CN104595928B - Acoustic flame tube of diffusion combustion chamber - Google Patents
Acoustic flame tube of diffusion combustion chamber Download PDFInfo
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- CN104595928B CN104595928B CN201510035923.5A CN201510035923A CN104595928B CN 104595928 B CN104595928 B CN 104595928B CN 201510035923 A CN201510035923 A CN 201510035923A CN 104595928 B CN104595928 B CN 104595928B
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Abstract
The invention relates to the technical field of gas turbines, and particularly discloses an acoustic flame tube of a diffusion combustion chamber, which comprises a head nozzle hole and a flame tube body, wherein the head nozzle hole is formed in the front end of the flame tube body and used for installing a nozzle, an opening in the rear end of the flame tube body is used for connecting a transition section, the flame tube body is used for limiting the flow of reactants, a cooling structure and a main combustion hole are arranged on the flame tube body, the acoustic flame tube further comprises a combustion chamber cover cap and a resonator, the combustion chamber cover cap is arranged between the head nozzle hole and the flame tube body, a plurality of divergent cooling holes are formed in the combustion chamber cover cap, the number of resonators is multiple, and the resonators are arranged on the combustion chamber cover cap and are in airtight connection with a working medium in the flame tube body. The invention can effectively adjust the frequency in the combustion chamber and restrain the thermoacoustic oscillation.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to an acoustic flame tube of a diffusion combustion chamber suitable for hydrogen-rich fuel.
Background
For heavy duty gas turbines, as the parameter rating increases, the average temperature in the combustion chamber also increases, so the risk of combustion chamber thermo-acoustic oscillations increases. The essence of the thermoacoustic oscillation is the coupling of heat release fluctuation and pressure fluctuation inside the combustion chamber, the thermoacoustic oscillation can lead to the increase of combustion pollutants and the increase of tempering risk on the one hand, and can lead to the damage to the structure of the combustion chamber on the other hand, thus leading to the reduction of the service life of the combustion chamber.
Control and prediction of thermoacoustic oscillations is a difficult problem for heavy duty gas turbine combustors. The thermoacoustic oscillation control method comprises active control and passive control. The active control means includes adjusting the fuel distribution inside the combustion chamber to change the heat release profile inside the combustion chamber, primarily by applying a dynamic adjustment to the fuel control valve in phase opposition to the combustion chamber oscillation frequency to dampen oscillations inside the combustion chamber. Passive control attenuates the relevant amplitude by arranging the helmholtz resonator.
Generally speaking, it is believed that the lean premixed combustors are more susceptible to thermo-acoustic oscillations, whereas conventional combustors are relatively less susceptible to thermo-acoustic oscillations due to the fact that the more cooling holes present in the liner can dissipate the conversion of thermal energy to acoustic energy. However, when the combustion chamber is burned with the hydrogen rich fuel, the flame characteristics in the combustion chamber are largely changed. In recent years, however, several industrial applications have also developed thermoacoustic oscillations in diffusion combustors burning hydrogen-rich fuels, causing significant economic losses. The reasons for this phenomenon mainly include two aspects: (1) the increase of the parameters of the gas turbine causes the increase of the average temperature inside the combustion chamber and the increase of the heat release intensity, and the corresponding heat release fluctuation causes larger influence; (2) the hydrogen-rich fuel has high activity and high flame propagation speed, and is more sensitive to internal pressure fluctuation in the combustion chamber.
In the prior art: in patent publication No. CN101922711A, general electric company discloses a resonator assembly for mitigating dynamics in a gas turbine, the resonator assembly being respectively connected to combustors, by selectively arranging and adjusting a plurality of resonators to suppress one or more out-of-phase and in-phase dynamic interactions of exhaust fluid from a plurality of serially arranged combustors; in patent publication No. CN102003286A, general electric company proposed an acoustically enhanced gas turbine combustor supply strategy in which pressure oscillations in the combustor are damped or damped by arranging variable geometry resonators and corresponding controllers on the fluid injection system upstream of the gas turbine combustor; in the patent with publication number CN101263343A, siemens corporation invented a method and apparatus for damping thermoacoustic oscillations in a gas turbine, in which a resonator was mounted on a casing of a combustion chamber, the resonator and the combustion chamber were communicated through two pipes, so that the thermoacoustic oscillation problem in a certain frequency band could be effectively eliminated/avoided; in the patent publication CN101061353A, siemens ag invented a combustion chamber having at least one combustion chamber wall and at least one resonator device arranged in the combustion chamber wall, by means of which resonators certain frequencies of the combustion pulsations are damped; in patent publication No. CN1551965A, alstoni discloses a vibration damping device for reducing combustion pulsations in a gas turbine plant, which has a combustion chamber wall in the form of a double wall and which hermetically closes off an intermediate chamber with an outer wall surface portion and an inner wall surface portion, with this structural improvement to damp pulsations of certain frequencies formed in the combustion chamber; in patent publication CN1615416A, alstoni has invented a new gas turbine combustion chamber structure, in order to damp thermo-acoustic vibrations in the combustion chamber, at least one helmholtz damper is arranged, the damping volume of which is connected to the combustion chamber via a duct, while the damping frequency of the helmholtz damper is adjustable.
Disclosure of Invention
Technical problem to be solved
The invention aims to provide an acoustic flame tube of a diffusion combustion chamber, which is used for effectively adjusting the frequency in the combustion chamber and inhibiting thermoacoustic oscillation.
(II) technical scheme
In order to solve the technical problem, the invention provides an acoustic flame tube of a diffusion combustion chamber, which comprises a head nozzle hole and a flame tube barrel, wherein the head nozzle hole is formed in the front end of the flame tube barrel and used for installing a nozzle, an opening in the rear end of the flame tube barrel is used for connecting a transition section, the flame tube barrel is used for limiting the flow of reactants, a cooling structure and a main combustion hole are arranged on the flame tube barrel, the acoustic flame tube further comprises a combustion chamber cover cap and a resonator, the combustion chamber cover cap is arranged between the head nozzle hole and the flame tube barrel, a plurality of divergent cooling holes are formed in the combustion chamber cover cap, the number of the resonators is multiple, and the resonators are arranged on the combustion chamber cover cap and are in airtight connection with a working medium in the flame tube barrel.
Preferably, the diameter of the divergent cooling holes is 0.5mm to 1.5 mm.
Preferably, an included angle between a central axis of the divergent cooling hole and a normal direction of the combustor cap is 45 ° to 60 °.
Preferably, the radial positions of the plurality of resonant cavities are the same and are uniformly distributed along the circumferential direction.
Or the longitudinal positions of the resonant cavities are the same and the positions of the main burning holes are staggered in the circumferential direction.
Alternatively, the plurality of resonant cavities have two radial positions and the resonant cavities at the two radial positions are arranged in a staggered mode in the circumferential direction.
Or the resonant cavities at two radial positions are arranged in a staggered mode in the circumferential direction and staggered with the positions of the main burning holes.
Preferably, the resonant cavity is a helmholtz resonant cavity.
Or, the resonant cavity is a quarter-wave resonant cavity.
Preferably, the suppression frequency range of the resonant cavity at least comprises a suppression frequency range of 500 Hz-1000 Hz, a suppression frequency range of 1000 Hz-2000 Hz and a suppression frequency range of 2000 Hz-3000 Hz.
(III) advantageous effects
The acoustic flame tube of the diffusion combustion chamber is provided with a combustion chamber hood, and a series of resonant cavities are added on the combustion chamber hood, so that the frequency in the combustion chamber can be effectively adjusted, and thermoacoustic oscillation is inhibited; firstly, the thermoacoustic oscillations at different positions and different frequencies in the combustion chamber are inhibited through the resonant cavity arranged at a specific position, and the dynamic characteristics in the combustion chamber caused by different fuels and different outlet acoustic conditions can be inhibited; secondly, the structure of the hood of the head part of the traditional combustion chamber is optimized, and due to the limitation of processing technological conditions, the hood structure of the traditional combustion chamber usually consumes more cooling air and has low cooling efficiency, so that on one hand, the air quantity participating in combustion inside the combustion chamber can be reduced, the flame temperature can be indirectly improved, the pollutant emission level is higher, on the other hand, the carbon monoxide emission control difficulty is increased, and the combustion chamber hood is adopted to save the cold air quantity of the head part of the combustion chamber, improve the cooling efficiency, the saved cooling air can optimize the flame inside the combustion chamber, and is beneficial to reducing the pollutant emission.
Drawings
FIG. 1 is a front view of a diffusion combustor acoustic liner of embodiment 1 of the present invention;
FIG. 2 is a left side view of a diffusion combustor acoustic liner of embodiment 1 of the present invention;
FIG. 3 is a left side view of a diffusion combustor acoustic liner of embodiment 2 of the present invention;
FIG. 4 is a left side view of a diffusion combustor acoustic liner of embodiment 3 of the present invention;
fig. 5 is a left side view of a diffusion combustor acoustic liner of embodiment 4 of the present invention.
In the figure, 1: a head nozzle hole; 2: a flame tube body; 3: a combustion chamber hood; 4: a resonant cavity; 21: a cooling structure; 22: a main burning hole; 23: a main burner bore axis; 31: a divergent cooling aperture.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
In the description of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art. In addition, in the description of the present invention, "a plurality" means two or more unless otherwise specified.
Example 1
As shown in fig. 1 and 2, the diffusion combustor acoustic liner of the present embodiment includes: a head nozzle hole 1, a flame tube cylinder 2, a combustion chamber cover cap 3 and a resonator 4.
The head nozzle hole 1 is arranged at the front end of the flame tube barrel body 2, the head nozzle hole 1 is used for installing a nozzle, the rear end opening of the flame tube barrel body 2 is used for connecting a transition section, the flame tube barrel body 2 is used for limiting the flowing of reactants, and the flame tube barrel body 2 is provided with a cooling structure 21 and a main combustion hole 22.
The combustion chamber cap 3 is established between head nozzle hole 1 and flame tube barrel 2, is equipped with a plurality of cooling holes 31 of dispersing on the combustion chamber cap 3, and a plurality of cooling holes 31 of dispersing can be for following circumference to become matrix form evenly distributed, and the syntonizer 4 is a plurality of, and a plurality of syntonizers 4 all establish on combustion chamber cap 3 and with the inside working medium airtight connection of flame tube barrel 2. This structure is through arranging resonant cavity 4 on combustor cap 3, and resonant cavity 4 is connected with the inside working medium of flame tube through dispersing cooling hole 31, and the thermoacoustic oscillation of different positions, different frequencies in the dissipation combustor is to different fuel, the inside dynamic characteristic of combustor that different export acoustics conditions lead to restraines. In addition, the specific unevenness of the resonator 4 should be selected according to actual conditions, and different layouts are suitable for different combustion chamber structures, different fuel combustion chambers and different outlet acoustic conditions.
As shown in fig. 2, in the present embodiment, the plurality of resonant cavities 4 have the same radial position and are uniformly distributed along the circumferential direction.
The diameter of the divergent cooling hole 31 is 0.5mm to 1.5 mm. The included angle between the central axis of the divergent cooling hole 31 and the normal direction of the combustor cap 3 is 45-60 degrees.
The cavity 4 may be a helmholtz or quarter wave cavity. The suppression frequency range of the resonant cavity 4 includes at least:
(1) the suppression frequency range is 500 Hz-1000 Hz;
(2) the suppression frequency range is 1000 Hz-2000 Hz;
(3) the suppression frequency range is 2000 Hz-3000 Hz.
Example 2
As shown in fig. 3, the plurality of resonators 4 of the acoustic liner of the diffusion combustor of the present embodiment have the same radial position and are circumferentially offset from the main combustion holes 22 or the main combustion hole axes 23 (matching the number of the main combustion holes 22).
Example 3
As shown in fig. 4, the plurality of resonant cavities 4 of the acoustic combustor liner of the diffusion combustor of the present embodiment has two radial positions and the resonant cavities 4 of the two radial positions are arranged in a staggered manner in the circumferential direction.
Example 4
As shown in fig. 5, the plurality of resonant cavities 4 of the acoustic flame tube of the diffusion combustion chamber of the present embodiment have two radial positions, and the resonant cavities 4 at the two radial positions are circumferentially staggered and staggered from the positions of the main combustion holes 22 or the main combustion hole axes 23 (matching with the number of the main combustion holes 22).
The acoustic flame tube of the diffusion combustion chamber is provided with a combustion chamber hood, and a series of resonant cavities are added on the combustion chamber hood, so that the frequency in the combustion chamber can be effectively adjusted, and thermoacoustic oscillation is inhibited; firstly, the thermoacoustic oscillations at different positions and different frequencies in the combustion chamber are inhibited through the resonant cavity arranged at a specific position, and the dynamic characteristics in the combustion chamber caused by different fuels and different outlet acoustic conditions can be inhibited; secondly, the structure of the hood of the head part of the traditional combustion chamber is optimized, and due to the limitation of processing technological conditions, the hood structure of the traditional combustion chamber usually consumes more cooling air and has low cooling efficiency, so that on one hand, the air quantity participating in combustion inside the combustion chamber can be reduced, the flame temperature can be indirectly improved, the pollutant emission level is higher, on the other hand, the carbon monoxide emission control difficulty is increased, and the combustion chamber hood is adopted to save the cold air quantity of the head part of the combustion chamber, improve the cooling efficiency, the saved cooling air can optimize the flame inside the combustion chamber, and is beneficial to reducing the pollutant emission.
The embodiments of the present invention have been presented for purposes of illustration and description, and are not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiment was chosen and described in order to best explain the principles of the invention and the practical application, and to enable others of ordinary skill in the art to understand the invention for various embodiments with various modifications as are suited to the particular use contemplated.
Claims (5)
1. An acoustic flame tube of a diffusion combustion chamber comprises a head nozzle hole and a flame tube barrel, wherein the head nozzle hole is formed in the front end of the flame tube barrel, the head nozzle hole is used for installing a nozzle, an opening in the rear end of the flame tube barrel is used for connecting a transition section, the flame tube barrel is used for limiting the flow of reactants, and a cooling structure and a main combustion hole are formed in the flame tube barrel;
the included angle between the central axis of the divergent cooling hole and the normal direction of the combustion chamber hood is 45-60 degrees;
the plurality of resonant cavities have two radial positions, and the resonant cavities at the two radial positions are arranged in a staggered manner in the circumferential direction and staggered with the positions of the main combustion holes; or the radial positions of the resonant cavities are the same and are uniformly distributed along the circumferential direction; or the radial positions of the resonant cavities are the same and the positions of the main combustion holes are staggered in the circumferential direction; or the plurality of resonant cavities have two radial positions and the resonant cavities at the two radial positions are arranged in a staggered way in the circumferential direction.
2. The diffusion combustor acoustic combustor basket of claim 1, wherein the diverging cooling holes have a diameter of 0.5mm to 1.5 mm.
3. The diffusion combustor acoustic liner of claim 1, wherein the resonant cavity is a helmholtz resonant cavity.
4. The diffusion combustor acoustic combustor basket of claim 1, wherein the resonant cavity is a quarter wave resonant cavity.
5. The acoustic combustor basket of claim 1, wherein the suppression frequency range of the resonant cavity includes at least a suppression frequency range of 500Hz to 1000Hz, a suppression frequency range of 1000Hz to 2000Hz, and a suppression frequency range of 2000Hz to 3000 Hz.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510035923.5A CN104595928B (en) | 2015-01-23 | 2015-01-23 | Acoustic flame tube of diffusion combustion chamber |
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| CN201510035923.5A CN104595928B (en) | 2015-01-23 | 2015-01-23 | Acoustic flame tube of diffusion combustion chamber |
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| CN104595928A CN104595928A (en) | 2015-05-06 |
| CN104595928B true CN104595928B (en) | 2020-02-14 |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3543610B1 (en) * | 2018-03-23 | 2021-05-05 | Ansaldo Energia Switzerland AG | Gas turbine having a damper |
| CN109737450B (en) * | 2018-12-11 | 2019-12-03 | 北京航空航天大学 | Combustion chambers burn oscillation control device and combustion chambers burn oscillation control method |
| CN113719861B (en) * | 2021-09-10 | 2022-12-06 | 中国联合重型燃气轮机技术有限公司 | Combustion chamber and gas turbine with same |
| CN113669759A (en) * | 2021-09-13 | 2021-11-19 | 中国联合重型燃气轮机技术有限公司 | Cap for a gas turbine |
| CN113739203B (en) * | 2021-09-13 | 2023-03-10 | 中国联合重型燃气轮机技术有限公司 | Cap assembly for a combustor |
| CN113739202B (en) * | 2021-09-13 | 2023-04-25 | 中国联合重型燃气轮机技术有限公司 | Cap with thermal-acoustic vibration adjusting function |
| CN115355534B (en) * | 2022-09-05 | 2024-03-12 | 中国联合重型燃气轮机技术有限公司 | Gas turbine fuel mixing system and gas turbine |
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| CN1639512A (en) * | 2002-03-07 | 2005-07-13 | 西门子公司 | Gas turbine |
| CN101169252A (en) * | 2007-11-29 | 2008-04-30 | 北京航空航天大学 | Aerial engine lean premixed preevaporated low contamination combustion chamber |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1007919B (en) * | 1985-04-01 | 1990-05-09 | 英萨科公司 | Method and equipment for burning macro particles fuel |
| DE19851636A1 (en) * | 1998-11-10 | 2000-05-11 | Asea Brown Boveri | Damping device for reducing vibration amplitude of acoustic waves for burner for internal combustion engine operation is preferably for driving gas turbo-group, with mixture area for air and fuel |
| AR023360A1 (en) * | 1998-12-30 | 2002-09-04 | Shell Int Research | PULSE COMBUSTION APPARATUS, A METHOD FOR IMPROVING THE FLUID FLOW IN A NATURAL GAS PRODUCTION WELL AND A METHOD FOR HEATING A SUB-GROUND FORMATION WITH SUCH DEVICE |
| US7334408B2 (en) * | 2004-09-21 | 2008-02-26 | Siemens Aktiengesellschaft | Combustion chamber for a gas turbine with at least two resonator devices |
| DE102011081962A1 (en) * | 2011-09-01 | 2013-03-07 | Siemens Aktiengesellschaft | Combustion chamber for a gas turbine plant |
| CN203464337U (en) * | 2013-09-04 | 2014-03-05 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Structure of transition section of combustion chamber of combustion gas turbine |
| CN204665355U (en) * | 2015-01-23 | 2015-09-23 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Diffusion burner acoustics burner inner liner |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1639512A (en) * | 2002-03-07 | 2005-07-13 | 西门子公司 | Gas turbine |
| CN101169252A (en) * | 2007-11-29 | 2008-04-30 | 北京航空航天大学 | Aerial engine lean premixed preevaporated low contamination combustion chamber |
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