CN103717970B - Combustor with bi-directional manifold for dynamics damping - Google Patents
Combustor with bi-directional manifold for dynamics damping Download PDFInfo
- Publication number
- CN103717970B CN103717970B CN201180070864.5A CN201180070864A CN103717970B CN 103717970 B CN103717970 B CN 103717970B CN 201180070864 A CN201180070864 A CN 201180070864A CN 103717970 B CN103717970 B CN 103717970B
- Authority
- CN
- China
- Prior art keywords
- burner
- stream
- way manifold
- air path
- resonantron
- 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.)
- Expired - Fee Related
Links
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
-
- 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
Technical field
The present invention relates generally to gas-turbine unit and relates more specifically to a kind of band for gas-turbine unit
There is the burner of two-way manifold, wherein described two-way manifold is used as Helmholtz（Helmholtz）Type resonator is to damp combustion
Power in burner（dynamics）.
Background technology
Generally, mixture of the gas-turbine unit to compressed air with compressed fuel burns, to produce
The burning gases of heat.The burning gases of heat may be used to provide useful mechanical work.Burning can started around gas turbine
Occur in multiple burners of the longitudinal axis radial positioning of machine.As the turbulent flow property in combustion process closes sky with being discharged into
Large volume strain energy in chamber, such burner may easily receive the various of the transient pressure vibration of the amplitude of burning initiation
Pattern and frequency influence.If one of frequency band is the natural frequency band pair with part or subsystem in gas-turbine unit
Should, then be likely to result in the damage of the part or whole engine.
Traditionally, the known method for suppressing these pressure oscillations is concentrated on and decouples excitation source and feedback mechanism
Aspect.Generally, such restraining device is only effective in the limited range of operation of burner.
Accordingly, it would be desirable to improve burner design and operation method.Preferably, these design and method can be dynamic to burner
Power and its frequency range are limited, to prevent which is caused to damage and guarantee sufficient component life.
The content of the invention
Present invention accordingly provides a kind of burner for being burnt to air stream and The fuel stream.The burner can be wrapped
Include：Multiple fuel nozzles；The air path of the air stream is carried wherein, the air path leads to the fuel nozzle；With
And manifold, the manifold is positioned in the air path of the fuel nozzle upstream end.The manifold can include multiple
Resonantron.
The present invention further provides a kind of method of the burner of operating gas turbine engine.Methods described can be wrapped
Include following steps：Surrounding air stream, reduced oxygen gas stream and The fuel stream are burnt；Produce combustion powered；Positioning bidirectional manifold with
Which is made to connect with the surrounding air stream and the reduced oxygen gas stream；Multiple resonantrons are positioned around the two-way manifold；And adjust
The whole resonantron size is described combustion powered to damp.
The present invention further provides a kind of chemistry for being burnt to surrounding air stream, reduced oxygen gas stream and The fuel stream
Metering（stoichiometric）Waste gas recycle burning device.The burner casing includes：Multiple fuel nozzles；Wherein band has been
The ambient air path of surrounding air stream is stated, the ambient air path leads to the fuel nozzle；Wherein there is the hypoxemia
The hypoxemia recycling entrance of air-flow；And two-way manifold, the two-way manifold and the surrounding air stream and/or the low oxygen
Stream connection.The two-way manifold can include multiple resonantrons.
When with reference to some accompanying drawings and appended claims to read described in detail below, the technology in art
Personnel are apparent that these and other features and advantage of of the invention and corresponding patent.
Description of the drawings
Fig. 1 is the schematic diagram of gas-turbine unit.
Fig. 2 be with can the burner of two-way manifold and multiple resonantrons as described in this specification side cross-sectional, view.
Fig. 3 is the amplification side cross-sectional, view of a part for burner shown in Fig. 2, there is shown with two-way manifold and resonance
Pipe.
Fig. 4 is the schematic diagram of the example of Helmholtz resonator.
Specific embodiment
Referring now to accompanying drawing, wherein in some accompanying drawings, like numeral refers to similar components, and Fig. 1 is illustrated can be such as this specification
The schematic diagram of described gas-turbine unit 10.Gas-turbine unit 10 may include compressor 15.Compressor 15 compresses
Into air-flow 20.Compressed air stream 20 is transported to burner 25 by compressor 15.Burner 25 by compressed air stream 20 with it is pressurized
The fuel stream 30 mixes, and puts burning mixt to produce combustion-gas flow 35.Although illustrating only single burner 25, gas turbine
Engine 10 may also comprise any amount of burner 25.Then, combustion-gas flow 35 is transported on turbine 40.Combustion-gas flow
35 pairs of turbines 40 are driven to produce mechanical work.The mechanical work produced in turbine 40 drives compressor via axle 45
15, and drive the external loading 50 such as generator and similar installation.
Gas-turbine unit 10 can use natural gas, various types of synthesis gas and/or other types fuel.Combustion gas
Turbogenerator 10 can be the General Electric Co. Limited positioned at New York Schenectady（General Electric
Company）Any one of various different gas-turbine unit provided with similar company.Gas-turbine unit
10 can have different configurations and can use other types part.In this manual, it is possible to use other kinds of gas turbine
Engine.In this manual, also multiple gas-turbine units, other kinds of turbine and other types can be generated electricity
Equipment is used together.
Fig. 2 illustrates the example of burner 25.In this example, stoichiometry waste gas recycling（“SEGR”）Burner
100 are illustrated.This specification can also use other kinds of burner.Stoichiometry waste gas recycle burning device 100 may include
Multiple fuel nozzles 110, the fuel nozzle are positioned in end cap 120.Although illustrating five（5）Fuel nozzle 110, but
Any quantity fuel nozzle 110 can also be used in this specification.Fuel nozzle 110 can be via one or more fuel inlets
130 connecting with The fuel stream 30.Hypoxemia recycling entrance 140 can also position to provide reduced oxygen gas stream 150 around end cap 120
On fuel nozzle 110.Reduced oxygen gas stream 150 can be via stoichiometry waste gas recovery compressor（Do not show that）With similar installation from
Turbine 40 is transmitted.
Stoichiometry waste gas recycle burning device 100 can also include combustion liner 160.Combustion liner 160 can be at which
Middle restriction combustion zone 170.Fair water sleeves 180 can surround combustion liner 160, and can be for the environment from compressor 15
Air stream 20 limits ambient air path 190 wherein.Housing 200 can surround fair water sleeves 180 and combustion liner 160.Transition
Connector 210 is can be positioned at the downstream of combustion zone 170.
Bleeding point 220 can be positioned around housing 200, and can be existed with the ambient air path 190 of fair water sleeves 180
On one direction connection, and with fuel nozzle 110 and hypoxemia recycling entrance 140 connect on other direction.Bleeding point 220
Can connect with turbine 40 and other devices.In jet mode, extend into air-flow 20 along ambient air path 190,
In the ambient air path, the entrance air-flow is in the downstream of fuel nozzle 110 with reduced oxygen gas stream 150 and The fuel stream 130
It is mixed to be incorporated in burning in combustion zone 170.Or, a part of into air-flow 20 can be extracted out via bleeding point 220, while remaining
Stream continue towards fuel nozzle 110.Under extraction pattern, a part for reduced oxygen gas stream 150 also can be taken out via bleeding point 220
Go out.In this manual, it is possible to use other configurations and miscellaneous part.
End cap 120 may also include two-way manifold 230 mutually to fit with jet mode and extraction pattern, that is, accommodate injection stream and enter
In entering burner 100 or accommodate extraction flow.Two-way manifold 230 can be big circle in shape, and can include circular empty
Chamber 240.Two-way manifold 230 may also include multiple resonantrons 250, and the resonantron extends between cavity 240, and extend towards
Fair water sleeves 180 in ambient air path 190.
As shown in figure 4, two-way manifold 230 serves as Helmholtz resonator 260 to a great extent.Therefore, Helmholtz
Resonator 260 includes the cavity 240 for serving as main body 270 and the resonantron 250 for serving as throat 280.Substantially limit, Hai Muhuo
Hereby resonator 260 is sound chamber（acoustical chamber）, it includes pressure fluid so as to concrete frequency to be shaken
Swing.The geometric configuration of Helmholtz resonator 260 directly determines frequency of oscillation.If Fluid pressure ripple because external force affects
It is dynamic, then resonator 260 can be tuned to the amplitude that these fluctuate is damped in the case of vibration frequency.Helmholtz is altogether
The device 260 that shakes includes the throat 280 of main body 270 and diameter less than main body 270.Pressure fluid into throat 280 is to collect leading
In body 270, the pressure in main body 270 is more than exterior fluid pressure.Now, the fluid in main body 270 via throat 280 from
Open, so as to reduce the pressure in main body 270.Lower pressure lures that fluid reenters main body 270 into, and so, process can repeat
Carry out.The resonant frequency of Helmholtz resonator 260 is set up in air circle movement.
As described above, the resonant frequency of Helmholtz resonator 260 is mainly determined by its geometric configuration.Definitely
Say, the Helmholtz resonator 60 of cylinder can produce resonant frequency " f ", and the resonant frequency is based partially on below equation：f=
c/2Π*√d2/LHD2.In this equation, " c " is by fluid（For example, air, fuel, diluent etc.）In the velocity of sound,
" d " is the diameter of throat 280, 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
Degree.In this example, the configuration of main body 270, i.e. circular cavity 240, through fixed so that resonant frequency can be by changing
Throat 280（That is resonantron 250）Length and diameter changing.Thus, resonantron 250 can be adjusted to size for some
Frequency range is damped, such as to combustion hardware and the frequency range of manifold 230 most serious itself.In this manual, can be with
Using any amount of resonantron 250 in any required size, shape or configuration.In this manual, can also be used together
Different configuration of resonantron 250 is damping different frequency scope.
Therefore, the Helmholtz resonator 260 that two-way manifold 130 is formed is in this manual by damping some frequency models
Enclose and to prevent high cycle fatigue.In addition, no matter two-way manifold 230 is run with jet mode or extraction pattern, Helmholtz
Resonator 260 all provides such protection.Although this specification is retouched to stoichiometry waste gas recycle burning device 100
State, but Helmholtz resonator 260 can also be suitable for other kinds of burner and be suitable for and undergo hunting of frequency and analogue
Other types device.In this manual, it is possible to use unidirectional, two-way or multidirectional stream.
It should be clear that foregoing teachings merely relate to some embodiments of of the invention and corresponding patent.Skill in art
Art personnel can make various changes in the case of the overall spirit without departing substantially from the present invention and scope in this manual and repair
Change, overall spirit wherein of the invention and scope are limited by appended claims and its equivalent.
Claims (19)
1. a kind of burner for being burnt to air stream and The fuel stream, the burner include：
Multiple fuel nozzles；
Wherein there is the air path of the air stream, the air path leads to the plurality of fuel nozzle；And
Two-way manifold, the two-way manifold are located in the air path of the plurality of fuel nozzle upstream end；
Wherein described two-way manifold includes multiple resonantrons, and wherein described two-way manifold is with the wherein hypoxemia with reduced oxygen gas stream again
Loop head is connected.
2. burner as claimed in claim 1, the burner are stoichiometry waste gas recycle burning device.
3. burner as claimed in claim 1, wherein described air stream extends in a first direction and the reduced oxygen gas stream exists
Second party is upwardly extended.
4. burner as claimed in claim 1, wherein described air path are limited between combustion liner and fair water sleeves.
5. burner as claimed in claim 4, wherein described air path include bleeding point.
6. burner as claimed in claim 1, which further includes jet mode and extraction pattern, wherein described two-way manifold
Injection stream is accommodated respectively in burner under jet mode and under extraction pattern and accommodates what is be evacuated from air path
Extraction flow.
7. burner as claimed in claim 1, wherein described two-way manifold include circular cavity.
8. burner as claimed in claim 1, wherein described two-way manifold and the plurality of resonantron are configured to Helmholtz
Resonator.
9. burner as claimed in claim 8, wherein described two-way manifold are configured to the main body of the Helmholtz resonator.
10. burner as claimed in claim 8, wherein the plurality of resonantron are configured to the larynx of the Helmholtz resonator
Portion.
11. burners as claimed in claim 8, wherein described Helmholtz resonator is to hindering from the vibration for wherein passing through
Buddhist nun.
12. burners as claimed in claim 1, wherein the plurality of resonantron each have length and diameter.
13. burners as claimed in claim 12, wherein the plurality of resonantron is each with the frequency with the burner
Corresponding predetermined length and predetermined diameter.
A kind of 14. methods of the burner for operating gas turbine engine, methods described include：
Surrounding air stream, reduced oxygen gas stream and The fuel stream are burnt；
Produce combustion powered；
Arrange two-way manifold to connect with the surrounding air stream and the reduced oxygen gas stream；
Around the two-way manifold, multiple resonantrons are set；And
It is described combustion powered to damp to adjust the plurality of resonantron.
A kind of 15. stoichiometry waste gas recycle burnings for being burnt to surrounding air stream, reduced oxygen gas stream and The fuel stream
Device, the stoichiometry waste gas recycle burning device include：
Multiple fuel nozzles；
Wherein there is the ambient air path of the surrounding air stream, the ambient air path leads to the plurality of fuel spray
Mouth；
Wherein the hypoxemia with the reduced oxygen gas stream recycles entrance；And
Two-way manifold, the two-way manifold are connected with the surrounding air stream and the reduced oxygen gas stream；
Wherein described two-way manifold includes multiple resonantrons.
16. stoichiometry waste gas recycle burning devices as claimed in claim 15, wherein described two-way manifold are included in first
The upwardly extending surrounding air stream in side and the reduced oxygen gas stream for extending in a second direction.
17. stoichiometry waste gas recycle burning devices as claimed in claim 15, which further includes jet mode and pumping
Pattern, wherein described two-way manifold accommodate injection stream under jet mode and under extraction pattern respectively in burner and accommodate
From the extraction flow is evacuated by ambient air path.
18. stoichiometry waste gas recycle burning devices as claimed in claim 15, wherein described two-way manifold and the plurality of
Resonantron is configured to Helmholtz resonator.
19. stoichiometry waste gas recycle burning devices as claimed in claim 15, wherein the plurality of resonantron each have
Predetermined length corresponding with the frequency of the burner and predetermined diameter.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/RU2011/000358 WO2012161609A1 (en) | 2011-05-25 | 2011-05-25 | Combustor with bi-directional manifold for dynamics damping |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103717970A CN103717970A (en) | 2014-04-09 |
| CN103717970B true CN103717970B (en) | 2017-03-22 |
Family
ID=45351086
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201180070864.5A Expired - Fee Related CN103717970B (en) | 2011-05-25 | 2011-05-25 | Combustor with bi-directional manifold for dynamics damping |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP2715232A1 (en) |
| CN (1) | CN103717970B (en) |
| WO (1) | WO2012161609A1 (en) |
Citations (4)
| 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 |
| 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 (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7334408B2 (en) * | 2004-09-21 | 2008-02-26 | Siemens Aktiengesellschaft | Combustion chamber for a gas turbine with at least two resonator devices |
| 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 |
-
2011
- 2011-05-25 WO PCT/RU2011/000358 patent/WO2012161609A1/en active Application Filing
- 2011-05-25 CN CN201180070864.5A patent/CN103717970B/en not_active Expired - Fee Related
- 2011-05-25 EP EP11797281.0A patent/EP2715232A1/en not_active Withdrawn
Patent Citations (4)
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2715232A1 (en) | 2014-04-09 |
| CN103717970A (en) | 2014-04-09 |
| WO2012161609A1 (en) | 2012-11-29 |
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| C06 | Publication | ||
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| C10 | Entry into substantive examination | ||
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170322 Termination date: 20170525 |
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| CF01 | Termination of patent right due to non-payment of annual fee |