058A (en) * 1997-07-15 2000-12-26 Abb Research Ltd. Arrangement for damping combustion-chamber oscillations
EP1001224A2 (en) * 1998-11-12 2000-05-17 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
EP1568869A1 (en) * 2002-12-02 2005-08-31 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor, and gas turbine with the combustor
US20060059913A1 (en) * 2004-09-21 2006-03-23 Siemens Aktiengesellschaft Combustion chamber for a gas turbine with at least two resonator devices
DE102005062284A1 (en) * 2005-12-24 2008-01-31 Alstom Technology Ltd. Combustion chamber for gas turbine of power plant system, has damping device that is formed as Helmholtz Resonator arrangement with helmholtz-Resonator including resonator area and resonator neck, and is attached to chamber through opening

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CN103717970B (en) 2017-03-22
WO2012161609A1 (en) 2012-11-29
EP2715232A1 (en) 2014-04-09

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